inlet attack 中文意思是什麼
inlet attack
解釋
進口侵蝕-
On the basis of these results, the relations of total - pressure recovery coefficient or flow coefficient and flight mach number, angle of attack and the second movable wedge angle of the inlet have been founded by hypersurface fitting, then the mathematical model of the inlet is established
根據流場計算結果並利用超曲面擬合方法建立了進氣道總壓恢復系數、流量系數與飛行馬赫數、進氣道攻角及二級可調斜板角度之間的關系，由此得到了二元混壓式超聲速進氣道數學模型。 -
The existence of angle of attack reduces the inlet performance
攻角的存在也在一定程度上降低了進氣道性能。 -
At large attack angle the frequency of the vortex has n ' t a apparent zone of " lock - in ". the fluid - induced vibration at large attack angle belongs to the stable dynamic response problems. but a sudden skip of amplitude will occur at large inlet velocity
在大攻角下分離渦脫落的頻率沒有一個明顯的頻率鎖定區域，流體振動屬于穩定的動力響應問題，但在大來流速度下會出現振幅突跳的現象。 -
The full flow field characteristics of a supersonic inlet are illustrated at design conditions ; the influence of attack angle on flow field of the inlet is investigated ; b - spline theory is used to model the inlet with attack angle
給出了設計狀態下進氣道內外流場特徵；分析了攻角變化對進氣道流場的影響；以數值模擬結果為基礎，利用b樣條理論建立了反映攻角、馬赫數及可調斜板角度變化的超聲速進氣道數學模型。 -
On basis of the modeling results, the effects of mach number, attack angle and ramp angle on the inlet performance are analyzed
根據此數學模型，分析了攻角和進口氣流馬赫數對進氣道性能的影響，同時給出了斜板對進氣道性能的影響。 -
The relevance functions between total pressure recover coefficient and the parameters ( mach number, angle of attack, flow coefficient, angle of sideslip ) for subsonic submerged inlet in turbojet and turbofan engine were investigated
摘要根據某埋入式進氣道試驗數據建立了計算埋入式亞聲速進氣道總壓恢復系數的經驗公式，表現為關于馬赫數、流量系數、攻角、側滑角的函數。 -
At different attack angles, mach numbers and ramp angles, the numerical calculations of inner and external flow field are performed for an adjustable mixed compression inlet
摘要對某可調混壓進氣道在不同攻角、不同馬赫數、不同斜板角度下進行了大量的數值計算。
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