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Relevant bibliographies by topics / Wake Flight Testing

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Academic literature on the topic 'Wake Flight Testing'

Author: Grafiati

Published: 6 September 2023

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Journal articles on the topic "Wake Flight Testing"

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Zawodny, Nikolas, Nicole Pettingill, and Christopher Thurman. "Identification and Reduction of Interactional Noise of a Quadcopter in Hover and Forward Flight Conditions." INTER-NOISE and NOISE-CON Congress and Conference Proceedings 265, no. 5 (2023): 2947–58. http://dx.doi.org/10.3397/in_2022_0415.

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Advanced Air Mobility is a vision for a safe, accessible, and sustainable aviation system to transport people and packages between places not served by traditional aviation. With this emerging transportation industry, there is motivation to characterize the noise of vehicles to determine their potential impacts on the community. An experimental testing campaign was conducted on a small unmanned aerial vehicle in the NASA Langley Low Speed Aeroacoustic Wind Tunnel as a continuation of a previous testing campaign. The goals of the current test are to identify sources of interactional noise as we

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Zhelannikov, A. I. "Features of vortex trace propagation for aircraft with propellers." Civil Aviation High Technologies 26, no. 3 (2023): 103–13. http://dx.doi.org/10.26467/2079-0619-2023-26-3-103-113.

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The article presents the results of a study of the characteristics of the wake vortex of aircraft with turboprop engines. Using the example of the An-12 aircraft, it is shown that rotating propellers make a noticeable contribution to the propagation of the vortex trail behind the aircraft. This is proved by some studies, as well as numerous observations. It also describes a technique for studying the wake vortex of aircraft with propellers. The method is based on the method of discrete vortices. The relevance of such studies is due to the growing interest of carrier companies in aircraft with

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Singh, Sunayna, Martin Sippel, and Sven Stappert. "Full-scale simulations of ‘In-Air Capturing’ return mode for winged reusable launch vehicles." Journal of Physics: Conference Series 2526, no. 1 (2023): 012114. http://dx.doi.org/10.1088/1742-6596/2526/1/012114.

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Abstract The recent success of reusable launchers has become a driving force for sustainable launch technologies. An innovative approach proposed by DLR, involves winged rocket stages captured mid air and towed back to the launch site by an aircraft. This recovery concept known as ‘In-Air Capturing (IAC)’, shows potential for substantial cost reduction, when compared to existing return modes. In the light of the Horizon 2020 project FALCon, full-scale simulations and sub-scale flight testing were carried out for further development of the technology. The paper summarizes the full-scale studies

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Zhelannikov, A. I., and A. N. Zamyatin. "Investigation of the influence of engine displacement along the aircraft wing on the propagation of a condensation trail." Civil Aviation High Technologies 25, no. 5 (2022): 48–58. http://dx.doi.org/10.26467/2079-0619-2022-25-5-48-58.

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With the publication of this article, the authors continue their research into the interaction of vortex and condensation trails behind aircraft, which has begun in the previously published articles in the Civil Aviation High Technologies of the Moscow State Technical University of Civil Aviation. This paper presents the investigation results of the influence of engine displacement along the A320 aircraft wing on the development and propagation of a contrail. It should be clear that a contrail is a product of aviation fuel combustion in the engine and represents condensed moisture in the form

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Huber, F. W., P. D. Johnson, O. P. Sharma, J. B. Staubach, and S. W. Gaddis. "Performance Improvement Through Indexing of Turbine Airfoils: Part 1—Experimental Investigation." Journal of Turbomachinery 118, no. 4 (1996): 630–35. http://dx.doi.org/10.1115/1.2840918.

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This paper describes the results of a study to determine the performance improvements achievable by circumferentially indexing successive rows of turbine stator airfoils. An experimental/analytical investigation has been completed that indicates significant stage efficiency increases can be attained through application of this airfoil clocking concept. A series of tests was conducted at the National Aeronautics and Space Administration’s (NASA) Marshall Space Flight Center (MSFC) to experimentally investigate stator wake clocking effects on the performance of the Space Shuttle Main Engine Alte

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Raffel, Markus, James T. Heineck, Edward Schairer, Friedrich Leopold, and Kolja Kindler. "Background-Oriented Schlieren Imaging for Full-Scale and In-Flight Testing." Journal of the American Helicopter Society 59, no. 1 (2014): 1–9. http://dx.doi.org/10.4050/jahs.59.012002.

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Background-oriented schlieren (BOS) methods suited for large-scale and in-flight testing are presented with special emphasis on the detection and tracing of blade tip vortices in situ. Retroreflective recording and photogrammetric epipolar analysis for the computation of the vortices' spatial coordinates in the wind tunnel are described. Feasibility and fidelity of reference-free BOS in conjunction with natural formation backgrounds and related evaluation methods are discussed, additionally, illustrating their simplicity and robustness. Results of successful image acquisition from a chaser air

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Hall, David S., Rhodri Jervis, Louis F. J. Piper, Alexandra L. Kersting, and Clare P. Grey. "Battery Degradation and Lifetime – Studies within the Faraday Institution on NMC811/Graphite Full Cells." ECS Meeting Abstracts MA2022-01, no. 2 (2022): 341. http://dx.doi.org/10.1149/ma2022-012341mtgabs.

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Lithium-ion batteries (LIBs) find use in a wide range of applications, each of which has its own design specifications and practical requirements. With regards to the role of LIBs in mitigating carbon emissions, and therefore climate change, it is desirable to support the rapidly growing adoption of electric vehicles and renewable grid-storage systems via development of higher energy density, lower cost, and improved rate capability. However, the design of energy-dense, low-cobalt, and/or high-rate cell chemistries is impeded by inherent trade-offs with cycling and calendar lifetimes. A key go

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Saetti, Umberto, and Batän Buäday. "Tiltrotor Simulations with Coupled Flight Dynamics, State-Space Aeromechanics, and Aeroacoustics." Journal of the American Helicopter Society, 2023. http://dx.doi.org/10.4050/jahs.69.012003.

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This article describes the development, implementation, and validation of a generic tilt-rotor simulation model with coupled flight dynamics, state-variable aeromechanics, and aeroacoustics. A major novelty of this work lies in the integration of the flight dynamics with a state-space free-vortex wake code that adopts a near-wake vortex-lattice model. This way, the flight dynamics are augmented by the vortex wake dynamics so that the coupled flight and wake dynamics are self-contained and inherently linearizable. The model is implemented for a Bell XV-15 tiltrotor and validated against U.S. Ar

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Dissertations / Theses on the topic "Wake Flight Testing"

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Rogge, Matthew Douglas. "In-process sensing of weld penetration depth using non-contact laser ultrasound system." Diss., Atlanta, Ga. : Georgia Institute of Technology, 2009. http://hdl.handle.net/1853/31698.

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Thesis (Ph.D)--Mechanical Engineering, Georgia Institute of Technology, 2010.<br>Committee Chair: Ume, Charles; Committee Member: Chen, Ye-Hwa; Committee Member: Michaels, Jennifer; Committee Member: Sadegh, Nader; Committee Member: Vachtsevanos, George. Part of the SMARTech Electronic Thesis and Dissertation Collection.

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Poggi, Francesco. "Bending properties of commercial wood-based panels by NDT methods." Thesis, Linnéuniversitetet, Institutionen för skog och träteknik (SOT), 2017. http://urn.kb.se/resolve?urn=urn:nbn:se:lnu:diva-66162.

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This thesis work focuses mainly on the application of non-destructive testing (NDT) methods on wood-based panels (WBP) in order to estimate the bending properties. To prove the accuracy and applicability of these methods on WBP, their results are correlated with results from a standardized static bending test. The behavior in different climate conditions and the application on panels of larger sizes is also questioned to provide an indication about strong points and boundaries of NDT methods applied on WBP.The bending properties are of major importance, especially for materials suited to bear

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Carbol, Ladislav. "Měření akustických vlastností stavebních materiálů pomocí pseudonáhodné sekvence." Doctoral thesis, Vysoké učení technické v Brně. Fakulta stavební, 2017. http://www.nusl.cz/ntk/nusl-355599.

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The thesis deals with research of pulse compression of the acoustic signal in terms of applications in civil engineering. Based on the study and analysis of these methods, automated measuring equipment for non-destructive testing with pseudorandom sequence of maximum length and automated signal analysis, have been designed and implemented. In a single test cycle are obtained three parameters that characterize the linear and nonlinear behavior of the sample. A nonlinear parameter, Time of Flight of ultrasonic wave in the sample is further in the work compared with the conventional pulse measuri

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Books on the topic "Wake Flight Testing"

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Garodz, Leo J. Vortex characteristics of C5A/B, C141B, and C130E aircraft applicable to ATC terminal flight operations tower fly-by data. U.S. Dept. of Commerce, National Oceanic and Atmospheric Administration, Environmental Research Laboratories, Air Resources Laboratory, 1991.

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L, Clawson K., and Air Resources Laboratory (U.S.), eds. Vortex characteristics of C5A/B, C141B and C130E aircraft applicable to ATC terminal flight operations tower fly-by data. U.S. Dept. of Commerce, National Oceanic and Atmospheric Administration, Environmental Research Laboratories, Air Resources Laboratory, 1991.

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Vortex characteristics of C5A/B, C141B and C130E aircraft applicable to ATC terminal flight operations tower fly-by data. U.S. Dept. of Commerce, National Oceanic and Atmospheric Administration, Environmental Research Laboratories, Air Resources Laboratory, 1991.

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Book chapters on the topic "Wake Flight Testing"

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Bai, Xuejiao, and Haijiang Zhu. "Research on Finite Element Analysis Method of Laser Ultrasonic Velocity Measurement." In Proceedings of the 2022 International Conference on Smart Manufacturing and Material Processing (SMMP2022). IOS Press, 2022. http://dx.doi.org/10.3233/atde220833.

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As a new nondestructive testing method, the accurate measurement of laser ultrasonic velocity is of great significance for judging the internal crack defects of composites, calculating the elastic modulus, residual stress and grain size. Based on the finite element analysis method, the thermoelastic effect of laser induced ultrasonic vibration, the time-of-flight method and laser grating method for measuring ultrasonic velocity are studied in this paper. Firstly, the waveforms of laser point source, line source and laser grating are compared and analyzed. Secondly, the error analysis of the wave velocity under different radius laser point source, different half width laser line source and different grating spacing is carried out. The simulation results show that the laser grating method has higher stability and smaller measurement error. In addition, this method is less affected by other waves and the external environment. This paper provides a basis for improving the measurement accuracy of laser ultrasonic velocity and further applying laser ultrasonic velocity to nondestructive testing and measurement of related physical quantities.

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Conference papers on the topic "Wake Flight Testing"

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Tierney, Charles, Nicholas Jaffa, David Reich, and Sven Schmitz. "Scaled Model Testing of Coaxial Rotor Hub Flows." In Vertical Flight Society 77th Annual Forum & Technology Display. The Vertical Flight Society, 2021. http://dx.doi.org/10.4050/f-0077-2021-16877.

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Rotor hub parasite drag remains a primary obstacle to improving the forward-flight capabilities of helicopters. As part of a rotor hub flow physics project at the Vertical Lift Research Center of Excellence (VLRCOE) at Penn State, this investigation was designed to improve the understanding of the interactional aerodynamics and wake flow physics of counter-rotating coaxial rotor hubs and explore designs for reducing the rotor hub drag factor, Kfe. These experiments measured the time-averaged and time-varying drag on four rotor hub designs, each with unique blade stubs. The four shapes tested w

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Brown, Anthony, and Matthew Bastian. "Wake Vortex Flight Measurements and Tactical Aircraft WVE Design and Flight Testing Requirements." In 2008 U.S. Air Force T&E Days. American Institute of Aeronautics and Astronautics, 2008. http://dx.doi.org/10.2514/6.2008-1651.

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Steen, Meiko, Mirko Stanisak, Thomas Feuerle, and Peter Hecker. "In-Flight Testing of Airborne LIDAR for Wake Vortex Detection, Characterization and Tracking." In 6th AIAA Atmospheric and Space Environments Conference. American Institute of Aeronautics and Astronautics, 2014. http://dx.doi.org/10.2514/6.2014-2336.

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Saetti, Umberto, and Batin Bugday. "Generic Tilt-Rotor Simulation Model with Coupled Flight Dynamics, State-Variable Aeromechanics, and Aeroacoustics." In Vertical Flight Society 79th Annual Forum & Technology Display. The Vertical Flight Society, 2023. http://dx.doi.org/10.4050/f-0079-2023-18110.

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This paper describes the development, implementation, and validation of a generic tilt-rotor simulation model with coupled flight dynamics, state-variable aeromechanics, and aeroacoustic. A major novelty of this work lies in the integration of the flight dynamics with a state-space free-vortex wake code that adopts a near-wake vortex-lattice model. This way, the flight dynamics are augmented by the vortex wake dynamics so that the coupled flight and wake dynamics is self-contained and inherently linearizable. The model is implemented for a Bell XV-15 tiltrotor and validated against U.S. Army/N

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Tritschler, John, Joseph Milluzzo, and John Holder. "Performance Effects of Hover In-Ground-Effect over Sloped Terrain." In Vertical Flight Society 75th Annual Forum & Technology Display. The Vertical Flight Society, 2019. http://dx.doi.org/10.4050/f-0075-2019-14520.

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The present work reports the results of a research investigation into the performance effects of hovering over sloping terrain as characterized in both laboratory-scale testing of an isolated rotor as well as flight testing of a UH-72A helicopter. The design of the experiment included variation in the slope magnitude, rotor hub height, thrust/power setting, and aircraft orientation with respect to the slope (for the flight test data). In addition to performance measurements, flow field measurements of the laboratory flows were computed via particle image velocimetry, and rotor wake visualizati

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Staruk, William, Evan Bonny, Lauren Butt, et al. "Wind Tunnel Testing and Analysis of a Rigid, Variable Speed Rotor for eVTOL Applications." In Vertical Flight Society 76th Annual Forum & Technology Display. The Vertical Flight Society, 2020. http://dx.doi.org/10.4050/f-0076-2020-16411.

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Many electric vertical take-off and landing (eVTOL) aircraft intended for the urban air mobility (UAM) market are currently being designed with multirotor configurations using variable speed fixed-pitch, rigid rotors for lift. These types of rotors, which are similar in construction to general aviation airplane propellers, are simpler than helicopter rotors and have no moving parts in the rotating frame. This paper discusses wind-tunnel testing of a full-scale, UAM multirotor size, fixed-pitch, rigid rotor with a focus on vibratory blade loads and on the ability to predict these loads with com

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Welsh, Jake, and David Peters. "Floquet Instability in Periodically Reversing Flows." In Vertical Flight Society 79th Annual Forum & Technology Display. The Vertical Flight Society, 2023. http://dx.doi.org/10.4050/f-0079-2023-18107.

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Current 3-D finite-state wake models are incapable of simulating a maneuver in which the sign of the free-stream velocity changes direction and the rotor enters its own wake - as might occur in the case of a helicopter which ascends and then descends. It is the purpose of this work to create a 2-D finite-state wake model which is capable of handling changes in free-stream direction as a precursor to development of a 3-D model that can do the same. The 2-D finite-state model used for reentry modifications is an existing model created by Peters, Johnson, and Karunamoorthy. By the addition of a p

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Keller, Jeffrey, Mark J., Ondrej Juhasz, Robert McKillip, Daniel Wachspress, and Mark Tischler. "Linearized Inflow and Interference Models from High Fidelity Free Wake Analysis for Modern Rotorcraft Configurations." In Vertical Flight Society 76th Annual Forum & Technology Display. The Vertical Flight Society, 2020. http://dx.doi.org/10.4050/f-0076-2020-16290.

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Linearized inflow models have been used to represent dynamic wake effects for control law development and flight dynamics simulation of conventional main rotor / tail rotor helicopters. With the current focus in the industry toward high-speed concepts and electric vertical take-off and landing (eVTOL) aircraft, modern rotorcraft designs are trending away from the conventional main rotor / tail rotor configuration for which low-order dynamic inflow models have been applied and validated. Configurations currently in design and flight testing stages include coaxial, coaxialcompound, tiltrotor, mu

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Taymourtash, Neda, Daniele Zagaglia, Alex Zanotti, Giuseppe Gibertini, and Giuseppe Quaranta. "Towards a Wind Tunnel Testing Environment for Rotorcraft Operations Close to Obstacles." In Vertical Flight Society 75th Annual Forum & Technology Display. The Vertical Flight Society, 2019. http://dx.doi.org/10.4050/f-0075-2019-14640.

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The correct identification of the aerodynamic loads due to interaction between rotorcraft and obstacles requires to run computationally intensive numerical models characterized by a high level of uncertainty. Wind tunnel data can be used as a source of information to improve those models. The present paper investigates the aerodynamic interaction of a helicopter and ship airwake exploiting wind tunnel data. A series of wind tunnel experiment, using a scaled helicopter model and Simple Frigate Shape 1, has been performed to measure forces and moments acting on the rotor, while the helicopter is

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Keller, Jeffrey, Mark Tischler, Robert M., Daniel Wachspress, and Ondrej Juhasz. "Linearized Inflow and Interference Models from High Fidelity Free Wake Analysis for Modern Rotorcraft Configurations." In Vertical Flight Society 75th Annual Forum & Technology Display. The Vertical Flight Society, 2019. http://dx.doi.org/10.4050/f-0075-2019-14638.

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Linearized inflow models have been used to represent dynamic wake effects for control law development and flight dynamics simulation of conventional main rotor / tail rotor helicopters. With the current focus in the industry toward high-speed concepts and electric vertical take-off and landing (eVTOL) aircraft, modern rotorcraft designs are trending away from the conventional main rotor / tail rotor configuration for which low-order dynamic inflow models have been applied and validated. Configurations currently in design and flight testing stages include coaxial, coaxialcompound, tiltrotor, mu

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