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Готові списки джерел за темами / Aerodynamics (except hypersonic aerodynamics)

Добірка наукової літератури з теми "Aerodynamics (except hypersonic aerodynamics)"

Автор: Grafiati

Опубліковано: 10 грудня 2022

Оновлено: 28 січня 2023

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Статті в журналах з теми "Aerodynamics (except hypersonic aerodynamics)"

1

Yang, R. J. "Hypersonic fin aerodynamics." Journal of Spacecraft and Rockets 31, no. 2 (March 1994): 339–41. http://dx.doi.org/10.2514/3.26443.

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2

Cummings, Russell M., and Hsun-Tiao Yang. "Lester Lees and Hypersonic Aerodynamics." Journal of Spacecraft and Rockets 40, no. 4 (July 2003): 467–74. http://dx.doi.org/10.2514/2.3988.

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3

Agnone, Anthony M., and B. Prakasam. "Hypersonic aerodynamics of nonaxisymmetric boattailed bodies." Journal of Spacecraft and Rockets 24, no. 2 (March 1987): 181–82. http://dx.doi.org/10.2514/3.25894.

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4

Harloff, Gary J. "High angle-of-attack hypersonic aerodynamics." Journal of Spacecraft and Rockets 25, no. 5 (September 1988): 343–44. http://dx.doi.org/10.2514/3.26010.

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5

YE, YouDa. "Advances and prospects in hypersonic aerodynamics." Chinese Science Bulletin 60, no. 12 (April 1, 2015): 1095–103. http://dx.doi.org/10.1360/n972014-01180.

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6

Gerasimov, S. I., V. I. Erofeev, A. G. Sirotkina, A. V. Zubankov, and R. V. Gerasimova. "Contactless Measuring Section in Hypersonic Aerodynamics." Journal of Applied Mechanics and Technical Physics 60, no. 4 (July 2019): 639–43. http://dx.doi.org/10.1134/s0021894419040060.

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7

Candler, Graham V. "Book Review: Computational Methods in Hypersonic Aerodynamics." AIAA Journal 31, no. 2 (February 1993): 410. http://dx.doi.org/10.2514/3.59985.

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8

Cunningham, Mark J. "Hypersonic aerodynamics for an entry research vehicle." Journal of Spacecraft and Rockets 24, no. 2 (March 1987): 97–98. http://dx.doi.org/10.2514/3.25879.

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9

Thuruthimattam, B. J., P. P. Friedmann, K. G. Powell, and R. E. Bartels. "Computational aeroelastic studies of a generic hypersonic vehicle." Aeronautical Journal 113, no. 1150 (December 2009): 763–74. http://dx.doi.org/10.1017/s0001924000003420.

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Анотація:

Abstract The hypersonic aeroelastic problem of a generic hypersonic vehicle having a lifting-body type fuselage and canted fins is studied using third order piston theory and Euler aerodynamics. Computational aeroelastic response results are used to obtain frequency and damping characteristics, and compared with those from piston theory solutions for a variety of flight conditions. Aeroelastic behavior is studied for the range of 2·5 < M < 28, at altitudes ranging from 10,000ft to 80,000ft. Because of the significant computational resources required, a study on optimal mesh selection was first carried out for use with Euler aerodynamics. The three dimensional flow effects captured using Euler aerodynamics was found to lead to significantly higher flutter boundaries when compared to those based on nonlinear piston theory. The results presented here illustrate some of the more important three dimensional effects that can be encountered in hypersonic aeroelasticity of complex configurations.

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10

McNamara, Jack J., Andrew R. Crowell, Peretz P. Friedmann, Bryan Glaz, and Abhijit Gogulapati. "Approximate Modeling of Unsteady Aerodynamics for Hypersonic Aeroelasticity." Journal of Aircraft 47, no. 6 (November 2010): 1932–45. http://dx.doi.org/10.2514/1.c000190.

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Дисертації з теми "Aerodynamics (except hypersonic aerodynamics)"

1

Khorrami, Ahmad Farid. "Hypersonic aerodynamics on flat plates and thin aerofoils." Thesis, University of Oxford, 1991. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.292584.

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2

Hunt, Dillon C. "Measurement of ablation in transient hypersonic flows /." St. Lucia, Qld, 2001. http://www.library.uq.edu.au/pdfserve.php?image=thesisabs/absthe16475.pdf.

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3

Singh, Amarjit. "Experimental study of slender vehicles at hypersonic speeds." Thesis, Cranfield University, 1996. http://hdl.handle.net/1826/4257.

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Анотація:

An experimental investigation of the hypersonic flow over (i) a wing-body configuration, (ii) a hemi-spherically blunted cone-cylinder body and (iii) a one-half- power-law body has been conducted for M,, = 8.2 and Re,, = 9.35x104 per cm. The tests were performed at model incidences, a=0,5 and 10° for flap deflection angles, (3 = 0,5,15, and 25° for the wing-body. The incidence ranged from -3 to 10° for the cone- cylinder and -5 to 15° for the power-law body. (i) The schlieren pictures showing top and side views of the model indicate that the body nose shock does not intersect the wing throughout the range of a under investigation. Detailed pressure measurements on the lower surface of the wing and flap along with the liquid crystal pictures suggest that the body nose shock does not strike the flap surfaces either. The wing leading edge shock is found to be attached at a=0 and 5° but detached at a= 10°. The liquid crystal pictures and surface pressure measurements indicated attached flow on the lower surface of the wing and flap for 13 =0 and 5° at all values of a under test. However at a= 0°, as the flap angle is increased to 15° the flow separates ahead of the hinge line. As incidence is increased the boundary layer becomes transitional giving rise to complex separation patterns around the flap hinge line. The spherically blunted body nose causes strong entropy layer effects over the wing and the trailing edge flap. A Navier-Stokes solution indicated a thick entropy layer of approximately constant thickness all around the cylindrical section of the body at zero incidence. However, at an incidence of 10° the layer tapers and becomes thinner under the body. The surface pressure over the wing and the plateau pressure for separated flow was found to increase from the root to the tip. This is partly because of the decrease in local Reynolds number across the span, however in the present case, entropy layer effects also affected separation. The entropy layer effects were found to reduce the peak pressures obtainable on the flap. The peak pressures, over the portion of the flap unaffected by entropy layer effects, could be estimated assuming quasi two dimensional flow. (ii) Force measurements were made for the blunted cone-cylinder alone as well as with the delta wing, with trailing-edge flap, attached to it. The lift, drag, and pitching moment characteristics for the cone-cylinder agree reasonably well with the modified Newtonian theory and the N-S results. The addition of a wing to the cone-cylinder body increases the lift as weil as the drag coefficient but there is an overall increase in the lift/drag ratio. The deflection of a flap from 0° to 25° increases the lift and drag coefficients at all the incidences tested. However, the lift/drag ratio is reduced showing the affects of separation over the wing. The experimental results on the wing-body are compared with the theoretical estimates based upon two-dimensional shock-expansion theory. (iii) The lift, and drag characteristics of a one-half-power-law body are compared with other existing results. The addition of strakes to the power-law body are found to improve its aerodynamic efficiency without any significant change in its pitching moment characteristics.

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4

Babinsky, Holger. "A study of roughness in turbulent hypersonic boundary-layers." Thesis, Cranfield University, 1993. http://dspace.lib.cranfield.ac.uk/handle/1826/7586.

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The influence of large scale regular roughness on a Mach 5 turbulent boundary layer and a compression corner was investigated on axisymmetric wind tunnel models. Three types of roughness were examined; a series of square cavities at two different sizes and a 45 degree sawtooth. Typical sizes ranged from 50% to 100% of an undisturbed boundary layer thickness. The roughness was limited to a short region followed by a smooth surface. Compression corners were formed by 15° and 20° flares located downstream of the roughness. The flow in the wind tunnel was investigated in detail to obtain knowledge on operating conditions and flow quality. Liquid crystal thermography was developed for routine use in hypersonic blow-down wind tunnels with superior spatial resolution and experimental uncertainties in the range of traditional techniques. The effect on flow parameters downstream of the last roughness element were 7, found to differ significantly for the different quantities. Velocity profiles were found i, to be less full and skin friction was found to be reduced for all streamwise "~ distances. Surface heat transfer was increased in a short region limited to 1.5 boundary layer thicknesses behind the roughness whereas surface pressure was not affected. Sawtooth shaped roughness was found to cause a stronger j disturbance than square cavities of twice the size. Little influence of the roughness was noted on the flow over the compression corner. The flow over the 20° compression corner showed an increase in upstream influence for the sawtooth shaped roughness as well as the larger cavities. Surface pressure measurements did not indicate a separation in any case. Heat transfer measurements revealed a peak located approximately 0.25 boundary layer thicknesses behind the corner. No such feature was found in the surface pressure distributions. It is suggested that a small scale separation is located very close to the corner causing the peak in heat transfer at reattachment without any effect on surface pressures. The existence of such a separation has been confirmed by surface flow visualisations for both flares.

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5

Asproulis, Panagiotis. "High resolution numerical predictions of hypersonic flows on unstructured meshes." Thesis, Imperial College London, 1994. http://hdl.handle.net/10044/1/8357.

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6

Surah, Davinder. "Investigation of attachment line boundary layer characteristics in hypersonic flows." Thesis, Cranfield University, 2000. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.323921.

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7

Atcliffe, Phillip Arthur. "Effects of boundary layer separation and transition at hypersonic speeds." Thesis, Cranfield University, 1995. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.336458.

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8

Robinson, Matthew J. "Simultaneous lift, moment and thrust measurement on a scramjet in hypervelocity flow /." [St. Lucia, Qld.], 2003. http://www.library.uq.edu.au/pdfserve.php?image=thesisabs/absthe17611.pdf.

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9

Axdahl, Erik Lee. "A study of premixed, shock-induced combustion with application to hypervelocity flight." Diss., Georgia Institute of Technology, 2013. http://hdl.handle.net/1853/50290.

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One of the current goals of research in hypersonic, airbreathing propulsion is access to higher Mach numbers. A strong driver of this goal is the desire to integrate a scramjet engine into a transatmospheric vehicle airframe in order to improve performance to low Earth orbit (LEO) or the performance of a semi-global transport. An engine concept designed to access hypervelocity speeds in excess of Mach 10 is the shock-induced combustion ramjet (i.e. shcramjet). This dissertation presents numerical studies simulating the physics of a shcramjet vehicle traveling at hypervelocity speeds with the goal of understanding the physics of fuel injection, wall autoignition mitigation, and combustion instability in this flow regime. This research presents several unique contributions to the literature. First, different classes of injection are compared at the same flow conditions to evaluate their suitability for forebody injection. A novel comparison methodology is presented that allows for a technically defensible means of identifying outperforming concepts. Second, potential wall cooling schemes are identified and simulated in a parametric manner in order to identify promising autoignition mitigation methods. Finally, the presence of instabilities in the shock-induced combustion zone of the flowpath are assessed and the analysis of fundamental physics of blunt-body premixed, shock-induced combustion is accelerated through the reformulation of the Navier Stokes equations into a rapid analysis framework. The usefulness of such a framework for conducting parametric studies is demonstrated.

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10

Rohrschneider, Reuben R. "Variable-Fidelity Hypersonic Aeroelastic Analysis of Thin-Film Ballutes for Aerocapture." Diss., Georgia Institute of Technology, 2007. http://hdl.handle.net/1853/14590.

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Ballute hypersonic aerodynamic decelerators have been considered for aerocapture since the early 1980's. Recent technology advances in fabric and polymer materials as well as analysis capabilities lend credibility to the potential of ballute aerocapture. The concept of the thin-film ballute for aerocapture shows the potential for large mass savings over propulsive orbit insertion or rigid aeroshell aerocapture. Several technology hurdles have been identified, including the effects of coupled fluid structure interaction on ballute performance and survivability. To date, no aeroelastic solutions of thin-film ballutes in an environment relevant to aerocapture have been published. In this investigation, an aeroelastic solution methodology is presented along with the analysis codes selected for each discipline. Variable-fidelity aerodynamic tools are used due to the long run times for computational fluid dynamics or direct simulation Monte Carlo analyses. The improved serial staggered method is used to couple the disciplinary analyses in a time-accurate manner, and direct node-matching is used for data transfer. In addition, an engineering approximation has been developed as an addition to modified Newtonian analysis to include the first-order effects of damping due to the fluid, providing a rapid dynamic aeroelastic analysis suitable for conceptual design. Static aeroelastic solutions of a clamped ballute on a Titan aerocapture trajectory are presented using non-linear analysis in a representative environment on a flexible structure. Grid convergence is demonstrated for both structural and aerodynamic models used in this analysis. Static deformed shape, drag and stress level are predicted at multiple points along the representative Titan aerocapture trajectory. Results are presented for verification and validation cases of the structural dynamics and simplified aerodynamics tools. Solutions match experiment and other validated codes well. Contributions of this research include the development of a tool for aeroelastic analysis of thin-film ballutes which is used to compute the first high-fidelity aeroelastic solutions of thin-film ballutes using inviscid perfect-gas aerodynamics. Additionally, an aerodynamics tool that implements an engineering estimate of hypersonic aerodynamics with a moving boundary condition is developed and used to determine the flutter point of a thin-film ballute on a Titan aerocapture trajectory.

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Книги з теми "Aerodynamics (except hypersonic aerodynamics)"

1

Park, Chul. Nonequilibrium hypersonic aerothermodynamics. New York: Wiley, 1990.

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2

HEPPENHEIMER, T. A. Hypersonic technologies. Arlington, Va: Pasha Publications, 1993.

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3

Hypersonic flow. New York: Wiley, 1994.

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4

Heinrich, Ralf. Berechnung stationärer Hyperschallströmungen unter Verwendung eines zonalen Konzeptes. Aachen: Shaker, 1996.

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5

Anderson, John David. Hypersonic and high temperature gasdynamics. New York: McGraw-Hill, 1989.

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6

Anderson, John David. Hypersonic and high temperature gas dynamics. New York: McGraw-Hill, 1989.

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7

Anderson, John David. Hypersonic and high-temperature gas dynamics. 2nd ed. Reston, VA: AIAA, 2007.

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8

Tannehill, John C. Development of a 3-D upwind PNS code for chemically reacting hypersonic flowfields. [Washington, DC: National Aeronautics and Space Administration, 1992.

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9

Tannehill, John C. Development of a 3-D upwind PNS code for chemically reacting hypersonic flowfields. [Washington, DC: National Aeronautics and Space Administration, 1992.

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10

Radespiel, R. Progress with multigrid schemes for hypersonic flow problems. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1991.

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Частини книг з теми "Aerodynamics (except hypersonic aerodynamics)"

1

Kaushik, Mrinal. "Hypersonic Flows." In Theoretical and Experimental Aerodynamics, 237–50. Singapore: Springer Singapore, 2018. http://dx.doi.org/10.1007/978-981-13-1678-4_10.

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2

Viviand, H. "Similitude in Hypersonic Aerodynamics." In Hypersonic Flows for Reentry Problems, 72–97. Berlin, Heidelberg: Springer Berlin Heidelberg, 1991. http://dx.doi.org/10.1007/978-3-642-84580-2_7.

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3

Gülçat, Ülgen. "Hypersonic Flow." In Fundamentals of Modern Unsteady Aerodynamics, 205–58. Singapore: Springer Singapore, 2015. http://dx.doi.org/10.1007/978-981-10-0018-8_7.

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4

GÜlçat, Ülgen. "Hypersonic Flow." In Fundamentals of Modern Unsteady Aerodynamics, 209–64. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-60777-7_7.

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5

Gülçat, Ülgen. "Hypersonic Flow." In Fundamentals of Modern Unsteady Aerodynamics, 193–244. Berlin, Heidelberg: Springer Berlin Heidelberg, 2010. http://dx.doi.org/10.1007/978-3-642-14761-6_7.

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6

Chattot, J. J., and M. M. Hafez. "Introduction to Hypersonic Flows." In Theoretical and Applied Aerodynamics, 399–456. Dordrecht: Springer Netherlands, 2015. http://dx.doi.org/10.1007/978-94-017-9825-9_12.

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7

Viviani, Antonio, and Giuseppe Pezzella. "Basics of Hypersonic Aerodynamics and Aerothermodynamics." In Aerodynamic and Aerothermodynamic Analysis of Space Mission Vehicles, 1–125. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-13927-2_1.

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8

Hirschel, Ernst Heinrich, and Hans Ulrich Meier. "Aerodynamics — from Near-Sonic to Hypersonic Flight." In Aeronautical Research in Germany, 387–407. Berlin, Heidelberg: Springer Berlin Heidelberg, 2004. http://dx.doi.org/10.1007/978-3-642-18484-0_16.

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9

Carlomagno, G. M., L. Luca, and G. Cardone. "Hypersonic Aerodynamics Research with an Infrared Imaging System." In New Trends in Instrumentation for Hypersonic Research, 493–502. Dordrecht: Springer Netherlands, 1993. http://dx.doi.org/10.1007/978-94-011-1828-6_44.

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10

Dimitrienko, Yury, Mikhail Koryakov, and Andrey Zakharov. "Application of Finite Difference TVD Methods in Hypersonic Aerodynamics." In Finite Difference Methods,Theory and Applications, 161–68. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-20239-6_15.

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Тези доповідей конференцій з теми "Aerodynamics (except hypersonic aerodynamics)"

1

FINLEY, DENNIS. "Hypersonic aerodynamics considerations and challenges." In 2nd International Aerospace Planes Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1990. http://dx.doi.org/10.2514/6.1990-5222.

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2

Riabov, Vladimir V. "Rarefaction Effects in Hypersonic Aerodynamics." In 27TH INTERNATIONAL SYMPOSIUM ON RAREFIED GAS DYNAMICS. AIP, 2011. http://dx.doi.org/10.1063/1.3562828.

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3

COCKRELL, JR., CHARLES, and LAWRENCE HUEBNER. "Generic hypersonic inlet module analysis." In 9th Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1991. http://dx.doi.org/10.2514/6.1991-3209.

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4

SOBIECZKY, H. "Generic supersonic and hypersonic configurations." In 9th Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1991. http://dx.doi.org/10.2514/6.1991-3301.

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5

Landon, Mark, Darryl Hall, Jerry Udy, and Ernest Perry. "Automatic supersonic/hypersonic aerodynamic shape optimization." In 12th Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1994. http://dx.doi.org/10.2514/6.1994-1898.

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6

Heller, M., F. Holzapfel, and G. Sachs. "Robust lateral control of hypersonic vehicles." In 18th Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2000. http://dx.doi.org/10.2514/6.2000-4248.

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7

Lindblad, I., T. Groenland, J. L. Cambier, S. Wallin, T. Berens, P. Sacher, M. Netterfield, et al. "A study of hypersonic afterbody flowfields." In 15th Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1997. http://dx.doi.org/10.2514/6.1997-2289.

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8

HARLOFF, GARY. "High angle of attack hypersonic aerodynamics." In 5th Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1987. http://dx.doi.org/10.2514/6.1987-2548.

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9

HOFFMANN, KLAUS, DENNIS WILSON, and CHARLES HAMBURGER. "Aerothermodynamic analysis of projectiles at hypersonic speeds." In 7th Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1989. http://dx.doi.org/10.2514/6.1989-2185.

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10

Li, Suxun, Yongkang Chen, Yulin Li, Suxun Li, Yongkang Chen, and Yulin Li. "Hypersonic flow over double-ellipsoid - Experimental investigation." In 15th Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1997. http://dx.doi.org/10.2514/6.1997-2287.

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Звіти організацій з теми "Aerodynamics (except hypersonic aerodynamics)"

1

Anderson, Jr, and John D. Hypersonic Aerodynamics Fellowships. Fort Belvoir, VA: Defense Technical Information Center, February 1991. http://dx.doi.org/10.21236/ada233584.

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2

Anderson, John D., and Jr. Fellowships in Hypersonic Aerodynamics. Fort Belvoir, VA: Defense Technical Information Center, February 1988. http://dx.doi.org/10.21236/ada194265.

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3

Munipalli, Ramakanth, Kamesh Subbarao, Shashi Aithal, Donald R. Wilson, and Jennifer D. Goss. Automated Design Optimization for Hypersonic Plasma-Aerodynamics. Fort Belvoir, VA: Defense Technical Information Center, June 2005. http://dx.doi.org/10.21236/ada435356.

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4

AIR FORCE TEST PILOT SCHOOL EDWARDS AFB CA. Volume 1. Aircraft Performance. Chapter 10. Hypersonic Aerodynamics. Fort Belvoir, VA: Defense Technical Information Center, April 1987. http://dx.doi.org/10.21236/ada320212.

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