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transonic

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transonic adj.＝transsonic.

adj. ＝transsonic. “aerodynamics; transonic“ 中文翻譯：   穿音速空氣動力學“aircraft; transonic“ 中文翻譯：   穿音速飛機“airfoil; transonic“ 中文翻譯：   穿音速翼形“all transonic“ 中文翻譯：   純跨音速的“all-transonic“ 中文翻譯：   純跨音速的“bump; transonic“ 中文翻譯：   穿音速突起“flow，transonic“ 中文翻譯：   穿音速流動“speed; transonic“ 中文翻譯：   跨音速“transonic acceleration“ 中文翻譯：   跨音速(時的)加速度; 跨音速加速度“transonic aerodynamics“ 中文翻譯：   跨聲速空氣動力學; 跨音速空氣動力學“transonic aircraft“ 中文翻譯：   跨音速飛機“transonic airfoil“ 中文翻譯：   跨音速翼型“transonic barrier“ 中文翻譯：   音障“transonic bomber“ 中文翻譯：   跨音速轟炸機“transonic buffeting“ 中文翻譯：   跨音速抖振“transonic bump“ 中文翻譯：   跨音速型塊“transonic cascade“ 中文翻譯：   跨聲速葉柵“transonic characteristics“ 中文翻譯：   跨音速特性“transonic combat“ 中文翻譯：   跨音速戰斗“transonic compression“ 中文翻譯：   聲速壓縮“transonic compressor“ 中文翻譯：   跨聲速壓氣機; 跨音速壓氣機; 跨音速壓縮器“transonic control“ 中文翻譯：   跨音速操縱“transonic deceleration“ 中文翻譯：   跨音速減速“transonic-supersonic“ 中文翻譯：   跨超音速的; 跨音速到超音速的“transome“ 中文翻譯：   橫檔“transom, transom window“ 中文翻譯：   氣窗

transpacific

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。

Based on an engineering background , through numerical simulation of the flow field in the hp turbine of the energy efficient engine ( e3 ) , the article research the unsteady flow in a transonic turbine stage , the unsteady phenomena in the stage include the shockwave , wake , shedding vortex , endwall vortex , passage vortex and leakage vortex , etc . there are two shockwaves generated on the vane the tailing edge , one on suction side is named moving shockwave , and name another on pressure side steady shockwave 本文首先對于研究的意義和國內外研究的現狀做了簡要的介紹，再從某工程背景出發，通過對e3發動機高壓渦輪內流場的數值模擬，研究了干涉的周期性的問題，以及渦輪級內常見的非定常現象：激波、尾跡、脫落渦、根腳渦、通道渦、漏流渦。導向器尾緣會出現兩道激波，在吸力面的激波可稱為“運動”激波，壓力面的激波可稱為“定常”激波。

Accurate calculation of aircraft steady and unsteady aerodynamics and flutter characteristics , especially in the transonic speed range is a crucial problem for aircraft designers . it is very important for us to develop an efficient , accurate , robust navier - stokes / euler flow solver that could be used to study transonic steady and unsteady flowfields 飛行器的定常和非定常氣動力的準確數值求解及顫振特性研究，特別是跨音速范圍內的準確數值求解及研究，一直以來都是飛行器設計工作者必須面對的重要研究難題。

The flowfield over low - drag and long - range projectile with small attack angle is numerically studied from transonic to supersonic velocity . it provides basic work for aerodynamics characteristic of this projectile and for lateral jet interaction flowfield , and it shows this projectile can decrease drag . zonal method is tried to compute flow over projectiles and results is satisfied , but computation is much slower 系統研究了低阻遠程彈丸在小攻角狀態，低跨聲速、高跨聲速和超聲速時的非對稱繞流流場，為該彈形氣動力研究提供理論指導并為彈丸側噴流研究奠定基礎，結果顯示低阻遠程彈丸外形具有優化繞流場、減小空氣阻力的特點。

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 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。

The cfd code used to simulate the fluid field is the commercial software fluent . through the numerical simulation , it can make a qualitative looking of unsteady flow in a transonic turbine stage and the numerical result can be a valuable result to the following research 本次數值模擬使用的是商業計算流體力學軟件fluent ，通過數值模擬，最終能夠對整個流場有定性的說明，同時對一些特定的流動現象能夠較好的模擬出來，為以后的進一步研究提供參考。

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。

For unsteady - state calculations , jameson ' s dual - time method is used . to confirm the validity , effectivity and reliability of developed flow solvers based on ausm + scheme , test cases of steady / unsteady transonic flow of naca0012 airfoil and onera m6 wings are investigated first 本文首先以naca0012翼型、 oneram6機翼為算例，驗證了本文發展的基于ausm +格式的跨音速定常、非定常navier - stokes euler方程解算器是正確、有效和可靠的。

High - resolution nnd scheme and fully implicit dual - time stepping method were adopted in the three - dimensional vibrating cascade flow calculation . thus , the correct simulation of the shock in transonic flow and the efficiency of calculation were both taken into consideration 在三維振動葉柵流動數值模擬中，采用高分辨率tvd類型的格式和全隱式雙時間方法，保證了對流動的正確模擬，準確地捕捉了跨音流動中的激波，其計算效率非常高。

In this paper based on the optimization design method using control theory for airfoils , a design method for multi - element airfoils is developed with the chimera grids . and optimization computation for reducing drag of shockwave of single airfoil in transonic flow is also successful 本文的主要工作是：以在控制理論進行單段翼型優化設計的基礎上，利用嵌套網格技術將其發展為適用于帶襟翼多段翼型的優化設計。

This deforming method coupled with ale euler solver is applied to simulate unsteady transonic flow about oscillating airfoil ( 2 - d ) and oscillating rigid rectangular wing ( 3 - d ) . computational results are in good agreement with experimental data 本文將網格變形方法與數值解算器耦合起來求解了二維振動翼型繞流和三維振動矩形機翼繞流，計算結果與實驗結果一致，證明本文的數值方法具有較高的準確性。

The propose of this project is to develop a three - dimensional , compressible navier - stokes solver for detailed study the flow inside transonic turbine and compressor ' s stator in the airplane turbomachinery 摘要本研究的目的在發展一系列飛機滑輪引擎之靜子葉片的計算流體力學方法與程式，計算程式方面包括三維葉片格點的建立與黏性流程式開發及撰寫等，程式發展完成后將進行一系列外形及氣流條件計算模擬。

The calculation of the37 # transonic compressor rotor shows that the simulation results of the author ' s multi - grid scheme fit fairly well with those of professor denton j . d . ' s , however , the author ' s converging speed is faster 與nasarotor37的計算結果對比表明，本文多重網格算法的計算結果與dentonj . d .的計算結果十分接近，而在提高計算效率方面比dentonj . d的多重網格算法更加有效。

Furthermore , numerical simulations for steady or unsteady transonic flow of rae2822 and dfvlr - r2 supercritical airfoils and a supercritical wings are investigated . the numerical results are in good agreement with experimental data where available 進而，應用該解算器對超臨界翼型rae2822 、 dfvlr - r2及某超臨界機翼的定常或非定常流場進行了數值計算研究，得出了良好、合理的結論。

2 . the transonic flow field solutions of a ttcp standard waf - body combinations are computed using the software of cfd , the results are agreement with experiment dates , this verifies that the accuracy of the numerical simulation model is ensured 2 .應用cfd軟件對某ttcp標準卷弧翼-身組合體跨聲速下流場進行數值計算,將計算結果與文獻試驗結果進行對比,驗證本文數值計算模型。

In this study , the transonic shock - wave / boundary - layer interaction and viscous shear stress for the turbine and compressor stator were simulated used the implicit two - factor flux - splitting schemes for solving the thin - layer compressible flow 除驗證各式正確性外并模擬葉片外形對氣流分離、震波/邊界層相互干擾及壓縮比等關系，以及流體黏滯性等影響下，引擎能量損失與效益分析。

In this study , the transonic shock - wave / boundary - layer interaction and viscous shear stress for the turbine and compressor stator were simulated used the implicit two - factor flux - splitting schemes for solving the thin - layer compressible flow 除驗證各式正確性外并仿真葉片外形對氣流分離、震波/邊界層相互干擾及壓縮比等關系，以及流體黏滯性等影響下，引擎能量損失與效益分析。