In order to investigate the effects of factors such as Mach number,Reynolds number,sweep angle,wall temperature and pressure gradient on the natural transition of supersonic boundary layer in the cross-flow mode and Oblique T-S mode,linear stability theory(LST)and eN transition prediction method are used in two-dimensional or quasi three-dimensional flows such as flat plates,airfoils and infinite swept-back wings.The effects of these influencing factors on the N factor of cross-flow mode and Oblique T-S mode are studied through variable parameter analysis.Based on the inflow and wall conditions set in the cases in this article,the calculation results show that the growth rate of the N factor in the cross-flow mode is positively correlated with the inflow Mach number and Reynolds number,respec-tively.As the sweep angle increases from 30 ° to 60 °,the N factor growth of the cross-flow mode continues to accel-erate.After exceeding 60 °,N factor growth in the stationary wave begins to weaken,while the N factor in travelling wave does not change significantly in the range of 60 ° to 75°.It can be inferred that the critical sweep angle at which the N factor in travelling wave begins to decay is larger.The N factor growth rate of Oblique T-S mode is positively correlated with the inflow Reynolds number,the ratio of wall temperature to inflow temperature,respectively.The N factor growth rate decreases as the inflow Mach number increases or the positive pressure gradient increases.There-fore,the influence of the variation of inflow Mach number on natural transition is related to the type of analyzed in-stability mode,while the trend of the influence of the variation of inflow Reynolds number on the N factor of natural transition of cross-flow mode and Oblique T-S mode is consistent.
cross-flow modeOblique T-S modeMach numberReynolds numbersweep anglewall temperature
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