The results of a parametric, numerical study of aftbody exhaust flows on a conical, airbreathing, hypersonic vehicle are presented. Three-dimensional Euler simulations were performed at Mach 9 and steered to a pitch-trimmed lift-equals-weight condition. Quasi-1-D cycle analysis was employed to model the scramjet propulsion and viscous forces were accounted for using a separate boundary-layer code. The simulation method is presented and credibility demonstrated before parameters controlling the aftbody design and their effect on vehicle performance are reviewed. The parameter sweep resulted in a wide range of predicted performance (thrust-to-drag ratios of 1.17 to 1.79) with 3-D flow features, interaction between engine modules, and trim penalties identified as strong drivers. The large variation in the thrust-to-drag ratio observed in the results of this study highlights the criticality of the aftbody design of an accelerator.
Parametric Study of the Aftbody Design of an Airbreathing Hypersonic Accelerator
Journal of Spacecraft and Rockets ; 58 , 5 ; 1361-1373
2021-04-23
13 pages
Article (Journal)
Electronic Resource
English
DESIGN OF A MINIMUM TRIM HYPERSONIC AIRBREATHING ACCELERATOR VEHICLE
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