attack jet 中文意思是什麼
attack jet
解釋
戰斗機-
Fluent was used to simulate the flowfield of 3 - d complex flowfield of rocket - missile with wings and empennages induced by the interaction by base jet and the flow around the body. in order to study the complex flow problem above, numerical simulations were performed under the following kinds of flow conditions : ( l ) flow of rocket - missile with wings disturbed by supersonic upstream flow. ( 2 ) flow of rocket - missile with wings disturbed by supersonic upstream flow with attack angle
為了研究以上復雜流場考慮了如下幾種情況： （ 1 ）帶彈翼彈箭超音速無攻角繞流； （ 2 ）帶彈翼彈箭超音速有攻角繞流； （ 3 ）帶彈翼彈箭亞音速有攻角繞流； （ 4 ）帶彈翼彈箭超音速有攻角繞流噴流干擾； （ 5 ）帶彈翼尾翼彈箭超音速有攻角繞流； （ 6 ）帶彈翼尾翼彈箭超音速有攻角繞流噴流干擾。 -
Numerical investigation of three - dimensional steady jet - interaction phenomenology. ( 1 ) aerodynamics characteristic is calculated by using renolds - averaged navier - stokes equations discretitted in cell - centered finite volume framework and improved on baldwin - lomax turbulent model for the slender body at the high angle of attack
（ 1 ）採用三維積分形式n - s方程的中心有限體積離散方法，提出了改進的b - l湍流模型，進行了較大攻角彈體的氣動特性計算和結果分析。 -
The flowfield over low - drag and long - range projectile with small attack angle is numerically studied from transonic to supersonic velocity. it provides basic work for aerodynamics characteristic of this projectile and for lateral jet interaction flowfield, and it shows this projectile can decrease drag. zonal method is tried to compute flow over projectiles and results is satisfied, but computation is much slower
系統研究了低阻遠程彈丸在小攻角狀態，低跨聲速、高跨聲速和超聲速時的非對稱繞流流場，為該彈形氣動力研究提供理論指導並為彈丸側噴流研究奠定基礎，結果顯示低阻遠程彈丸外形具有優化繞流場、減小空氣阻力的特點。
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