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用激波-边界层被动控制降低运载火箭的脉动压力

LAUNCH VEHICLE FLUCTUATING PRESSURE REDUCTION BY PASSIVE SHOCK-WAVE/BOUNDARY-LAYER CONTROL
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摘要 一个箭头模型的跨声速风洞实验表明,用激波-边界层被动控制来降低运载火箭头部的脉动压力能获得明显的效果,自由流 M 数为0.87~0.88时,可使脉动压力系数△C_p%的最大值下降50~60%。实验得出了激波下方开孔表面的开孔率变化对脉动压力系数的影响规律:随着开孔率的加大,起初脉动压力系数的下降十分明显,后来△C_p%趋近一个极限值。结果还表明,在激波前采用45°前倾斜孔,在激波后采用直孔的开孔分布比全部采用直孔分布能获得更好的降低脉动压力的效果。所拍摄的纹影照片清楚地显示了采用激波-边界层被动控制后模型表面激波状态的变化。 The transonic wind tunnel tests of a vehicle model showedthat the fluctuating pressure on the surface in the front area of alaunch vehicle can be greatly reduced by passive shock-wave/boundary-layer control.For freestream Mach numbers 0.87~0.88,it led to a reduc-tion in maximum fluctuating pressure coefficient as much as 50~60%.Theresults gave the effects on the fluctuating pressure coefficient due to theporosity variance on the porous surface under the shock-wave.Withthe increase in porosity,at first the fluctuating pressure coefficentreduced rapidly,then it tended to a constant value.The results alsoshowed that the porous surface with 45°forward-facing inclined holesin the region before the shock-wave and mormal holes in the regionbehind the shock-wave produced a larger reduction in fluctuating press-ure than that by mormal holes in the entire porous region.Variationof the shock-wave at model surface by passive shock-wave]boundary-layer control was clearly shown by the schlieren photographs.
作者 卢奇正
出处 《气动实验与测量控制》 CSCD 1991年第4期16-21,共6页
关键词 激波 边界层 脉动压力 运载火箭 shock wave-boundary layer disturbance passive control fluctuating prssure transonic wind tunnel test
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