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Experimental and theoretical aerodynamic characteristics of two hypersonic cruise aircraft concepts at Mach numbers of 2.96, 3.96, and 4.63The longitudinal and lateral directional aerodynamic characteristics for two Mach 5 cruise aircraft concepts were determined for test Mach numbers of 2.96, 3.96, and 4.63. Estimates from hypersonic impact theory and first order supersonic linearized theory were compared with data to indicate the usefulness of these methods. The method which applied tangent cone empirical theory to the body and tangent wedge theory to the wings and to the horizontal and vertical tails provided the best estimates. The tangent cone empirical theory applied to all components showed poor agreement with data, and the linear theory estimates were accurate only for lift coefficient and drag coefficient at low angles of attack.
Document ID
19810003513
Document Type
Technical Publication (TP)
Authors
Pittman, J. L. (NASA Langley Research Center Hampton, VA, United States)
Riebe, G. D. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
December 1, 1980
Subject Category
AERODYNAMICS
Report/Patent Number
NASA-TP-1767
L-13868
Funding Number(s)
PROJECT: RTOP 505-31-73-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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