Surface configuration for delaying transition of hypersonic boundary layer and surface configuration manufacturing method

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Surface configuration for delaying transition of hypersonic boundary layer and surface configuration manufacturing method

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YANG JIAJI / LYU PENG / CHEN ZHIPING / WANG XI

The invention provides a surface configuration for delaying hypersonic boundary layer transition and a surface configuration manufacturing method, the surface configuration comprises a plurality of groove channels arranged on the surface of an aircraft, the plurality of groove channels are arranged in the boundary layer range of the aircraft, the width of the groove channels is gradually reduced from the top of the groove channels to the bottom of the groove channels, and the width of the groove channels is gradually reduced from the top of the groove channels to the bottom of the groove channels. The multiple groove channels are used for inhibiting unstable second modal growth in the boundary layer, and the second modal change range of the aircraft surface provided with the multiple V-shaped section groove channels is smaller than the second modal change range of the aircraft surface provided with the multiple rectangular section groove channels. The aircraft surface provided with the plurality of V-shaped cross section grooves effectively inhibits the growth of the second mode so as to delay the transition of the boundary layer, and when the flow condition changes, the aircraft surface provided with the plurality of V-shaped cross section grooves has a better conservative design effect.

本发明提供一种用于延迟高超声速边界层转捩的表面构型及表面构型制造方法，该表面构型包括设置在飞行器表面的多个凹槽道，多个凹槽道设置在飞行器的边界层范围内，凹槽道的宽度沿凹槽道的顶部向凹槽道底部方向渐缩，多个凹槽道用于抑制边界层内不稳定的第二模态增长，其中，设有多个V形截面凹槽道的飞行器表面的第二模态变化范围小于设有多个矩形截面凹槽道的飞行器表面的第二模态变化范围，设有多个V形截面凹槽道的飞行器表面有效抑制了第二模态增长，进而延迟边界层转捩，当流动条件发生改变时，设有多个V形截面的凹槽道的飞行器表面有更好的保守设计效果。