mach range 中文意思是什麼
mach range
解釋
馬赫數范圍-
" another new development is that boeing has announced its plan to develop a faster, longer - range aircraft than can fly at speeds close to the speed of sound ( i. e. mach 0. 95 or faster ) over extended ranges. this new aircraft will open a new chapter in commercial aviation as it provides not only a higher speed and longer range but also the comfort of flight at higher altitudes and the environmental benefits of quieter landings and takeoffs, and in the latter sense it will provide benefits not only to the airlines and passengers but also to the communities living near the airports
95馬赫或更快） 。這類新飛機不但速度較快和可飛越更長程，而且因其在較高高度運作，可令旅客倍感舒適。此外，由於其升降較為寧靜，故不但令航空公司和乘客受惠，也可減少對居住機場附近的社區造成的影響，為商業航空發展編寫新一頁，實在令人鼓舞。 -
In the range of flight mach number mo = 3 ~ 7, in order to take the advantage of ramjet and scramjet, a fix - shaped dual - mode scramjet, in which both subsonic and supersonic combustion can be obtained, is used for hypersonic vehicle
在飛行馬赫數m _ = 3 - 7的范圍內，為充分發揮沖壓發動機的性能優勢，高超聲速飛行器採用了既能在亞聲速燃燒模態，又能在超聲速燃燒模態下工作的固定幾何形狀的雙模態沖壓發動機。 -
The effects of such elements as primary flow total pressure, flow rate, degree of fuel rich, nozzle structure, flying speed and secondary combustion on ejecting mode performance were researched. it was found that thrust augmentation can be achieved on the condition that the flying mach number is above 0. 7. to deeply analyze thrust augmentation mechanism in low speed range, the research was further continued by changing secondary combustion organization and aft - body configuration
研究了一次流總壓、流量、富燃程度、噴管結構、二次流來流速度、二次燃燒組織對引射模態性能的影響，發現實驗樣機構型在0 . 7ma以上的飛行條件下可以獲得推力增強，而在0 . 7ma以下無推力增強。 -
To prove the accuracy of the mach number, and the parameter homogeneity of the design nozzle " s exit, cfd calculate has carried on the design results. under the condition of supersonic and hypersonic flow, and a certain range of temperature, and mach number, the conclusion of the influence of specific heat to nozzle design is drawn
為了驗證所設計的噴管出口馬赫數的大小和噴管出口流場的均勻性，採用nnd格式和b l湍流模型求解雷諾平均n - s方程，對設計結果進行了cfd驗算，得出了在一定溫度范圍內，超音速、高超聲速流動的條件下，不同馬赫數范圍內變比熱容對噴管型面和噴管出口馬赫數的影響。 -
With zonal patched grid technology and second - order zonal solver method, the numerical simulation on inlet complex flow field of solid rocket ramjet assisted range projectiles with different struts shapes was made at different mach numbers
摘要結合分區對接網格技術和二階精度區域分解演算法，對某沖壓增程彈丸進氣道在不同來流攻角和不同側向支柱形狀工況下的內外復雜流場進行了數值模擬。
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