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Computational Study of a McDonnell Douglas Single-Stage-to-Orbit Vehicle Concept for Aerodynamic AnalysisThis paper presents the results of a computational flow analysis of the McDonnell Douglas single-stage-to-orbit vehicle concept designated as the 24U. This study was made to determine the aerodynamic characteristics of the vehicle with and without body flaps over an angle of attack range of 20-40 deg. Computations were made at a flight Mach number of 20 at 200,000 ft. altitude with equilibrium air, and a Mach number of 6 with CF4 gas. The software package FELISA (Finite Element Langley imperial College Sawansea Ames) was used for all the computations. The FELISA software consists of unstructured surface and volume grid generators, and inviscid flow solvers with (1) perfect gas option for subsonic, transonic, and low supersonic speeds, and (2) perfect gas, equilibrium air, and CF4 options for hypersonic speeds. The hypersonic flow solvers with equilibrium air and CF4 options were used in the present studies. Results are compared with other computational results and hypersonic CF4 tunnel test data.
Document ID
19970001416
Acquisition Source
Langley Research Center
Document Type
Contractor Report (CR)
Authors
Prabhu, Ramadas K. (Lockheed Martin Engineering and Sciences Co. Hampton, VA United States)
Date Acquired
September 6, 2013
Publication Date
September 1, 1996
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-201606
NAS 1.26:201606
Accession Number
97N11232
Funding Number(s)
PROJECT: RTOP 242-20-80-02
CONTRACT_GRANT: NAS1-19000
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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