NASA-TN-D-5392
Experimental pressure distributions for a family of blunt bodies at Mach numbers from 2.49 to 4.63 and angles of attack from 0 deg to 15 deg
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Abstract:
Pressure distributions for blunt body wind tunnel models at supersonic speeds and angles of attack from 0 to 15 degrees
Author(s):
D.T. Howell; R.L. Stallings Jr
Indexed under:
- None
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