Plume interference effects on missile bodies

Journal of Spacecraft and Rockets

Volumn 40, Issue 1, 2003, Pages 136-138

  Raghunathan, S ^a   Kim, H D ^a   Benard, E ^a   Mallon, P ^b   Harrison, R ^b  

^a QUEEN'S UNIVERSITY BELFAST   (United Kingdom)

^b Thales Optics Ltd   (United Kingdom)

Author keywords

[No Author keywords available]

Indexed keywords

BOUNDARY CONDITIONS; COMPUTATIONAL FLUID DYNAMICS; SHOCK WAVES; SUPERSONIC FLOW; WIND TUNNELS;

MISSILE BODIES;

MISSILES;

EID: 0037282261     PISSN: 00224650     EISSN: 15336794     Source Type: Journal    
DOI: 10.2514/2.3928     Document Type: Article

References (6)

1. Dryer, N., and North, W. J., "Preliminary Analysis of the Effect of Flow Separation Due to Rocket Jet Pluming on Aircraft Dynamic Stability During Atmospheric Exit," NASA Memo 4-22-59E, 1959.
2. Alpinieri, T. C., Jr., and Adams, R. H., "Flow Separation due to Jet Pluming," AIAA Journal, Vol. 4, No. 10, 1966, pp. 1865, 1866.
3. McGhee, R. J., "Jet-Plume-induced Flow Separation on a Lifting Entry Body at Mach Numbers from 4.00 to 6.00" NASA TM X-1997, April 1970.
4. Klineberg, J., Kubota, T., and Lees, L., "Theory of Exhaust-Plume/Bounday-Layer Interactions at Supersonic Speeds," AIAA Journal, Vol. 10, No. 5, 1972, pp. 581-588.
5. Boger, R. C., Rosenbaum, H., and Reeves, B. L., "Flowfield Interactions Induced by Underexpanded Exhaust Plumes," AIAA Journal, Vol. 10, No. 3, 1972; pp. 300-306.
6. Burt, J. R., Jr., "An Investigation of the Effectiveness of Several Devices in Simulating a Rocket Plume at Free Stream Mach Numbers of 0.9 to 1.2," U.S. Army Missile Command, RD-TR-71-22, Redstone Arsenal, AL, Sept. 1971.