Wind Tunnel and Flight Performance of the YF-12 Inlet System

Smeltzer, D. B.; Smitht, Ronald H.; Cubbison, R. W.

doi:10.2514/3.59814

Cited by 4 publications

(1 citation statement)

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“…Therefore, variable geometry hypersonic inlet are increasingly receiving devotion of researchers[5~7] because of its capability in matching engine in wide flight range, superior self-start ability and the steady operation potential in mode transition process [7,8]. Blackbird supersonic cruise reconnaissance plane adopted supersonic axisymmetric variable geometry inlet to match the twin J-58 engines [9]. By translating the inlet centerbody from stretching position at low Mach inflow condition backward to retracted position at high Mach status, CR of the inlet increases to gain a larger internal compression.…”

Section: Introductionmentioning

confidence: 99%

Design Methodology and Unsteady Aerodynamic Characteristics of a Rectangular Variable Geometry Hypersonic Inlet

Teng

Yuan

2013

AMM

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Design methodology of a rectangular variable geometry hypersonic inlet whose cowl lip is translatable along flow direction is clarified in current study and recommendation of key design parameters are given. Unsteady Reynolds-averaged Navier-Stokes (uRANS) calculation were carried out to investigate the feasibility and unsteady aerodynamic characteristics of this inlet. Results indicate that by stretching the movable lip of a model inlet upstream, mass flow rate will increases apparently due to the increases of inlet internal duct entrance area. Stretching the movable lip upstream will decrease CR of the model inlet which is favorable for the start or restart of the inlet from an unstarted status. The lip translating process is smooth and will not induce large amplitude flow disturbance within inlet duct. The movable lip is conducive to improve the aeropropulsive performance of the hypersonic inlet in wide flight range

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Section: Introductionmentioning

confidence: 99%