Inviscid design of hypersonic wind tunnel nozzles for a real gas

38th Aerospace Sciences Meeting and Exhibit

Volumn , Issue , 2000, Pages

  Korte, J J ^a  

^a NASA LANGLEY RESEARCH CENTER   (United States)

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EID: 84894330124     PISSN: None     EISSN: None     Source Type: Conference Proceeding    
DOI: None     Document Type: Conference Paper

References (21)

1. Anderson, J. D., Modern Compressible Flow, 1st ed., McGraw-Hill, New York, 1982, pp. 303-305.
2. Sivells, J. C., "Aerodynamic Design of Axisymmetric Hypersonic Wind Tunnel Nozzles, " Journal of Spacecraft and Rockets, Vol. 7, Nov. 1970, pp. 1292-1299.
3. Armstrong, A. H., and Smith, M. G., "Two-Dimensional Supersonic Nozzle Design, Part I: Theory, " Armament Research Establishment, Report No. 5/51, Oct. 1951.
4. Ruptash, J., "Supersonic Wind Tunnels-Theory, Design and Performance, " University of Toronto, Institute of Aerophysics, June 1952.
5. Beckwith. I. E. and Moore. J. A. "An Accurate and Rapid Method for the Design of Supersonic Nozzles, " NACA TN 3322, Feb. 1955.
6. Johnson, C. B., "Real-Gas Effects on Hypersonic Nozzle Contours With a Method of Calculation, " NASA TN D-1622, 1963.
7. Lukasiewicz, J., Experimental Methods of Hypersonics, Gasdynamics, Vol. 3, Part I, Dekker, New York, 1973, pp. 80-86.
8. Zucrow M. J., and Hoffman, J. D., Gas Dynamics, Volume 2: Multidimensional Flow, John Wiley & Sons, Inc., New York, 1977.
9. Shapiro, A. H., The Dynamics and Thermodynamics of Compressible Fluid Flow, Vol. 1, The Ronald Press Company, New York, 1953.
10. Korte, J. J., and Hodge, J. S., "Flow Quality of Hypersonic Wind-Tunnel Nozzles Designed Using Computational Fluid Dynamics, " Journal of Spacecraft and Rockets, Vol. 32, No. 4, 1995, pp. 569-580.
11. Korte, J. J., Kumar, A., Singh, D. J., and White, J. A., "CAN-DO, D-Based Aerodynamic gozzle I&sign & Qptimization Program for SupersomclHypersonic Wind Tunnels, " AIAA Paper 92-4009, July 1992.
12. Johnson, C. B., and Boney, L. R., 'A Method for Calculating a Real-Gas Two-Dimensional Nozzle Contour Including the Effects of Gamma, " NASA TM X-3243, 1975.
13. Jacobs, P. A., and Stalker, R. J., "Design of Axisymmetric Nozzles for Reflected Shock Tunnels, " QueenslandA, ustralia, Report l/89, 1988.
14. Hannemann, K., "Design of an Axisymmetric, Contoured Nozzle for the HEG, " Institut fiir Theoretische Stromungsmechanik, DLR Report DLR-FB 90-04, Gottingen, Germany, 1990.
15. Chadwick, K. M., Holden, M. S., Korte, J. J., and Anderson, E. C., "Design and Fabrication of a Mach 8 Contoured Nozzle for the LENS Facility, " AIAA Paper 96-0585, Jan. 1996.
16. Sivells, J. C., "A Computer Program for the Aerodynamic Design of Axisymmetric and Planar Nozzles for Supersonic and Hypersonic Wind Tunnels, " AEDC-TR-78-63, Dec. 1978.
17. Anderson, E. C., and Lewis, C. H., "Laminar or Turbulent Boundary-Layer Flows of Perfect Gases or Reacting Gas Mixtures in Chemical Equilibrium, " NASA CR-1893, Oct. 1971.
18. Korte, J. J., Hedlund, E., and Anandakrishnan, S., "A Comparison of Experimental Data With CFD For The NSWC Hypervelocity Wind Tunnel #9 Mach 14 Nozzle, " AIAA Paper 92-4010, July 1992.
19. Beckwith, I. E., personal communication, 1990.
20. Eggers, A. J., Jr., "One-Dimensional Flows of an Imperfect Diatomic Gas, " NACA Rep. 959, 1950.
21. Gaffney, R. L. Jr., "CFD Calculations of the AHSTF Mach 6 Nozzle, " to be published as Analytical Services and Materials Report, Hampton, VA.