Design and fabrication of a Mach 8 contoured nozzle for the LENS facility

34th Aerospace Sciences Meeting and Exhibit

Volumn , Issue , 1996, Pages

  Chadwick, Kenneth M ^a,b   Holden, Michael S ^a,b   Korte, John J ^c   Anderson, E Clay ^c  

^a Calspan Corporation   (United States)

^b UNIVERSITY AT BUFFALO   (United States)

^c NASA LANGLEY RESEARCH CENTER   (United States)

Author keywords

[No Author keywords available]

Indexed keywords

AERODYNAMICS; AEROSPACE ENGINEERING; BOUNDARY LAYERS; COMBUSTORS; COMPUTATIONAL FLUID DYNAMICS; DESIGN; FLUID DYNAMICS; GASES; MACH NUMBER; NAVIER STOKES EQUATIONS; NOZZLES; QUALITY CONTROL; SHOCK TESTING; TRANSPORT PROPERTIES;

BOUNDARY LAYER CORRECTIONS; CLASSICAL METHODS; DESIGN APPROACHES; HIGH QUALITY TEST; PARABOLIZED NAVIER-STOKES (PNS); RESERVOIR PRESSURES; SCRAMJET COMBUSTORS; THERMOCHEMICAL EQUILIBRIUM;

NOZZLE DESIGN;

EID: 84962194616     PISSN: None     EISSN: None     Source Type: Conference Proceeding    
DOI: None     Document Type: Conference Paper

References (12)

1. Holden, M. S., Kolly, J., Chadwick, K. M., "Calibration, Validation, and Evaluation Studies in the LENS Facility, " AIAA 95-0291, January 1995.
2. Large Energy National Shock Tunnel (LENS) Description and Capabilities, Calspan-UB Research Center, Buffalo, NY, February 1991.
3. Korte, J. J.; Kumar, A.; Singh, D. J.; and White. J. A., "CAN-DO - CFD-Based Aerodynamic Nozzle Design & Optimization Program for Supersonic/Hypersonic Wind Tunnels, " AIAA Paper 92-4009, July 1992.
4. Korte, J.J. and Hodge. J.S. "Flow Quality of Hypersonic Wind-Tunnel Nozzles Designed Using Computational Fluid Dynamics, " Vol. 32, No. 4, July-August 1995, pp. 569-580.
5. 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.
6. Jacobs, P. A. and Stalker, R. J., "Design of Axisymmetric Nozzles For Reflected Shock Tunnels, " Report 1/89 Department of Mechanical Engineering University of Queensland, Australia.1988.
7. Hannemann, Klaus, "Design of an Axisymmetric, Contoured Nozzle for the HEG, " DLR Report DLR- FB 90-04, Institut fur Theoretische Stromungsmechanik, Gottingen.
8. 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, December 1978.
9. Sivells, J. C., "Aerodynamic Design of Axisymmetric Hypersonic Wind Tunnel Nozzles, " Journal of Spacecraft and Rockets, Vol. 7, November 1970, pp. 1292-1299.
10. 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.
11. Korte, J. J.; Hedlund E.; and Anandakrishnan S., "A Comparison of Experimental Data With CFD For TheNSWC Hypervelocity Wind Tunnel #9 Mach 14 Nozzle, " AIAA Paper 92-4010, July 1992.
12. McGrory, W. D., Slack, D. C., Applebaum, M. P., and Walters, R. W., "GASP Version 2.2 User's Guide, " Aerosoft, Inc., Backsburg, VA, 1992.