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Aerodynamic characteristics of a hypersonic research airplane concept having a 70 deg swept double-delta wing at Mach numbers from 0.80 to 1.20, with summary of data from 0.20 to 6.0The static longitudinal, lateral, and directional stability characteristics of a hypersonic research airplane concept having a 70 deg swept double-delta wing were investigated. Force tests were conducted in the Langley 8 foot transonic pressure tunnel for a Reynolds number (based on fuselage length) range of 6.30 x 10 to the 6th power to 7.03 x 10 to the 6th power, at angles of attack from about -4 deg to 23 deg, and at angles of sideslip of 0 deg and 5 deg. The configuration variables included the wing planform, tip fins, the center vertical tail, and scramjet engine modules. Variations of the more important aerodynamic parameters with Mach number for Mach numbers from 0.20 to 6.0 are summarized. A state-of-the-art example of theoretically predicting performance parameters and static longitudinal and directional stability over the Mach number range is included.
Document ID
19800003814
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Penland, J. A. (NASA Langley Research Center Hampton, VA, United States)
Hallissy, J. B. (NASA Langley Research Center Hampton, VA, United States)
Dillon, J. L. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
December 1, 1979
Subject Category
Aerodynamics
Report/Patent Number
L-13158
NASA-TP-1552
Accession Number
80N12064
Funding Number(s)
PROJECT: RTOP 505-11-33-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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