Flow-Field Investigation of a 0.0667-Scale Model of the X-15 Research Vehicle at Mach 4, 6, 8
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Report Number: AEDC -TDR-201
Author(s): Rippey, J.
Corporate Author(s): ARO, inc.
Laboratory: Arnold Engineering Development Center
Date of Publication: 1964-10
Pages: 25
Contract: AF 40(600)-1000
DoD Task:
Identifier: AD0448305
Abstract:
Selected results are presented from pressure tests of a 0.0667-scale model of the X-15 research vehicle at Mach numbers of 4, 6, and 8. The effects of Mach number and model attitude on the flow-field characteristics between the model surface and nose shock wave were investigated in the region of a proposed air-breathing engine. The tests were conducted at a Reynolds number of 3.4 x 10 to the 6th power per foot through an angle-of-attack range from -3 to 20 deg.
Provenance: Bearcat
Author(s): Rippey, J.
Corporate Author(s): ARO, inc.
Laboratory: Arnold Engineering Development Center
Date of Publication: 1964-10
Pages: 25
Contract: AF 40(600)-1000
DoD Task:
Identifier: AD0448305
Abstract:
Selected results are presented from pressure tests of a 0.0667-scale model of the X-15 research vehicle at Mach numbers of 4, 6, and 8. The effects of Mach number and model attitude on the flow-field characteristics between the model surface and nose shock wave were investigated in the region of a proposed air-breathing engine. The tests were conducted at a Reynolds number of 3.4 x 10 to the 6th power per foot through an angle-of-attack range from -3 to 20 deg.
Provenance: Bearcat