AIRCRAFT AND RE-LAMINARIZATION CONFIRMATION CALCULATION MACHINE OF AIRCRAFT

PROBLEM TO BE SOLVED: To confirm that re-laminarization phenomenon is generated at a transonic range and to suppress the re-laminarization phenomenon of the transonic range. SOLUTION: A vortex excitation structure 27 arranged so as to be supported to an airframe 15 and re-exciting a turbulent flow boundary layer is provided at a downstream side of the turbulent flow boundary layer produced at a surface area of the airframe 15 flying at a transonic speed. When it flies at the transonic speed, the turbulent flow sometimes makes the re-laminarization. When the re-laminarization is not carried out, it is not preferably that the vortex excitation structure 27 is added since resistance of the airframe 15 is increased. But profits for avoiding unstabilization of lift or reduction of the lift is large by avoiding re-laminarization and avoiding generation of an impact wave by sacrificing increase of the resistance. Existence of the re-laminarization can be easily confirmed by digitalizing an acceleration parameter as a determination index. COPYRIGHT: (C)2005,JPO&NCIPI