喷流干扰的英文

• jet interference

• "喷"英文翻译    time on the market; in seaso ...
• "干扰"英文翻译    disturb; obstruct; jam; back ...
• "喷流干扰模型" 英文翻译 :    jet interference model
• "喷流干燥器" 英文翻译 :    jet dryer
• "交流干扰" 英文翻译 :    ac interference
• "气流干扰" 英文翻译 :    airflow interference; interference in air flow
• "涡流干扰" 英文翻译 :    vortex interference
• "自由流干扰" 英文翻译 :    free-stream interference
• "残留交流干扰" 英文翻译 :    residual hum
• "交流干扰图像" 英文翻译 :    mains hum pattern
• "图像交流干扰" 英文翻译 :    picture hum
• "位置交流干扰" 英文翻译 :    positional hum
• "涡流干扰效应" 英文翻译 :    vortex interference effect; vortex-interference effect
• "几何形状交流干扰" 英文翻译 :    geometry hum
• "交流干扰喀啦声" 英文翻译 :    grinder
• "旋翼桨尖涡流干扰" 英文翻译 :    rotor-tip vortex interaction
• "流干" 英文翻译 :    drain off
• "喷流" 英文翻译 :    backwash; jet efflux; jet flow; jet stream; open jet; pumjet; spouting; spurt; squirt
• "轮流干……" 英文翻译 :    take turns to do
• "电喷流" 英文翻译 :    electrojet
• "级喷流" 英文翻译 :    cascade
• "墨喷流" 英文翻译 :    ink jet stream
• "喷流的" 英文翻译 :    effusive
• "喷流幕" 英文翻译 :    jet curtain; spray sheet
• "喷流区" 英文翻译 :    jet band

• The aerodynamic pressure expression at jet location and in the area of jet interaction is established by blast wave principium
  采用爆炸波原理建立了喷流区和喷流干扰区的气动压力计算模型。
• 4 . ji effects . author does the work in defining transient jet interaction factor concept and establishing mathematic model
  提出了瞬态喷流干扰因子概念，建立了稳态和瞬态喷流干扰因子数学模型。
• ( 2 ) to evaluate the effects of a reaction control jet on the aerodynamic performance of a missile operating at supersonic / hypersonic flight condition , the single and two attitude jet - interaction flow between a lateral jet and the external flow has been analyzed by detailed numerical simulation
  ( 2 )分别计算了单喷流和双喷流干扰流场。详细分析了流场结构和弹体表面压力分布特性，获得了一些有实用价值的结果。
• Lateral jet control technology is researched in this dissertation , based on supersonic / hypersonic missile aerodynamics and lateral jet interaction ( ji ) effects associated with the attitude control solid - propellant rocket motors system in the low endoatmospheric range
  横向喷流干扰效应研究在超声速高超声速导弹总体设计和精确制导技术研究领域一直占有重要地位。本论文针对大气层内超声速高超声速导弹采用姿态固体火箭发动机侧喷流控制技术的一些问题进行了研究。
• 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
  为了研究以上复杂流场考虑了如下几种情况： ( 1 )带弹翼弹箭超音速无攻角绕流； ( 2 )带弹翼弹箭超音速有攻角绕流； ( 3 )带弹翼弹箭亚音速有攻角绕流； ( 4 )带弹翼弹箭超音速有攻角绕流喷流干扰； ( 5 )带弹翼尾翼弹箭超音速有攻角绕流； ( 6 )带弹翼尾翼弹箭超音速有攻角绕流喷流干扰。