Relaxation techniques for three-dimensional transonic flow about wings.A relaxation procedure has been developed to treat the three-dimensional, transonic small perturbation equations about finite lifting wings. A combination of two schemes is employed. For flow forward of the wing trailing edge the equations are written in terms of a velocity potential in order to minimize computer algebra and storage. For the remaining flow field the equations are written in terms of the velocity components in order to simplify the enforcement of the Kutta condition. Difference equations and relaxation procedures are described for both schemes. The computational method automatically captures the imbedded shock wave in the three-dimensional flow field. Computed results are given and compared to experiment and other inviscid methods.
Document ID
19720033177
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Bailey, F. R.
Steger, J. L. (NASA Ames Research Center Moffett Field, Calif., United States)
Date Acquired
August 6, 2013
Publication Date
January 1, 1972
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 72-189
Meeting Information
Meeting: American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting