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Impact of fuselage incidence on the supersonic aerodynamics of two fighter configurationsThe results of experimental and theoretical investigations into the effect of fuselage upwash on fighter aircraft wing performance are reported. Wind tunnel trials were performed on 4 percent scale models of two supersonic fighters. The trials were run at Mach 1.6-2.0, an Re of 2,000,000 and at angles of attack (AOA) of -4 to 20 deg. Measurements were made of lift, drag and pitching moments. Two linearized theory supersonic aerodynamic prediction codes, PAN AIR and the SDAS lift analysis, were used to predict the same aerodynamic coefficients. The fuselage AOA augmented the lift and pitching moment at 0, 2 and 5 deg. The contribution mainly arose from the fuselage-induced upwash. The PAN AIR code gave superior data for the fuselage aerodynamics and effects, although both codes accurately predicted the overall lift and moment increments due to the fuselage AOA.
Document ID
19840058558
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Wood, R. M.
(NASA Langley Research Center Hampton, VA, United States)
Miller, D. S.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 12, 2013
Publication Date
August 1, 1984
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 84-2193
Accession Number
84A41345
Distribution Limits
Public
Copyright
Other

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