Fast Viscous Correction Method for Full-Potential Transonic Wing Analysis
An analysis of the transonic flowfield around a three-dimensional wing is carried out using a strip method. Attention is given to the boundary layer growth in the streamwise direction. A viscous correction technique is defined for the TWING code for solving the full potential equations. A viscous ramp at the base of a shock is superimposed on the boundary layer displacement thickness generated by an integral boundary layer method. A relationship is then obtained between the effective displacement thickness and a vertical component of the surface velocity, a transpirational boundary condition. The viscous correction is found to be unnecessary in weak shock conditions but gives a better shock position and pressure distribution in a strong shock condition when compared with data from an ONERA M6 airfoil and the Hinson and Burdges (1980) Wing A.
S. C. Lee et al., "Fast Viscous Correction Method for Full-Potential Transonic Wing Analysis," Journal of Aircraft, American Institute of Aeronautics and Astronautics (AIAA), Jan 1987.
The definitive version is available at https://doi.org/10.2514/3.45419
Mechanical and Aerospace Engineering
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© 1987 American Institute of Aeronautics and Astronautics (AIAA), All rights reserved.