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san wei ding chang kua yin su ji yi rao liu de song chi fang fa
Author(s): 
Pages: 296-299
Year: Issue:  3
Journal: Chinese Journal of Theoretical and Applied Mechanics

Keyword:  机翼绕流跨音速流动松弛方法压力分布超临界展弦比双圆弧有限差分松弛迭代法three-dimension;
Abstract: Based on difference equations obtained from small perturbation theory and through a hyperbolic tangent transformation which maps the physical space into a cube, the three dimensional steady transonic flow about a wing is computed. Relaxation method reduces the demand on computer memory, and experience is gained through test runs. Calculated results are in good agreement with wind tunnel tests.
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