NDLI: Calculation of aerodynamic characteristics of airplane configurations at high angles of attack

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Calculation of aerodynamic characteristics of airplane configurations at high angles of attack

Content Provider	NASA Technical Reports Server (NTRS)
Author	Tseng, J. B. Lan, C. Edward
Copyright Year	1988
Description	Calculation of longitudinal and lateral directional aerodynamic characteristics of airplanes by the VORSTAB code is examined. The numerical predictions are based on the potential flow theory with corrections of high angle of attack phenomena; namely, vortex flow and boundary layer separation effects. To account for the vortex flow effect, vortex lift, vortex action point, augmented vortex lift and vortex breakdown effect through the method of suction analogy are included. The effect of boundary layer separation is obtained by matching the nonlinear section data with the three dimensional lift characteristics iteratively. Through correlation with results for nine fighter configurations, it is concluded that reasonably accurate prediction of longitudinal and static lateral directional aerodynamics can be obtained with the VORSTAB code up to an angle of attack at which wake interference and forebody vortex effect are not important. Possible reasons for discrepancy at higher angles of attack are discussed.
File Size	5585287
Page Count	119
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19880019507
Archival Resource Key	ark:/13960/t3pw1cx4r
Language	English
Publisher Date	1988-10-01
Access Restriction	Open
Subject Keyword	Aerodynamics Suction Flow Theory Longitudinal Stability Lift Potential Flow Boundary Layer Separation Aerodynamic Configurations Directional Stability Vortices Aerodynamic Interference Angle of Attack Aircraft Configurations Fighter Aircraft Viscous Flow 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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