Westerman, Hattori, Daniels & Adrian, LLP
Method for designing a natural laminar flow wing of a supersonic aircraft
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.
Japan Aerospace Exploration Agency
Y B B B B G
Y02T B64C B64F B64C B64C G06F
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Yoshine Hiroaki Kenji Kisa
Ueda Ishikawa Yoshida Matsushima