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Nonlinear slender wing aerodynamicsOn present day high performance aircraft, a large portion of the lift is generated by leading edge vortices generated by flow separation off the highly swept leading edges of the lifting surfaces employed. It has been shown in an earlier paper how the vortex effects can be superimposed on a modified slender wing theory to give the unsteady longitudinal characteristics of sharp-edged delta wings up to very high angles of attack. The present paper extends the previous analysis to include the effects of leading edge roundness and trailing edge sweep on the aerodynamic characteristics. The paper also derives analytic means for prediction of the yaw stability of slender wings and the first order effects of Mach number. Universal scaling laws are defined for rapid preliminary design estimates of the slender wing lift and rolling moment. The results indicate that simple analytic tools can be developed to predict the aeroelastic characteristics of the space shuttle ascent configuration with its complicated flow field and aeroelastic cross-couplings.
Document ID
19760035772
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Ericsson, L. E.
(Lockheed Missiles and Space Co. Sunnyvale, CA, United States)
Reding, J. P.
(Lockheed Missiles and Space Co., Inc. Sunnyvale, Calif., United States)
Date Acquired
August 8, 2013
Publication Date
January 1, 1976
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 76-19
Meeting Information
Meeting: Aerospace Sciences Meeting
Location: Washington, DC
Start Date: January 26, 1976
End Date: January 28, 1976
Sponsors: American Institute of Aeronautics and Astronautics
Accession Number
76A18738
Funding Number(s)
CONTRACT_GRANT: NAS8-28310
Distribution Limits
Public
Copyright
Other

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