NDLI: Experimental and theoretical aerodynamic characteristics of two hypersonic cruise aircraft concepts at mach numbers of 2.96, 3.96, and 4.63

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Experimental and theoretical aerodynamic characteristics of two hypersonic cruise aircraft concepts at mach numbers of 2.96, 3.96, and 4.63

Content Provider	NASA Technical Reports Server (NTRS)
Author	Riebe, G. D. Pittman, J. L.
Copyright Year	1980
Description	The 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.
File Size	6951327
Page Count	117
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19810003513
Archival Resource Key	ark:/13960/t6j14vp2j
Language	English
Publisher Date	1980-12-01
Access Restriction	Open
Subject Keyword	Aerodynamics Supersonic Aircraft Aerodynamic Configurations Nacelles Angle of Attack Aerodynamic Characteristics Hypersonic Aircraft Supersonic Drag Lift Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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