Asymmetric divert jet performance of a supersonic missile: Computational and experimental comparisons

Authors
Citation
B. Srivastava, Asymmetric divert jet performance of a supersonic missile: Computational and experimental comparisons, J SPAC ROCK, 36(5), 1999, pp. 621-632
Citations number
19
Language
INGLESE
art.tipo
Article
Categorie Soggetti
Aereospace Engineering
Journal title
JOURNAL OF SPACECRAFT AND ROCKETS
ISSN journal
0022-4650 → ACNP
Volume
36
Issue
5
Year of publication
1999
Pages
621 - 632
Database
ISI
SICI code
0022-4650(199909/10)36:5<621:ADJPOA>2.0.ZU;2-4
Abstract
Computational fluid dynamics (CFD) predictions are compared with the wind-t unnel tests for a missile consisting of ogive-nose cylindrical body, four w ings, and four in-lined tail panels at nominal supersonic Mach numbers 2, 3 , 4, and 5 and at angles of attack ranging from 0 to 35 deg with and withou t a lateral jet thruster with thrust ratios of 1 and 4. Comparisons also in clude roll angles that lead to asymmetric missile configuration with the th ruster jet. Excellent comparisons of the predicted normal-force, side-force , pitching-moment, yawing-moment, and rolling-moment coefficients with the measured data are shown. CFD-computed flowfield then is utilized to show th at the lateral thruster jet effectiveness diminishes as the jet thruster is gradually rolled toward the windward side of the missile. Flow physics ass ociated with this phenomenon and possible mechanisms to alleviate this effe ct are discussed.