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subsonic

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subsonic adj.亞音(速)的。n.亞音速飛機。

adj. 亞音(速)的。 n. 亞音速飛機。 “aerodynamics; subsonic“ 中文翻譯：   次音速空氣動力學“aircraft; subsonic“ 中文翻譯：   次音速飛機“airfoil; subsonic“ 中文翻譯：   次音速翼形“all subsonic“ 中文翻譯：   純亞音速的“all-subsonic“ 中文翻譯：   按亞音速設計的; 純亞音速的“flow，subsonic“ 中文翻譯：   次音速流動“speed; subsonic“ 中文翻譯：   次音速“subsonic acceleration“ 中文翻譯：   亞音速加速度“subsonic accident“ 中文翻譯：   亞音速飛行事故“subsonic accidents“ 中文翻譯：   亞音速飛行事故“subsonic aerodynamics“ 中文翻譯：   亞聲速空氣動力氣; 亞聲速空氣動力學; 亞音速空氣動力學“subsonic aircraft“ 中文翻譯：   亞聲飛機; 亞音速飛機“subsonic airfoil“ 中文翻譯：   亞音速翼型“subsonic airstream“ 中文翻譯：   亞音速氣流“subsonic area“ 中文翻譯：   亞音速區“subsonic climb“ 中文翻譯：   亞音速上升“subsonic combat“ 中文翻譯：   亞音速戰斗“subsonic combustion“ 中文翻譯：   亞音速燃燒“subsonic compression“ 中文翻譯：   超音速壓縮; 亞聲速壓縮“subsonic compressor“ 中文翻譯：   壓聲壓氣機; 亞音速壓氣機; 亞音速壓縮機; 亞音速壓縮器“subsonic diffuser“ 中文翻譯：   亞音速擴壓器“subsonic diffusion“ 中文翻譯：   亞音速擴散“subsonic discharge“ 中文翻譯：   亞音速流出“subsonic; critical“ 中文翻譯：   臨界次音速“subsoluble group“ 中文翻譯：   子可解群“subsolifuction“ 中文翻譯：   水下解凍泥流

subspace

The research of this dissertation is focused on how to solve the 3 - dimensional compressible navier - stokes equations by the implicit finite difference algorithm and to simulate numerically the unsteady subsonic and transonic viscous flows around rigid and elastic wings . on the base of them the aeroelastic characterictics of an elastic wing have been studied 本文的主要工作是用隱式有限差分法求解三維非定常紊流n - s方程組，數值模擬剛性機翼及彈性機翼的亞、跨、超音速定常及非定常粘性繞流，并在此基礎上研究了彈性機翼的氣動彈性問題。

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，引射火箭內更易于產生壅塞；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。

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，所采用的方法是矢通量分裂算法.通過計算可以得出密度、速度、溫度、壓力和馬赫數的分布.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

Nasa - 37 transonic and nwpu - 1 subsonic rotors are calculated by using this program . results of calculation indicates that this program can admirably simulate rotor rows flow in axial compressors and distinguish passage shock , leakage vortex path and separation of boundary layer 用該程序分別計算了nasa - 37跨音速轉子和nwpu - 1亞音速轉子，計算結果表明本文建立的孤立轉子程序能夠較好的模擬軸流壓氣機葉片排內流動情況，能夠有效的捕捉通道激波和間隙泄漏渦軌跡以及葉片附面層的分離。

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，并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。

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，需考慮采用兩級引射prs系統的結論。

The relationship between the load measured by strain method and the load calculated according to flight parameters and the wind tunnel test data has been investigated in this thesis . the result showed that the calculation load based on the flight parameters and wind tunnel test data is acceptable in subsonic speed and gets good agreement , with the load measured by strain method 本文研究了采用應變法實測載荷和根據飛行實測參數和風洞實驗數據計算載荷之間的關系，研究表明采用飛行實測參數和風洞實驗的數據計算載荷在亞音速范圍內是可行的，與采用應變法實測載荷是吻合的。

The moving grid of type c - h for wing are generated by an algebraic procedure . the steady and unsteady transonic ( and subsonic ) viscous flows around wing are numerically simulated . the 3 - dimensional time - averaged compressible navier - stokes equations with b - l or j - k turbulent models are solved by the implicit lu - n7nd algorithm 用代數方法生成機翼的c - h型運動網格，從三維非定常n - s方程組出發，利用lu - nnd有限差分格式和b - l或j - k湍流模型建立了一種數值模擬三維機翼的亞、跨、超音速定常及非定常粘性繞流的方法和程序。

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，并研究分析了機翼飛行迎角變化對顫振速度的影響。

The method of wing shape optimization of space shutlle has been developed with penalty function approach in which the objective function is the mass of the wing and the constraints are the hypersonic re - entry flight cross range , lift / drag ratio , and subsonic flight lift / drag ratio , the margin of the longitudial static stability and the magnitude of the horizontal landing speed etc 摘要介紹了在滿足高超音速再入橫向機動航程，高超音速再入飛行時的升阻比，亞音速進場飛行時的升阻比，縱向靜穩定性裕度和水平著陸速度等飛行性能設計要求下，用罰函數法尋求使航天飛機機翼質量為最小的外形優化方法并給出了算例。

The optimized shape in the parameter range was obtained . in order to studied the lightcraft ’ s flight performance , the 3 - d lightcraft aerodynamic performance research at different altitudes , velocity and angle of attack were simulated . in subsonic situation , the drag coefficient was reducing with the angle of attack increasing , but in supersonic situation , the drag coefficient was increasing with the angle of attack increasing 分析了激光推進技術的基本原理及其特點,對光船的氣動性能進行了數值模擬,在流場分析的基礎上,對光船的頭部外形進行了優化,并給出了參數變化范圍內的優化外形;為了進一步研究光船的飛行性能,對不同高度、不同速度和不同攻角等飛行條件下的三維光船氣動性能進行了數值研究,研究表明:在亞聲速情況下,阻力系數隨攻角的增大而減小;超聲速情況下,阻力系數隨攻角增大而增大。

The comparison showed that : ( l ) farassat 1a formula is the simplest one and work well for the subsonic rotor . ( 2 ) both kirchhoff formula and k - fwh formula can predict the nonlinear noise generated by transonic rotor ; ( 3 ) when the surface is not positioned in the linear region , kirchhoff approach for rotating integration surface could lead to substantial error , but k - fwh formula can still work well 數值研究表明： farassat1a公式在預測線性噪聲方面簡單有效，適用于亞音速旋翼的噪聲預測； kirchhoff公式和k - fwh公式均能夠預測跨音速旋翼聲場，并且具有較高的精度；當聲源面位于流動非線性時， kirchhoff公式會導致很大的計算誤差，而k - fwh公式不存在這樣的問題。

The coatings deposited with a new subsonic flame spraying possess high bonding strength , low porosity and is low costly , at the same time , it is applied to the worksite of boiler tubes specially . the coatings applied to water wall tubes were deposited by subsonic flame spraying in this study 本課題采用了一種新型亞音速火焰噴涂技術制備鍋爐水冷壁管道涂層，其涂層不僅結合強度高、孔隙率較低，而且涂層制備的成本低，特別適用于鍋爐水冷壁管的現場噴涂。

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，并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。

A requires all subsonic narrow - bodied jet aircraft flying in and out of hong kong to meet with the most stringent international noise standard ; and requires all subsonic jet aircraft taking off or landing in hong kong to be certificated in accordance with international established procedures A規定所有亞音速狹體噴射機必須符合最嚴格的國際噪音標準，方可在香港升降及b規定所有亞音速噴射機必須遵照國際民航公約規定程序領取證明書，方可在香港升降。

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、支板背壁回流區、二次流流動區以及發動機后部膨脹區，并確定了各區域準確劃分的原則。

On the base of the numerical simulation of unsteady viscous flows , the characters of the static aeroelastics and flutter for the wings are researched . some examples , simulating the steady and unsteady transonic ( and subsonic ) viscous flows around onera m6 wing , are given in this paper 以oneram6機翼為算例，分別對其亞、跨音速定常及非定常粘性繞流狀態進行了數值模擬，并運用b - l和j - k兩種湍流模型計算結果和實驗數據進行了對比。

With effect from 1 july 2002 , all chapter 2 subsonic jet aircraft as defined in part ii , volume i , annex 16 of the convention on international civil aviation , which only meet less stringent noise standards , are banned from landing and taking - off at the hong kong international airport 從2002年7月1日起，全面禁止噪音較強，屬于國際民航公約附件16卷1第2部第2章所界定的亞音速噴射飛機在香港國際機場升降。

Simulation results presented here demonstrate that during accelerating flight at constant altitude thrust increases up to approximately 12 percent in the maximum thrust mode , and at subsonic cruise specific fuel consumption decreases up to 2 percent in the minimum fuel consumption mode 試驗結果表明兩種優化模式下，飛推綜合控制的優化算法可以顯著提高發動機性能，也驗證了該優化計算機設計方案是可行的。