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Design Evolution and Performance Characterization of the GTX Air-Breathing Launch Vehicle InletThe design and analysis of a second version of the inlet for the GTX rocket-based combine-cycle launch vehicle is discussed. The previous design did not achieve its predicted performance levels due to excessive turning of low-momentum comer flows and local over-contraction due to asymmetric end-walls. This design attempts to remove these problems by reducing the spike half-angle to 10- from 12-degrees and by implementing true plane of symmetry end-walls. Axisymmetric Reynolds-Averaged Navier-Stokes simulations using both perfect gas and real gas, finite rate chemistry, assumptions were performed to aid in the design process and to create a comprehensive database of inlet performance. The inlet design, which operates over the entire air-breathing Mach number range from 0 to 12, and the performance database are presented. The performance database, for use in cycle analysis, includes predictions of mass capture, pressure recovery, throat Mach number, drag force, and heat load, for the entire Mach range. Results of the computations are compared with experimental data to validate the performance database.
Document ID
20020073103
Acquisition Source
Glenn Research Center
Document Type
Conference Paper
Authors
DeBonis, J. R.
(NASA Glenn Research Center Cleveland, OH United States)
Steffen, C. J., Jr.
(NASA Glenn Research Center Cleveland, OH United States)
Rice, T.
(Johns Hopkins Univ. Shadyside, MD United States)
Trefny, C. J.
(NASA Glenn Research Center Cleveland, OH United States)
Date Acquired
August 20, 2013
Publication Date
April 1, 2002
Publication Information
Publication: 26th JANNAF Airbreathing Propulsion Subcommittee Meeting
Volume: 1
Subject Category
Launch Vehicles And Launch Operations
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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