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Transonic aerodynamic and aeroelastic characteristics of a variable sweep wingThe flow over the B-1 wing is studied computationally, including the aeroelastic response of the wing. Computed results are compared with results from wind tunnel and flight tests for both low-sweep and high-sweep cases, at 25.0 deg. and 67.5 deg., respectively, for selected transonic Mach numbers. The aerodynamic and aeroelastic computations are made by using the transonic unsteady code ATRAN3S. Steady aerodynamic computations compare well with wind tunnel results for the 25.0 deg. sweep case and also for small angles of attack at the 67.5 deg. sweep case. The aeroelastic response results show that the wing is stable at the low sweep angle for the calculation at the Mach number at which there is a shock wave. In the higher sweep case, for the higher angle of attack at which oscillations were observed in the flight and wind tunnel tests, the calculations do not show any shock waves. Their absence lends support to the hypothesis that the observed oscillations are due to the presence of leading edge separation vortices and are not due to shock wave motion as was previously proposed.
Document ID
19850016892
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Goorjian, P. M. (NASA Ames Research Center Moffett Field, CA, United States)
Guruswamy, G. P. (Informatics General Corp. Palo Alto, Calif., United States)
Ide, H. (NASA Ames Research Center Moffett Field, CA, United States)
Miller, G. (Rockwell International Los Angeles, Calif., United States)
Date Acquired
September 5, 2013
Publication Date
February 1, 1985
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.15:86677
NASA-TM-86677
A-85119
Accession Number
85N25203
Funding Number(s)
PROJECT: RTOP 505-31-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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