Aerothermodynamic environment definition for an X-23/X-24A derived assured crew return vehicle

31st Thermophysics Conference

Volumn , Issue , 1996, Pages

  Campbell, Charles H ^a,b   Caram, Jose M ^a,b   Li, Chien P ^a,b   Madden, Christopher B ^a,c  

^a NASA JOHNSON SPACE CENTER   (United States)

^b Mail Stop EV33   (United States)

^c Thermal Branch   (United States)

Author keywords

[No Author keywords available]

Indexed keywords

ANGLE OF ATTACK; BOUNDARY LAYERS; LAMINAR BOUNDARY LAYER; REENTRY; THERMODYNAMICS; TURBULENT FLOW;

AEROTHERMODYNAMIC CHARACTERISTICS; CREW RETURN VEHICLES; NUMERICAL SOLUTION; REENTRY TRAJECTORIES; STAGNATION POINTS; THERMAL PROTECTION SYSTEM; TURBULENT BOUNDARY LAYERS; WALL TEMPERATURES;

THERMAL INSULATION;

EID: 84964446462     PISSN: None     EISSN: None     Source Type: Conference Proceeding    
DOI: None     Document Type: Conference Paper

References (17)

1. Engel, CD. and Praharaj, S.C., “MINIVER Upgrade for the Avid System,” REMTECH, Inc., Huntsville, AL, Aug. 1983.
2. DeVenezia, J., Wang, K.C., and Caram, J.M., “Space Shuttle Orbiter Wing Leading Edge Heating Predictions and Measurements”, Orbiter Experiments Aerothermodynamics Symposium, April, 1995.
3. Tarn, L.T., “LU-SGS Implicit Scheme for Entry Vehicle Flow Computation and Comparison with Aerodynamic Data,” AIAA-92-2671-CP, June 1992.
4. An, M.Y., Wang, K.C. and Tarn, L.T., “Computation of Inviscid Flowfield Around 3-D Aerospace Vehicles and Comparison with Experimental and Flight Data,” AIAA-93-0885, Jan., 1993.
5. Cooke, J.C., “An Axially Symmetric Analogue for General Three-Dimensional Boundary Layers,” British A.R.C., R and M No. 3200, 1959.
6. DeJarnette, F.R., and Davis, R.M., “A Simplified Method for Calculating Laminar Heat Transfer Over Bodies at an Angle of Attack,” NASA TN D-4720, 1968.
7. Wang, K.C., “An Axisymmetric Analog Two-Layer Convective Heating Procedure with Application to the Evaluation of Space Shuttle Orbiter Wing Leading Edge and Windward Surface Heating,” NASA CR-188343, Oct., 1993.
8. Li, CP., “Numerical Simulation of Entry Flow Over Blunt Swept-Wing Planes,” Advances in Hypersonics, ed. Bertin, J.J., et al, Vol. 3, pp. 220-298, Birkhaeuser, Boston, 1992.
9. Desideri, J.A., et al., “Hypersonic Flows for Reentry Problems,” Vol. 2; Test Cases -Experiments and Computations, Springer-Verlag, Berlin Heidelberg, 1991.
10. Weilmuenster, K.J. and Greene, F.A., “HL-20 Computational Fluid Dynamics Analysis,” J. Spacecraft and Rockets, Vol. 30, pp 558-566,1993.
11. Wurster, K.E., Zoby, E.V., and Thompson, R.A., “Influence of Flowfield and Vehicle Parameters on Engineering Aerothermal Methods,” AIAA-89-1769, June, 1989.
12. Weilmuenster, K.J., and Hamilton, H.H, II, “Calculations of Inviscid Flow Over Shuttle-Like Vehicles at High Angles of Attack and Comparisons with Experimental Data,”, NASA TP-2103, May, 1983.
13. Gnoffo, P.A., Hamilton, H.H, III, Zoby, E.V., Private communications, Oct. 1994, Dec. 1994.
14. Pro Engineer, a product of Parametric Technology Corporation.
15. ICEM CFD/CAE MULCAD, version 3.1.3.0 Reference Manual, July, 1994.
16. Chawner, J.R., and Steinbrenner, J.P., “GRIDGEN Version 10 Training Course Notes,” 1994.
17. Chan, W.M., Chiu, LT., Buning, P.G., “User's Manula for the HYPGEN Hyperbolic Grid Generator”, Sept. 1993.