subsonic supersonic 中文意思是什麼

subsonic supersonic 解釋
亞音速超音速的
  • subsonic : adj. 亞音（速）的。n. 亞音速飛機。
  • supersonic : adj. 【物理學】超聲波的；【航空】超音速的。 n. 1. 超聲波[頻]。2. 〈口語〉超音速飛機。n. -s 超聲學；超音速學。
  1. This is, of course, the reason why a sonic boom hits us with all its fury from a supersonic aircraft but not from a subsonic one.

    當然，這就是為什麼音爆從超音速飛機上以它的全部力量向我們沖來，而音速飛機上則沒有音爆傳來。
  2. 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。
  3. Both advantages of rocket engine and air - breathing engine are integrated into one kind of propulsion system, called rocket - based - combined - cycle ( rbcc ), which has multiple operating woke modes, including ejecting, subsonic combustion, supersonic combustion and rocket mode, with each mode operating at varying flying stage. rbcc has prominent potential of high efficiency and low cost, and so it is recognized as an advanced propulsion system of future single - stage - to - orbit reusable spacecraft and hipper - sonic missile. it has been broadly investigated in foreign countries and has been progressed into small and full - scale flying stage

    火箭基組合動力循環（ rbcc ， rocketbasedcombinedcycle ）將傳統的火箭發動機和吸氣式發動機的優點集中組合到一個具有多種工作模態（包括引射、亞燃、超燃及火箭模態）的發動機里，在不同的飛行階段啟用不同的工作模態，因此具有大幅提高航天推進系統經濟性與高效性的潛在優勢，並可能發展成為下一代單級可重復使用航天器以及高超聲速導彈武器的動力系統。
  4. According to the jet theory and the characteristics of the flow, the flow can be divided into 6 zones : supersonic core zone, supersonic mixing zone, subsonic mixing zone, secondary flow zone and expanding zone. the rules to distinguish these zones were established. 2

    根據射流理論及引射流動特點，將引射流場結構劃分為超聲速核心區、超聲速混合區、亞聲速混合區、支板背壁迴流區、二次流流動區以及發動機後部膨脹區，並確定了各區域準確劃分的原則。
  5. Then the steady and unsteady subsonic, transonic and supersonic viscous flows around airfoil and some aircraft are numerically simulated. the 3 - dimensional unsteady navier - stokes equations are solved using the implicit lu - nnd algorithm, with baldwin - lomax turbulent model. on the basis of simulating unsteady viscous flow, coupling the structure dynamics equations, the problems of static aeroelasticity and flutter are investigated for wings and elevator

    在模擬非定常粘性繞流的基礎上，與顫振運動方程相耦合，分別對機翼和全機流固耦合現象中顫振問題進行了研究，準確求解跨音速顫振臨界速度，分析機翼和全機的從亞音速到超音速范圍的顫振規律，並研究分析了機翼飛行迎角變化對顫振速度的影響。
  6. Therefore, in this paper the multi - objective optimization design of aerodynamic and stealthy configuration for the fighter is discussed according to the geometrical characteristics of the advanced tactical fighter. the work is performed as follows : 1 according to the different design requirement in subsonic and supersonic state, with the multi - objective optimization method, the aerodynamic configuration optimization method for different design requirements has been obtained

    基於以上考慮，本文從研究氣動隱身多目標優化問題的角度出發，針對先進戰斗機的外形設計特點，完成了以下工作： 1 、針對現代戰斗機亞、超音速的不同設計要求，利用多目標優化設計方法建立了可進行滿足不同設計要求的氣動外形優化設計方法。
  7. In order to research the aerodynamic characteristics of grid fins effected by width to length ratio, the grid fins of three hight to width ratios were adapted in wind tunnel experiments at subsonic, transonic and supersonic speeds

    為研究它對柵格翼氣動特性的影響規律，本研究採用風洞實驗的方法對3種不同格寬翼弦比的柵格翼在亞、跨、超聲速3個馬赫數下進行了氣動特性的研究。
  8. The research of this dissertation is focused on how to simulate numerically the steady and unsteady subsonic, transonic and supersonic viscous flows around wing and aircraft by computational fluid dynamics method. on this basis, several kinds of aeroelastic problems of aircraft are investigated

    本文的主要工作是利用計算流體力學（ cfd ）方法，數值模擬機翼和全機的定常及非定常粘性繞流，並在此基礎上耦合結構動力學方程研究了飛行器的多種氣動彈性問題。
  9. 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
  10. The two - dimensional axisymmetric subsonic - transonic - supersonic flow in an experimental arcjet thruster is simulated numerically using flux vector splitting method

    摘要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。
  11. Scramjet combustor may realize the subsonic - combustion mode and supersonic - combustion mode respectively based on the control of fuel in variable flight conditions. isolator has great effect on mode transition and preventing unstart of inlet. inlet can be unstarted by raising the back pressure result from chemical energy release in the combustor

    計算研究表明，在相同的來流條件下，供油規律對燃燒室的工作模態有著重大的影響；在不同的來流條件下，可以通過調節供油規律使燃燒室分別實現亞燃模態和超燃模態；隔離段對防止燃燒引起的壓力升高對進氣道的干擾和燃燒室的模態轉換具有重要的作用。
  12. The domestic research plan has been proposed and undertaken in nowadays. the progress in subsonic and supersonic combustions has been attained, but the ejecting mode and mode match of rbcc has just been begun

    國內已制定了研究計劃並正在開展，其中亞燃和超燃模態的研究取得了相當的進展，但引射模態以及模態匹配的研究還剛剛起步。
  13. 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。
  14. After that, the one - stage prs is connected with the chemical laser system to test cooperation of the two systems. tests show that the ejecting capacity of the one - stage prs is unable to fulfil the exhaust requkement of the chemical laser system, and that the starting process of the cavity and the diffuser is not thorough and the cavity pressure is too high, with the power output of the laser decreasing sharply. then, based on the achievements of the one - stage prs, a " subsonic - supersonic " two - stage prs is developed and a lot of tests are made

    隨后，開展了單級引射prs系統與df化學激光器的聯試研究工作，通過大量的聯試實驗，研究了激光器配方、引射器引射能力、聯試時序和擴壓器方案等等，對擴壓器和光腔的啟動特性、光腔壓強和出光功率的影響，得出了光腔壓強過低、單級引射prs系統無法滿足其壓縮比要求，需考慮採用兩級引射prs系統的結論。
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