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Design method of natural laminar flow wings at Reynolds number equivalent to real aircraft of supersonic aircraft
Design method of natural laminar flow wings at Reynolds number equivalent to real aircraft of supersonic aircraft
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机译：雷诺数等于超音速飞机真实飞机的自然层流翼的设计方法
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摘要
In designing supersonic aircrafts, a method of designing a natural laminar flow wing is provided which reduces friction drag by delaying boundary layer transition under flight conditions of actual aircrafts. A target Cp distribution on wing upper surface, suited to natural laminarization in which boundary layer transition is delayed rearward in desired Reynolds number states, is defined by a functional type having as coefficients parameters depending on each spanwise station, a sensitivity analysis employing a transition analysis method is applied to the parameters, and a search is performed for the optimum combination of parameters to delay transition rearward.
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