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Triple balance test of the PRR baseline space shuttle configuration on a .004 scale model of the MCR 0074 orbiter configuration in the MSFC 14 x 14 inch Trisonic Wind Tunnel (TWT 570) IA31F(B), volume 1A wind tunnel force and moment test of the space shuttle launch vehicle was conducted. The wind tunnel model utilized a triple balance such that component aerodynamics of the orbiter, external tank, and solid rocket booster was obtained. The test was conducted at an angle of attack range from -10 deg to 10 deg, and angle of sideslip range from -10 deg to 10 deg, and a Mach number range from 0.6 to 4.96. Simulation parameters to be used in future launch vehicle wind tunnel tests were investigated. The following were included: (1) effect of orbiter -ET attach hardware; (2) model attachment (spacer) effects; (3) effects of grit on model leading surfaces; and (4) model misalignment effects. The effects of external tank nose shape was studied by investigating five different nose configurations. Plotted and tabulated data is reported.
Document ID
19750006738
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Ramsey, P. E. (Chrysler Corp. New Orleans, LA, United States)
Davis, T. C. (Northrop Services, Inc., Huntsville Ala., United States)
Date Acquired
September 3, 2013
Publication Date
December 1, 1974
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
NASA-CR-134434
DMS-DR-2028-VOL-1
Accession Number
75N14810
Funding Number(s)
CONTRACT_GRANT: NAS9-13247
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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