Effect of the six engine air breathing propulsion system on space shuttle orbiter subsonic and transonic stability and control characteristics (OA91).

Author:: Smith, H. C.
Published:: Mar 1, 1974.
Physical Description:: 1 electronic document

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Summary:

Experimental aerodynamic investigations were conducted on a 0.015 scale representation (Model 42-0) of the VL70-000139B space shuttle orbiter configuration. The test objective was to determine the effect of three air breathing propulsion system ferry/flight test configurations on the transonic drag rise, the elevon effectiveness, the longitudinal stability, and the lateral-directional stability of the -139B shuttle orbiter. The model was sting mounted on a Task 1.5 inch internal strain gage balance, and six-component aerodynamic force and moment data were recorded over an angle of attack range of minus 3 deg to 14 deg at Mach numbers of 0.5, 0.6, 0.7, 0.8, and 0.9 with a Reynolds number of 6.4 million/ft. Data were also recorded at a sides lip angle of five degrees.

Other Subject(s):

SPACE VEHICLES

Collection:

NASA Technical Reports Server (NTRS) Collection.

Note:

Document ID: 19740013410.
Accession ID: 74N21523.
DMS-DR-2116.
NASA-CR-134088.

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