Wind tunnel test of the 0.010-scale space shuttle integrated vehicle in the NASA-Ames 3.5 foot hypersonic wind tunnel (IA10).

Author:: Fitzgerald, F. F.
Published:: Dec 1, 1973.
Physical Description:: 1 electronic document
Additional Creators:: Mellenthin, J. A., Cleary, J. W., and Petrozzi, M. T.

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Summary:

Experimental aerodynamic investigations were conducted in the NASA Ames Research Center 3.5-Foot Hypersonic Wind Tunnel on a 0.010-scale model of the space shuttle vehicle orbiter and external tank (model no. 32 0T). The purpose of the test was to evaluate the basic hypersonic stability characteristics of the external tank and orbiter and to define orbiter plume effects on aero characteristics using solid plumes. The test was conducted at angles of attack from minus 10 deg to 30 deg and angles of sideslip of minus 10 deg thru 10 deg. Six component force data and static base pressures were recorded during the test.

Other Subject(s):

SPACE VEHICLES

Collection:

NASA Technical Reports Server (NTRS) Collection.

Note:

Document ID: 19740008445.
Accession ID: 74N16558.
NASA-CR-128795.
DMS-DR-2078.

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