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Experimental low-speed and calculated high-speed aerodynamic characteristics of a hypersonic research airplane concept having a 65 deg swept delta wingAn experimental wind-tunnel investigation has been carried out to determine the static longitudinal, lateral, and directional stability and control characteristics of a model of a large-body, delta-wing hypersonic research airplane concept at low speed. This investigation was conducted at a dynamic pressure of 239.4 Pa (5 psf) and a Reynolds number, based on fuselage length, of 2 million. The configuration variables included vertical fins, engine modules, canards, and a canopy. The aerodynamic results of a computer study at Mach numbers of 3 to 12 are presented.
Document ID
19740023375
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Technical Note (TN)
Authors
Penland, J. A. (NASA Langley Research Center Hampton, VA, United States)
Creel, T. R., Jr. (NASA Langley Research Center Hampton, VA, United States)
Howard, F. G. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 3, 2013
Publication Date
August 1, 1974
Subject Category
Aircraft
Report/Patent Number
NASA-TN-D-7633
L-9453
Report Number: NASA-TN-D-7633
Report Number: L-9453
Accession Number
74N31488
Funding Number(s)
PROJECT: RTOP 760-66-01-02
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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