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Fast viscous correction method for full-potential transonic wing analysis
- Source :
- Journal of Aircraft. 24:218-220
- Publication Year :
- 1987
- Publisher :
- American Institute of Aeronautics and Astronautics (AIAA), 1987.
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Abstract
- 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.
Details
- ISSN :
- 15333868 and 00218669
- Volume :
- 24
- Database :
- OpenAIRE
- Journal :
- Journal of Aircraft
- Accession number :
- edsair.doi...........f6e97bb49a726687d2a056a67579bec3