Control of Vortical Lift on Delta Wings by Tangential Leading-Edge Blowing
Control of Vortical Lift on Delta Wings by Tangential Leading-Edge Blowing
复制标题
切向前缘吹气控制三角翼涡升力
DOI：
10.2514/3.45583
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发表时间：
1988
影响因子：
2.2
通讯作者：
L. Roberts
中科院分区：
文献类型：
--
作者：
N. Wood;L. Roberts
本文对60 °三角翼前缘切向质量喷射控制涡的可行性进行了实验研究。初步结果表明，直接控制一次分离可以有效地控制迎角达60 °的涡流。在较低迎角时，涡流可能完全从机翼表面消失，恢复完全附着流情况。质量注入的影响已经被证明是从几何迎角解耦的，允许在不改变姿态的情况下控制升力的可能性。标称值B =机翼半翼展c =翼根弦Cg' =展向截面滚转力矩系数CL' =机翼滚转力矩系数Cn =展向截面法向力系数CN =机翼法向力系数Cp =压力系数CM =生物翼动量系数CM * =横流吹气动量系数h =缝高Vj =喷流速度Fw =自由飞行速度ae =有效迎角oig =几何迎角e =机翼半顶角
An experiment has been performed to examine the feasibility of vortex control by tangential mass injection at the leading edge of a 60 deg delta wing. The initial results indicate that direct control of the primary separation allows significant control of the vortex flow up to angles of attack of 60 deg. At lower angles of attack, the vortical flow may be removed entirely from the surface of the wing, recovering the fully attached flow case. The effects of the mass injection have been shown to be decoupled from the geometric angle of attack, allowing the possibility for controlling lift without changing attitude. Nomenclature b =wing semispan c =wing root chord Cg' = spanwise sectional rolling moment coefficient CL' = wing rolling moment coefficient Cn = spanwise sectional normal force coefficient CN = wing normal force coefficient Cp = pressure coefficient CM = bio wing momentum coefficient CM * = crossflow blowing momentum coefficient h = slot height Vj =jet velocity Fw = freestream velocity ae = effective angle of attack oig = geometric angle of attack e = wing semi apex angle