subsonic mach number 中文意思是什麼

subsonic mach number 解釋
亞音速馬赫數
  • subsonic : adj. 亞音(速)的。n. 亞音速飛機。
  • mach : n. 【物理學】馬赫〈超高速單位,馬赫數,=Mach number〉。
  • number : n 1 數;數字;〈pl 〉算術。2 (汽車等的)號碼;第…,第…卷,第…期〈通常略作 No (復數 Nos ),用於...
  1. 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。
  2. The two - dimensional axisymmetric subsonic - transonic - supersonic flow in an experimental arcjet thruster is simulated numerically using flux vector splitting method. the profiles of density, velocity, temperature, pressure and mach number can be obtained by the computation. the computation grid and some computed results are given here. the test equipment such as power supply system, ignition system, propellant supply system, arcjet thruster, thrust measuring device and vacuum system are introduced briefly. some working phenomena of the arcjet are observed and discussed. three different kinds of instability appeared in the process of the experiments. except some important parameters are measured, it is found that the operating stability of argon is better than that of nitrogen

    對一實驗電弧加熱式發動機二維軸對稱亞跨超音速流動進行了數值模擬,所採用的方法是矢通量分裂演算法.通過計算可以得出密度、速度、溫度、壓力和馬赫數的分佈.給出了計算所使用的網格和一些計算結果.簡要介紹了實驗所使用的設備,如電源系統、點火系統、推進劑供給系統、電弧加熱式發動機、推力測量裝置和真空系統.對所觀察到的一些工作現象進行了討論.有三種不同的不穩定性出現于實驗過程.除了所測量的一些重要參數,通過實驗發現氬比氮工作更穩定
  3. 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。
  4. The main results are : supersonic region and subsonic region can co - exist in flow path simultaneously, subsonic flow is insignificance for engine performance ; total pressure of primary rocket should be decreased when mach number is increased. in the experimental aspect, some components of ejectorjet experimental system were improved, ejectorjet experiments using alcohol as secondary fuel were conducted

    由數值計算獲得的結論為:引射火箭內的一般流態為超音速區與亞音速區共存,亞音速區不具備做功能力;飛行馬赫數增大,引射火箭內更易於產生壅塞;為了獲得最佳的性能,隨著飛行馬赫數的提高,應當降低一次火箭的工作壓強。
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