高超声速杆-盘-自耦合冲压横向射流概念的减阻防热数值模拟

Numerical simulation on drag and heat reduction of hypersonic spike-aerodisk-self-coupled stamping lateral jet concept

对高超声速杆-盘-自耦合冲压横向射流构型的减阻防热效果进行数值模拟。相比单纯减阻杆-气动盘,杆-盘-自耦合冲压横向射流构型将剪切层推离壁面,扩大了靠近钝体的回流区,并将分离激波推离减阻杆,再附激波强度明显减弱,组合构型减阻防热特性显著提高。研究了杆-盘-自耦合冲压横向射流构型的减阻防热机理,并研究了不同参数对减阻防热效果的影响:在研究范围内,侧向排气口角度从30°增加到90°,减阻防热效果不断提升,但是当侧向排气角度从90°增加到120°,减阻防热效果略有降低。对于侧向多排气口,第二侧向排气口距离钝体壁面越远,减阻防热性能越好。在研究范围内,减阻防热效果最好的构型,与同参数减阻杆-气动盘构型相比,钝体壁面斯坦顿数峰值降低39.7%,构型阻力系数降低19.3%。

The drag and heat reduction effect of hypersonic spike-aerodisk-self-coupled stamping lateral jet configuration was numerically simulated.Compared with the simple spike-aerodisk,the spikeaerodisk-self-coupled stamping lateral jet configuration pushed the shear layer away from the wall,enlarged the recirculation zone near the blunt body,and pushed the separating shock away from the spike.The strength of the attachment shock was significantly weakened,and the drag and heat reduction characteristics of the combined configuration were significantly improved.The drag and heat reduction mechanism of the spike-aerodisk-self-coupled stamping lateral jet configuration was studied,and the influences of different parameters on the drag and heat reduction effect were discussed.Within the study range,the drag and heat reduction effect was continuously improved when the lateral jet angle increased from 30°to 90°,but when the lateral jet angle increased from 90°to 120°,the drag and heat reduction effect decreased slightly.For lateral multiple jets,the farther the second lateral jet was from the blunt body wall surface,the better the drag and heat reduction performance.The configuration with the best drag and heat reduction effect was compared with the configuration with the same parameter spike-aerodisk,finding that the peak value of Stanton number on blunt body wall was reduced by 39.7%,and the drag coefficient of configuration was reduced by 19.3%.