Relevant bibliographies by topics / Aerodynamic angle

Academic literature on the topic 'Aerodynamic angle'

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Published: 14 March 2023

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Journal articles on the topic "Aerodynamic angle"

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Tripathi, Manish, Mahesh M. Sucheendran, and Ajay Misra. "Experimental analysis of cell pattern on grid fin aerodynamics in subsonic flow." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 234, no. 3 (September 5, 2019): 537–62. http://dx.doi.org/10.1177/0954410019872349.

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Grid fins consisting of a lattice of high aspect ratio planar members encompassed by an outer frame are unconventional control surfaces used on numerous missiles and bombs due to their enhanced lifting characteristics at high angles of attack and across wider Mach number regimes. The current paper accomplishes and compares the effect of different grid fin patterns on subsonic flow aerodynamics of grid fins by virtue of the determination of their respective aerodynamic forces. Furthermore, this study deliberates the impact of gap variation on aerodynamics of different patterns. Results enunciate enhanced aerodynamic efficiency, and lift slope for web-fin cells and single diamond patterns compared to the baseline model. Moreover, the study indicates improved aerodynamic performance for diamond patterns with higher gaps by providing elevated maximum lift coefficient, delayed stall angle, and comparable drag at lower angles. The study established the presence of an additional effect termed as the inclination effect alongside the cascade effect leading to deviations with respect to lift, stall, and aerodynamic efficiency amongst different gap variants of the individual patterns. Thus, optimization based on the aerodynamic efficiency, stall angle requirements, and construction cost by optimum pattern and gap selection can be carried out through this analysis, which can lead to elevated aerodynamic performance for grid fins.
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Sun, Xiao-Ying, Tian-E. Li, Guo-Chang Lin, and Yue Wu. "A study on the aerodynamic characteristics of a stratospheric airship in its entire flight envelope." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 232, no. 5 (August 2, 2017): 902–21. http://dx.doi.org/10.1177/0954410017723358.

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Aerodynamic characteristics of a stratospheric airship in its entire flight envelope, including take-off, ascending, cruising, descending, and landing, is an important part of its research topic. In this paper, experiments of wind pressure measurement on a 1/30-scale stratospheric airship model were carried out to obtain a better assessment of the aerodynamic characteristics during the cruising process. Based on the wind pressure distribution, the effects of pitch angle, yaw angle, and combined angles (pitch angle and yaw angle acted simultaneously) on the aerodynamics of the airship were analyzed. In addition, the contributions of different portions of the airship hull (namely head, middle, and tail) to the aerodynamic forces and moments were discussed. The experimental results imply that the tail portion is the main contributor to pressure drag force. The combined angles significantly increase aerodynamic forces and rolling moment, and the rolling moment produced by the middle portion accounts for the major proportion. Secondly, the computational fluid dynamics method was verified and employed to study the aerodynamic characteristics of the full-scale model in its entire flight envelope based on the decision of the wind environment parameters and attitude. As a main result, it can be concluded that, more attention should be paid to the airship when it is located in the troposphere and near the ground with an inclined take-off angle.
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Taiming, Huang, Zhuang Xiaodong, Wan Zhongmin, and Gu Zhengqi. "Experimental and numerical investigations of the vehicle aerodynamic drag with single-channel rear diffuser." Proceedings of the Institution of Mechanical Engineers, Part D: Journal of Automobile Engineering 234, no. 8 (February 7, 2020): 2216–27. http://dx.doi.org/10.1177/0954407019893849.

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The main purpose of this paper is to reveal the drag reduction mechanism of single-channel rear diffuser on the vehicle aerodynamic drag and to obtain the relationship between the structure parameters of rear diffuser and the vehicle aerodynamic drag. The influence of the single-channel rear diffuser on the aerodynamic drag is studied using the Reynolds-averaged method with the 25° slant Ahmed model. The accuracy of the numerical method is validated by means of a wind tunnel test. The aerodynamic performance of the Ahmed model with different vertical diffuser angles, lateral diffuser angles, and channel widths is discussed. The results demonstrate that the vortex location will be influenced by the vertical diffuser angle, and with the vortex core approaching to the model, the aerodynamic drag will increase. The aerodynamic drag reaches the minimum value with a vertical diffuser angle of 10.46°. Moreover, the aerodynamic drag decreases with increasing channel width. Finally, the aerodynamic drag can be reduced by 5.3%, when the vertical diffuser angle, lateral diffuser angle, and channel width are 10.46°, 0°, and 351 mm, respectively.
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Baigang, Mi, and Yu Jingyi. "An Improved Nonlinear Aerodynamic Derivative Model of Aircraft at High Angles of Attack." International Journal of Aerospace Engineering 2021 (September 8, 2021): 1–12. http://dx.doi.org/10.1155/2021/5815167.

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The classical aerodynamic derivative model is widely used in flight dynamics, but its application is extremely limited in cases with complicated nonlinear flows, especially at high angles of attack. A modified nonlinear aerodynamic derivative model for predicting unsteady aerodynamic forces and moments at a high angle of attack is developed in this study. We first extend the higher-order terms to describe the nonlinear characteristics and then introduce three more influence parameters, the initial angle of attack, the reduced frequency, and the oscillation amplitude, to correct the constant aerodynamic derivative terms that have higher-order polynomials for these values. The improved nonlinear aerodynamic derivative model was validated by using the NACA 0015 airfoil and the F-18 model. The results show that the improved model has a higher prediction ability at high angles of attack and has the ability to predict the aerodynamic characteristics of other unknown states based on known unsteady aerodynamic data, such as the initial angle of attack, reduced frequency, and oscillation amplitude.
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Xiang, Jinwu, Kai Liu, Daochun Li, Chunxiao Cheng, and Enlai Sha. "Unsteady aerodynamic characteristics of a morphing wing." Aircraft Engineering and Aerospace Technology 91, no. 1 (January 7, 2018): 1–9. http://dx.doi.org/10.1108/aeat-04-2017-0101.

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Purpose The purpose of this paper is to investigate the unsteady aerodynamic characteristics in the deflection process of a morphing wing with flexible trailing edge, which is based on time-accurate solutions. The dynamic effect of deflection process on the aerodynamics of morphing wing was studied. Design/methodology/approach The computational fluid dynamic method and dynamic mesh combined with user-defined functions were used to simulate the continuous morphing of the flexible trailing edge. The steady aerodynamic characteristics of the morphing deflection and the conventional deflection were studied first. Then, the unsteady aerodynamic characteristics of the morphing wing were investigated as the trailing edge deflects at different rates. Findings The numerical results show that the transient lift coefficient in the deflection process is higher than that of the static case one in large angle of attack. The larger the deflection frequency is, the higher the transient lift coefficient will become. However, the situations are contrary in a small angle of attack. The periodic morphing of the trailing edge with small amplitude and high frequency can increase the lift coefficient after the stall angle. Practical implications The investigation can afford accurate aerodynamic information for the design of aircraft with the morphing wing technology, which has significant advantages in aerodynamic efficiency and control performance. Originality/value The dynamic effects of the deflection process of the morphing trailing edge on aerodynamics were studied. Furthermore, time-accurate solutions can fully explore the unsteady aerodynamics and pressure distribution of the morphing wing.
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Hu, Haode, and Dongli Ma. "Airfoil Aerodynamics in Proximity to Wavy Ground for a Wide Range of Angles of Attack." Applied Sciences 10, no. 19 (September 27, 2020): 6773. http://dx.doi.org/10.3390/app10196773.

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Wing-in-ground craft often encounter waves when flying over the sea surface, and the ground effect is more complicated than that of flat ground. Therefore, the aerodynamic characteristics of the NACA 4412 airfoil in proximity to wavy ground for a wide range of angles of attack is studied by solving the Reynolds Averaged Navier–Stokes equations. The validation of the numerical method is carried out by comparing it with the experimental data. The results show that the aerodynamic coefficients will fluctuate periodically when the airfoil moves over wavy ground at a small ride height. Except for the angle of attack of 0°, the fluctuation trend of aerodynamic coefficients at other angles of attack is the same. The analysis of aerodynamic fluctuation amplitude found that the medium angle of attack should be selected as the design cruise angle of attack for wing-in-ground craft. The time-averaged aerodynamic coefficients in the case of wavy ground are almost the same as those of flat ground. Hence, wavy ground mainly causes a fluctuation in aerodynamic coefficients. Considering the difference between aerodynamic coefficients at the angle of attack of 0° and at other angles of attack, the flow field structure at an angle of attack of 0° and 4° is analyzed. The results reveal the aerodynamic characteristics of the airfoil moving over wavy ground, which gives a deeper understanding of the ground effect in the conditions of wavy surface/ground. This has a certain guiding significance for the design of wing-in-ground craft.
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Zhang, Yanqi, and Zhaoming Zhang. "Unsteady Aerodynamic Characteristics of Antenna Rotating in Different Elevation Angles." International Journal of Antennas and Propagation 2021 (July 26, 2021): 1–16. http://dx.doi.org/10.1155/2021/5503330.

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The aerodynamic characteristics of radar antennas should be considered in computing their wind resistance and designing pedestal servo systems. In this paper, the aerodynamic characteristics of a flat plate antenna with azimuthal rotation are explored using a wind tunnel, and the effects of the antenna elevation angle and reduced frequency on the aerodynamic coefficients are analyzed. The corresponding results of numerical simulation are given to compare with the experimental results. The variation of aerodynamic coefficients with respect to the azimuth angle is found to depend on the reduced frequency and the antenna elevation angle. When the increase in antenna elevation angle is slight, the mean and root mean square values of the aerodynamic coefficients are not monotonic with respect to increases in elevation angle and may increase at individual elevation angles. When the elevation angle increases significantly, the mean, maximum, and root mean square values of the aerodynamic coefficients all significantly decrease. The simulation results are in good agreement with the experimental results, which verify the feasibility of using unsteady numerical simulations to obtain the flow field structure when the antenna is rotating. This approach allows the influence mechanism of the elevation angle change on the aerodynamic characteristics of the rotating antenna to be identified.
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Wang, Xu, Yuanhao Qian, Zengshun Chen, Xiao Zhou, Huaqiang Li, and Hailin Huang. "Numerical studies on aerodynamics of high-speed railway train subjected to strong crosswind." Advances in Mechanical Engineering 11, no. 11 (November 2019): 168781401988727. http://dx.doi.org/10.1177/1687814019887270.

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Under the action of strong crosswind, the aerodynamic behavior of a rail vehicle at high speed will be changed significantly, which could directly affect the safe operation of the vehicle. With the help of the shape of train used in China, the aerodynamic characteristics of trains with scale of 1:1 is investigated using computational fluid dynamics numerical simulation method, which consists of the variation of aerodynamics force and moment with wind yaw angle, wind speed, train speed, and nose shape. After an initial validation against Baker’s results from wind tunnel test, the numerical model is then used to investigate the aerodynamic characteristics of the trains. The numerical results indicate that lift coefficient of the M train is slightly higher than TMC1 and TMC2 trains. Regardless of aerodynamics force coefficients, TMC1 reaches the maximum at a yaw angle of 75°. Aerodynamics force coefficient increases with both wind speed and train speed, but the change of which is not linear. Comparing aerodynamic force with different geometric dimensions of train nose, it is shown that height–width ratio is insensitive to side force and rolling moment, but sensitive to lift force from the yaw angle 0°–90°. The side force coefficient, as we most concern, is less than other results, when the length–width ratio is 1 and height–width is 0.87.
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HUANG, DA, and GENXIN WU. "INVESTIGATION OF SUITABILITY FOR THE LINEAR SUPERPOSITION MODEL." Modern Physics Letters B 19, no. 28n29 (December 20, 2005): 1631–34. http://dx.doi.org/10.1142/s0217984905010086.

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An aircraft model was tested at the 3-meter low speed wind tunnel as it was oscillated with large amplitude. The unsteady aerodynamic behavior was acquired during the oscillation in yawing, rolling and yawing-rolling. The lateral-directional dynamic derivative was obtained using the mathematic model of unsteady aerodynamics and the dynamic derivative simulation. According to the principle of linear superposition, the unsteady aerodynamic parameters of the model about yaw-roll coupled motion can be obtained by the quasi-steady aerodynamic model and the result was compared with the experimental test. It was found that for the quasi-steady aerodynamic model the unsteady aerodynamic characteristic was in agreement with the test at the middle and large angle of attack (for example α ≤ 45°), but was opposite at the extremely large angle of attack (α > 45°).
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Kang, Chang-kwon, and Wei Shyy. "Analytical model for instantaneous lift and shape deformation of an insect-scale flapping wing in hover." Journal of The Royal Society Interface 11, no. 101 (December 6, 2014): 20140933. http://dx.doi.org/10.1098/rsif.2014.0933.

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In the analysis of flexible flapping wings of insects, the aerodynamic outcome depends on the combined structural dynamics and unsteady fluid physics. Because the wing shape and hence the resulting effective angle of attack are a priori unknown, predicting aerodynamic performance is challenging. Here, we show that a coupled aerodynamics/structural dynamics model can be established for hovering, based on a linear beam equation with the Morison equation to account for both added mass and aerodynamic damping effects. Lift strongly depends on the instantaneous angle of attack, resulting from passive pitch associated with wing deformation. We show that both instantaneous wing deformation and lift can be predicted in a much simplified framework. Moreover, our analysis suggests that resulting wing kinematics can be explained by the interplay between acceleration-related and aerodynamic damping forces. Interestingly, while both forces combine to create a high angle of attack resulting in high lift around the midstroke, they offset each other for phase control at the end of the stroke.
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Dissertations / Theses on the topic "Aerodynamic angle"

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Wilks, Brett Landon Burkhalter Johnny Evans. "Aerodynamics of wrap-around fins in supersonic flow." Auburn, Ala., 2005. http://repo.lib.auburn.edu/2005%20Fall/Thesis/WILKS_BRETT_54.pdf.

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Fan, Yigang. "Identification of an Unsteady Aerodynamic Model up to High Angle of Attack Regime." Diss., Virginia Tech, 1997. http://hdl.handle.net/10919/29830.

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The harmonic oscillatory tests for a fighter aircraft configuration using the Dynamic Plunge-Pitch-Roll (DyPPiR) model mount at Virginia Tech Stability Wind Tunnel are described and analyzed. The corresponding data reduction methods are developed on the basis of multirate digital signal processing techniques. Since the model is sting-mounted to the support system of DyPPiR, the Discrete Fourier Transform (DFT) is first used to identify the frequencies of the elastic modes of sting. Then the sampling rate conversion systems are built up in digital domain to resample the data at a lower rate without introducing distortions to the signals of interest. Finally linear-phase Finite Impulse Response (FIR) filters are designed by Remez exchange algorithm to extract the aerodynamic characteristics responses to the programmed motions from the resampled measurements. These data reduction procedures are also illustrated through examples. The results obtained from the harmonic oscillatory tests are then illustrated and the associated flow mechanisms are discussed. Since no significant hysteresis loops are observed for the lift and the drag coefficients for the current angle of attack range and the tested reduced frequencies, the dynamic lags of separated and vortex flow effects are small in the current oscillatory tests. However, large hysteresis loops are observed for pitch moment coefficient in the current tests. This observation suggests that at current flow conditions, pitch moment has large pitch rate and alpha-dot dependencies. Then the nondimensional maximum pitch rate q_max is introduced to characterize these harmonic oscillatory motions. It is found that at current flow conditions, all the hysteresis loops of pitch moment coefficient with same nondimensional maximum pitch rate are tangential to one another at both top and bottom of the loops, implying approximately same maximum offset of these loops from static values. Several cases are also illustrated. Based on the results obtained and those from references, a state-space model is developed to describe the unsteady aerodynamic characteristics up to the high angle of attack regime. A nondimensional coordinate is introduced as the state variable describing the flow separation or vortex burst. First-order differential equation is used to govern the dynamics of flow separation or vortex bursting through this state variable. To be valid for general configurations, Taylor series expansions in terms of the input variables are used in the determination of aerodynamic characteristics, resembling the current approach of the stability derivatives. However, these derivatives are longer constant. They are dependent on the state variable of flow separation or vortex burst. In this way, the changes in stability derivatives with the angle of attack are included dynamically. The performance of the model is then validated by the wind-tunnel measurements of an NACA 0015 airfoil, a 70 degree delta wing and, finally two F-18 aircraft configurations. The results obtained show that within the framework of the proposed model, it is possible to obtain good agreement with different unsteady wind tunnel data in high angle-of-attack regime.
Ph. D.
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Stagg, Gregory A. "An Aerodynamic Model for Use in the High Angle of Attack Regime." Thesis, Virginia Tech, 1998. http://hdl.handle.net/10919/35596.

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Harmonic oscillatory tests for a fighter aircraft using the Dynamic Plunge--Pitch--Roll model mount at Virginia Tech Stability Wind Tunnel are described. Corresponding data reduction methods are developed on the basis of multirate digital signal processing. Since the model is sting mounted, the frequencies associated with sting vibration are included in balance readings thus a linear filter must be used to extract out the aerodynamic responses. To achieve this, a Finite Impulse Response (FIR) is designed using the Remez exchange algorithm. Based on the reduced data, a state--space model is developed to describe the unsteady aerodynamic characteristics of the aircraft during roll oscillations. For this model, we chose to separate the aircraft into panels and model the local forces and moments. Included in this technique is the introduction of a new state variable, a separation state variable which characterizes the separation for each panel. This new variable is governed by a first order differential equation. Taylor series expansions in terms of the input variables were performed to obtain the aerodynamic coefficients of the model. These derivatives, a form of the stability derivative approach, are not constant but rather quadratic functions of the new state variable. Finally, the concept of the model was expanded to allow for the addition of longitudinal motions. Thus, pitching moments will be identified at the same time as rolling moments. The results show that the goal of modeling coupled longitudinal and lateral--directional characteristics at the same time using the same inputs is feasible.
Master of Science
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Sirangu, Vijaya. "AERODYNAMIC CONTROL OF SLENDER BODIES AT HIGH ANGLES OF ATTACK." University of Toledo / OhioLINK, 2010. http://rave.ohiolink.edu/etdc/view?acc_num=toledo1271365316.

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Sor, Wei Lun. "Aerodynamic Validation of Emerging Projectile Configurations." Thesis, Monterey, California. Naval Postgraduate School, 2012.

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Approved for public release; distribution is unlimited.
Ever-increasing demands for accuracy and range in modern warfare have expedited the optimization of projectile design. The crux of projectile design lies in the understanding of its aerodynamic properties early in the design phase. This research first investigated the aerodynamic properties of a standard M549, 155mm projectile. The transonic speed region was the focus of the research as significant aerodynamic variation occurs within this particular region. Aerodynamic data from wind tunnel and range testing was benchmarked against modern aerodynamic prediction programs like ANSYS CFX and Aero-Prediction 09 (AP09). Next, a comparison was made between two types of angle of attack generation methods in ANSYS CFX. The research then focused on controlled tilting of the projectile’s nose to investigate the resulting aerodynamic effects. ANSYS CFX was found to provide better agreement with the experimental data than AP09.
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Takahama, Morio, Noboru Sakamoto, and Yuhei Yamato. "Attitude Stabilization of an Aircraft via Nonlinear Optimal Control Based on Aerodynamic Data." Institute of Electrical and Electronics Engineers, 2009. http://hdl.handle.net/2237/14420.

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Mohmad, Rouyan Nurhana. "Model simulation suitable for an aircraft at high angle of attack." Thesis, Cranfield University, 2016. http://dspace.lib.cranfield.ac.uk/handle/1826/9722.

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Simulation of a dynamic system is known to be sensitive to various factors and one of them could be the precision of model parameters. While the sensitivity of flight dynamic simulation to small changes in aerodynamic coefficients is typically not studied, the simulation of aircraft required to operate in nonlinear flight regimes usually at high angles of attack can be very sensitive to such small differences. Determining the significance and impact of the differences in aerodynamic characteristics is critical for understanding the flight dynamics and designing suitable flight control laws. This thesis uses this concept to study the effect of the differences in aerodynamic data for different aerodynamic models provided for a same aircraft which is F-18 HARV combat aircraft. The aircraft was used as a prototype for the high angles of attack technology program. However modeling an aircraft at high angles of attack requires an extensive aerodynamic data which are usually di cult to access. All aerodynamic models were collected from open literature and implemented within a nonlinear six degree of freedom aircraft model. Inspection of aerodynamic data set for these models has shown mismatches for certain aerodynamic derivatives, especially at higher angles of attack where nonlinear dynamics are known to exist. Nonlinear simulations are used to analyse three different types of flight dynamic models that use look-up-tables, arc-tangent formulation and polynomial functions to represent aerodynamic data that are suitable for high angles of attack application. To achieve this, a nonlinear six degree of freedom Simulink model was developed to accommodate these aerodynamic models separately. The trim conditions were obtained for different combinations of angles of attack and airspeed and the models were linearized in each case. Properties of the resulting state matrices such as eigenvalues and eigenvectors were studied to determine the dynamic behaviour of the aircraft at various flight conditions.
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Quickel, Reuben Alexander. "Mount Interference and Flow Angle Impacts on Unshielded Total Temperature Probes." Thesis, Virginia Tech, 2019. http://hdl.handle.net/10919/89952.

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Accurately measuring the total temperature of a high-speed fluid flow is a challenging task that is required in many research areas and industry applications. The difficulty in total temperature measurement generally stems from attempting to minimize measurement error or accurately predict error so it can be accounted for. Conduction error and aerodynamic error are two very common sources of error in total temperature probe measurements. Numerous studies have been performed in prior literature to account for simple cases of both errors. However, the impacts of a mounting strut and freestream flow angle on conduction error and aerodynamic error have not been previously modeled. Both of these effects are very common in gas-turbine applications of total temperature probes. Therefore, a fundamental study was performed to analyze the impact of mount interference and freestream flow angle on a probe's conduction error and aerodynamic error. An experimental study of aerodynamic error was performed using strut-mounted thermocouples in a high-speed jet at Mach numbers ranging from 0.25-0.72. This study showed that a strut stagnation point can provide aerodynamic error reductions and insensitivity to approach Mach number. An off-angle experimental study of conduction error was also performed using strut-mounted thermocouples at pitch angles ranging from -30° to 30°. High-fidelity Computational Fluid Dynamics (CFD) simulations with Conjugate Heat Transfer (CHT) were performed in conjunction with the experiments to provide key heat transfer information and flow visualizations. It was identified that unshielded total temperature probes have reduced conduction error at off-angles, but are sensitive to changes in the freestream flow angle. A low-order method was developed to account for mount interference and flow angle effects. The developed low order method utilizes a local Mach number for aerodynamic error predictions and a local Reynolds number for conduction error predictions. This developed low-order method was validated against experiment and 3D, CFD results, and was shown to accurately capture flow angle trends, mount interference effects, and the impacts of varying probe geometry.
Master of Science
Accurately measuring the total temperature of a high-speed fluid flow is a challenging task that is required in many research areas and industry applications. Many methods exist for measuring total temperature, but the use of thermocouple based probes immersed into a flow remains a common and desirable measurement technique. The difficulty in using thermocouple based probes to acquire total temperature stems from attempting to minimize or accurately predict the probe’s measurement error. Conduction, convection, and radiation heat transfer between the fluid flow and probe create challenges for minimizing measurement error so that the accurate total temperature can be obtained. Numerous studies have been performed in prior literature to account for simple cases of each error source. However, there are many complex, practical applications in which the influence of each error source has not been studied. The impacts of a freestream flow angle and the total temperature probe’s mounting structure have not been previously modeled. Both of these effects are very common in gas-turbine applications of total temperature probes. This Thesis will present a fundamental study analyzing the impact that freestream flow angle and a probe’s mount have on a total temperature probe’s measurement error. The influence of conduction and convection heat transfer was studied experimentally for numerous probe geometries, and the impacts of a mounting strut and freestream flow angle were analyzed. A low-order method was developed to predict conduction error and aerodynamic error for total temperature probes in offangle conditions with the presence of mount interference. The developed low-order method was shown to accurately capture the effects of a mounting strut, varying probe geometry, and varying flow angle. Additionally, the low-order method was validated against experimental and 3D, CFD/CHT results.
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9

Lopera, Javier. "Aerodynamic Control of Slender Bodies from Low to High Angles of Attack through Flow Manipulation." Connect to Online Resource-OhioLINK, 2007. http://www.ohiolink.edu/etd/view.cgi?acc_num=toledo1177504352.

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Hammer, Patrick Richard. "A Discrete Vortex Method Application to Low Reynolds Number Aerodynamic Flows." University of Dayton / OhioLINK, 2011. http://rave.ohiolink.edu/etdc/view?acc_num=dayton1311792450.

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Books on the topic "Aerodynamic angle"

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United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., ed. Actuator and aerodynamic modeling for high-angle-of-attack aeroservoelasticity. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1993.

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United States. National Aeronautics and Space Administration., ed. High angle-of-attack aerodynamic characteristics of crescent and elliptic wings. Davis, CA: University of California, Dept. of Mechanical Engineering, Division of Aeronautical Science and Engineering, 1989.

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United States. National Aeronautics and Space Administration., ed. High angle-of-attack aerodynamic characteristics of crescent and elliptic wings. Davis, CA: University of California, Dept. of Mechanical Engineering, Division of Aeronautical Science and Engineering, 1989.

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Matsuo, N. Aerodynamic characteristics of general aviation at high angle of attack with the propeller slipstream. Washington DC: National Aeronautics and Space Administration, 1987.

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Klein, Vladislav. Aerodynamic parameters of High-Angle-of-Attack Research Vehicle (HARV) estimated from flight data. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1990.

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Klein, Vladislav. Aerodynamic parameters of high-angle-of-attack research vehicle (Harv) estimated from flight data. Hampton, Va: National Aeronautics and Space Administration, 1990.

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Center, Ames Research, ed. Two-dimensional high-lift aerodynamic optimization using neural networks. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1998.

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Center, Ames Research, ed. Two-dimensional high-lift aerodynamic optimization using neural networks. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1998.

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Center, Ames Research, ed. Two-dimensional high-lift aerodynamic optimization using neural networks. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1998.

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Center, Ames Research, ed. Two-dimensional high-lift aerodynamic optimization using neural networks. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1998.

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Book chapters on the topic "Aerodynamic angle"

1

Hage, W., D. W. Bechert, and M. Bruse. "Yaw Angle Effects on Optimized Riblets." In Aerodynamic Drag Reduction Technologies, 278–85. Berlin, Heidelberg: Springer Berlin Heidelberg, 2001. http://dx.doi.org/10.1007/978-3-540-45359-8_29.

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Nakamura, Y., Y. Nakajima, and W. Jia. "Aerodynamic Characteristics of Thick Delta Wing." In Fluid Dynamics of High Angle of Attack, 375–82. Berlin, Heidelberg: Springer Berlin Heidelberg, 1993. http://dx.doi.org/10.1007/978-3-642-52460-8_26.

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Morishita, E., H. Koyama, T. Kitamori, and Y. Aihara. "Unsteady Aerodynamic Characteristics of Deformable Airfoil." In Fluid Dynamics of High Angle of Attack, 91–105. Berlin, Heidelberg: Springer Berlin Heidelberg, 1993. http://dx.doi.org/10.1007/978-3-642-52460-8_5.

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Driss, Zied, Olfa Mlayeh, Dorra Driss, Makram Maaloul, and Mohamed Salah Abid. "Incidence Angle Effect on the Aerodynamic Structure of an Incurved Savonius Wind Rotor." In Applied Condition Monitoring, 101–10. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-14532-7_11.

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Frikha, Sobhi, Zied Driss, Hedi Kchaou, and Mohamed Salah Abid. "Study of the Incidence Angle Effect on a Savonius Wind Rotor Aerodynamic Structure." In CFD Techniques and Energy Applications, 161–77. Cham: Springer International Publishing, 2018. http://dx.doi.org/10.1007/978-3-319-70950-5_8.

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Dalbanjan, Manjunath S., and Niranjan Sarangi. "Sensitivity Study of Stagger Angle on the Aerodynamic Performance of Transonic Axial Flow Compressors." In Proceedings of the National Aerospace Propulsion Conference, 3–14. Singapore: Springer Nature Singapore, 2022. http://dx.doi.org/10.1007/978-981-19-2378-4_1.

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Wang, Yangwei, Jian Wang, and Jun Zhang. "Effects of Wind Rotor Tilt Angle on Aerodynamic Power of Wind Turbine under Typical Periodic Disturbances." In Advances in Mechanism and Machine Science, 3459–68. Cham: Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-20131-9_341.

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Kargarnovin, Mohammad H., and Mohammad H. Sayrarfie. "Vibrational Response vs. Change of Trailing Sweep Angle, Tip Angle and Wing’s Thickness of a Small Wing Under Aerodynamic and Aeroelastic Forces in Super Sonic Range." In Computational Mechanics ’95, 1047–52. Berlin, Heidelberg: Springer Berlin Heidelberg, 1995. http://dx.doi.org/10.1007/978-3-642-79654-8_171.

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Rom, Josef. "Introduction." In High Angle of Attack Aerodynamics, 1–7. New York, NY: Springer New York, 1992. http://dx.doi.org/10.1007/978-1-4612-2824-0_1.

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Rom, Josef. "Description of Flows at High Angles of Attack." In High Angle of Attack Aerodynamics, 8–61. New York, NY: Springer New York, 1992. http://dx.doi.org/10.1007/978-1-4612-2824-0_2.

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Conference papers on the topic "Aerodynamic angle"

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Didyk, Z. V., and V. A. Apostolyuk. "Whole angle approximations of aerodynamic coefficients." In 2012 2nd International Conference "Methods and Systems of Navigation and Motion Control" (MSNMC). IEEE, 2012. http://dx.doi.org/10.1109/msnmc.2012.6475107.

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NELSON, ROBERT. "Visualization techniques for studying high angle of attack separatedvortical flows." In 15th Aerodynamic Testing Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1988. http://dx.doi.org/10.2514/6.1988-2025.

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Jouannet, Christopher, and Petter Krus. "Modelling of High Angle of Attack Aerodynamic." In 25th AIAA Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2007. http://dx.doi.org/10.2514/6.2007-4295.

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Abney, Eric, and Melissa McDaniel. "High Angle of Attack Aerodynamic Predictions Using Missile Datcom." In 23rd AIAA Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2005. http://dx.doi.org/10.2514/6.2005-5086.

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Abdel-Salam, T., S. Tiwari, and T. Mohieldin. "Effects of ramp swept angle in supersonic mixing." In 21st Aerodynamic Measurement Technology and Ground Testing Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2000. http://dx.doi.org/10.2514/6.2000-2377.

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McCrink, Matthew, and James W. Gregory. "Aerodynamic Parameter Estimation for Derived Angle-of-Attack Systems." In AIAA Atmospheric Flight Mechanics Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2017. http://dx.doi.org/10.2514/6.2017-4061.

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Kumar, Rajeev, and Sergey Shkarayev. "Effects of Yaw Angle on Aerodynamic Response in Locusts." In 50th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2012. http://dx.doi.org/10.2514/6.2012-417.

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Bao, Haitao, Cheng Wang, and Yonghai Wu. "Effects of Rear Window Angle on Car Aerodynamic Characteristics." In 2020 3rd World Conference on Mechanical Engineering and Intelligent Manufacturing (WCMEIM). IEEE, 2020. http://dx.doi.org/10.1109/wcmeim52463.2020.00141.

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Xuechang, Zhu, Yu Xiaojing, and Hong Yan. "Aerodynamic Characteristics of Fairing Separation at Initial Opening Angle." In 1st International Conference on Mechanical Engineering and Material Science). Paris, France: Atlantis Press, 2012. http://dx.doi.org/10.2991/mems.2012.160.

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Jouannet, Christopher, and Petter Krus. "Modelling of High Angle of Attack Aerodynamic, a State-Space Approach." In 24th AIAA Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2006. http://dx.doi.org/10.2514/6.2006-3845.

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Reports on the topic "Aerodynamic angle"

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Bihrle, W., Barnhart Jr., Dickes B., and E. Static and Rotational Aerodynamic Data from O deg to 90 deg Angle of Attack for a Series of Basic and Altered Forebody Shapes. Fort Belvoir, VA: Defense Technical Information Center, September 1989. http://dx.doi.org/10.21236/ada216582.

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McInville, Roy M., and Frank G. Moore. A New Method for Calculating Wing Along Aerodynamics to Angle of Attack 180 deg. Fort Belvoir, VA: Defense Technical Information Center, March 1994. http://dx.doi.org/10.21236/ada277965.

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Bowersox, Rodney D., and Huaiguo Fan. Investigation of Combined Low-Angled Jets and Variable Wall Geometry for Hypersonic Aerodynamic Control. Fort Belvoir, VA: Defense Technical Information Center, November 2000. http://dx.doi.org/10.21236/ada384726.

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Aerodynamic Development of the GAC ENO.146 Concept. SAE International, September 2021. http://dx.doi.org/10.4271/2021-01-5093.

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Abstract:
This paper describes the aerodynamic development process and features of the flow field of the GAC ENO.146, a concept vehicle shown in Guangzhou Auto Show 2019, which achieved a CD of 0.146. Key factors in the design process, including how design decisions are made and how the interactions occur between aerodynamicists and designers are explained in detail. The design language forms the next generation of BEVs. The aerodynamic development philosophy is guided by three principles: minimizing flow separation, maximizing rear pressure recovery, and controlling tire wake. This vehicle took full advantage of the unique 2-1-2-1 seating configuration that allowed a tapered tail design with a narrower rear track to further minimize the size of the rear recirculation zone, improving rear pressure recovery. In order to reduce induced drag, detailed studies on roofline and diffuser angles were conducted to develop the optimal combination, eliminating any loss of flow momentum. The diffuser design also served to eliminate flow separation caused by the rear wheels. In addition to that, active aerodynamic devices were employed to reduce interaction between freestream and wheelhouse air. A comparison was also made between ENO.146 and Aion S, a GAC production EV to illustrate future development potentials. Through the development of ENO.146, the aerodynamic development process of ENO.146 serves as a template for future projects, providing expertise and best practices of aerodynamic development for both engineers and designers.
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