2. W i l c o x D. C. Multiscale Model for Turbulent Flows // AIAA Journal. – 1988. –
Vol. 26. – No. 11. – P. 1311–1320.
3. W i l c o x D. C. Reassessment of the Scale Determining Equation for Advanced
Turbulence Models // AIAA Journal. – 1988. – Vol. 26. – No. 11. – P. 1299–1310.
4. M e n t e r F. R. Multiscale model for turbulent flows // In 24th Fluid Dynamics
Conference. American Institute of Aeronautics and Astronautics, 1993.
5. M e n t e r F. R. Two-equation eddy-viscosity turbulence models for engineering
applications // AIAA Journal. – 1994. – Vol. 32. – No. 8. – P. 269–289.
6. M e n t e r F. R. Zonal Two Equation
k
−
ω
Turbulence Models for Aerodynamic
Flows // AIAA Paper 93-2906. 1993.
7. S p e z i a l e C. G., S a r k a r S. and G a t s k i T. B. Modeling the pressure-strain
correlation of turbulence: an invariant dynamical systems approach // J. Fluid Mech.
– 1991. – Vol. 227. – P. 245–272.
8. L a u n d e r B. E., R e e c e G. J. and R o d i W. Progress in the development of a
Reynolds stress turbulence closure // J. Fluid Mech. – 1975. – Vol. 68. – P. 537–566.
9. C o r n e t t e E. S.
Forebody Temperatures and Calorimeter Heating Rates
Measured During Project Fire II Reentry at 11.35 Kilometers Per Second // NASA
TM X-1305. Nov. 1966.
10. S l o c u m b T. H. Project Fire Flight II Afterbody Temperatures and Pressures at
11.35 Kilometers Per Second // NASA TM X-1319. – 1966.
11. C a u c h o n D. L. Radiative Heating Results from the Fire II Flight Experiment at
a Reentry Velocity of 11.4 Kilometers Per Second // NASA TM X-1402. – 1966.
12. G n o f f o P. A. A Code Calibration Program in Support of the Aeroassist Flight
Experiment // AIAA Paper. – No. 89-1673. – June 1989.
13. G r e e n d y k e R. B. and H a r t u n g L. C. Convective and Radiative Heat
Transfer Analysis for the Fire II Forebody // Journal of Spacecraft and Rockets.
– 1994. – Vol. 31. – No. 6. – P. 986–992.
14. G o k c e n T. Calculation of Nonequilibrium Radiating Shock Layers // Journal of
Thermophysics and Heat Transfer. – 1995. – Vol. 9. – No. 1. – P. 34–40.
15. O l y n i c k D. R. H e n l i n e W. D. C h a m b e r s L. H. and C a n d l e r G. V.
Comparisons of Coupled Radiative Navier-Stokes Flow Solutions with the Project
Fire II Flight Data // AIAA Paper. – No. 94-1955. – June 1994.
16. B r o w n J. L. Turbulence model validation for Hypersonic flows // AIAA Paper. –
2002-3308. – 2002.
17. N a n c e R. P., H o l l i s B. R. H o r v a t h T. J. A l t e r S. J. & H a s s a n H. A.
Computational study of hypersonic transitional wake flow // Journal of thermophysics
and heat transfer. – 13(2). – 1999.
18. S i n h a K. RANS simulation of Fire II re-entry configuration’ // International
Symposium on Shock Waves. – 2005.
19. S i n h a K., B a r n h a r d t M., and C a n d l e r G. V. Detached Eddy Simulation
of Hypersonic Base Flows with Application to Fire II Experiments // AIAA Paper. –
2004-2633. – 2004.
20. S i n h a K. Grid Sensitivity of Detached Eddy Simulation of a Mach 16 Re-entry
Configuration // AIAA Paper. – 2007-1115. – 2007.
21. S i n h a K. Effect of Reynolds Number on Detached Eddy Simulation of Hypersonic
Base Flow // AIAA Paper. – 2007-1457. – 2007.
22. S i n h a K. and R e d d y S. K. Hypersonic Turbulent Reacting Flow Simulation of
Fire II Re-entry Vehicle // AIAA Paper. – 2007-0805. – 2007.
23. W r i g h t M. J., P r a b h u D. K. and M a r t i n e z E. R. Analysis of Apollo
Command Module Afterbody Heating Part I: AS202 // Journal of thermophysics and
heat transfer. – 20(1). – 2006.
24. E d q u i s t K. T. Afterbody Heating Predictions of a Mars Science Laboratory Entry
Vehicle // AIAA Paper. – 2005-4817. – 2005.
24 ISSN 0236-3941. Вестник МГТУ им. Н.Э. Баумана. Сер. “Машиностроение”. 2009. № 2