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- The unsteady transonic flows around a pitching slender delta wing are simulated numerically with solving unsteady compressible Navier-Stokes equations by implicit finite difference TVD scheme. 用有限差分法求解N-S方程，數值模擬了細長(cháng)三角翼作勻速上仰運動(dòng)時(shí)的跨聲速繞流流場(chǎng)。
- AN IMPLICIT DIFFERENCE SCHEME OF EULER EQUATION FOR UNSTEADY TRANSONIC FLOW 跨音速非定常流動(dòng)的Euler方程隱式解
- NUMERICAL METHOD FOR SOLVING THE EULER EQUATION FOR UNSTEADY TRANSONIC FLOWS OVER OSCILLATING AIRFOILSS North-western Polytechnical University 振動(dòng)翼型跨音速非定常Euler方程數值解方法
- In order to save expense and calculating time,we apply first-order approximate conditions to solve the unsteady transonic Euler equations coupled with aeroelastic equations. 計算網(wǎng)格采用靜止的笛卡兒網(wǎng)格,通過(guò)薄翼和機翼小變形假設,使用一階近似邊界條件求解歐拉方程;由于文中方法在計算過(guò)程中不需要重新生成網(wǎng)格,節省了大量的時(shí)間。
- Jameson A. Transonic flow calculation [C]. MAE Report 1651,Prinston University. 傅德薰.;計算空氣動(dòng)力學(xué)
- Then the steady and unsteady transonic viscous flows are numerically simulated. The three-dimensional unsteady Navier-Stokes equations are solved by using the implicit LU-NND algorithm, with Baldwin-Lomax turbulent model. 從三維非定常Navier-Stokes方程組出發(fā),采用LU-NND有限差分格式和Baldwin-Lomax湍流模型建立了一種數值模擬三維機翼、組合體和T型尾翼的跨音速定常及非定常粘性繞流的計算方法和程序。
- The drag of aftbody keeps constant in low subsonic flow, but increases in transonic flow due to the shock wave. 在低亞音速范圍，后 體阻力基本不變化，隨著(zhù)馬赫數增加至跨音速，出現激波阻力。
- Using direct coupling some results of viscous/inviscid interaction are given in both incompressible and transonic flow. 給出了不可壓流動(dòng)和跨音速流動(dòng)中粘流/無(wú)粘流相互作用的某些正耦合的計算結果。
- A new and versatile algorithm for computing two-dimensional transonic flow using orthogonal stream-lines grids (SLG) has been developed. 本文給出了一種比較新型而通用的計算二維跨音速流動(dòng)的數值算法 --正交流線(xiàn)網(wǎng)格法（SLG）。
- In transonic flow, a simple empirical formulation is given to predict the wave drag of upswept aftbody, which extends the usable range of Mach number. 在跨音速范圍，給出了一種簡(jiǎn) 單的上翹后體波阻的估算方法，拓寬了馬赫數的適用范圍。
- Using the improved method we studied inviscid and viscous transonic flow in turbomachinery based on Euler and Navier Stokes equations. 計算結果表明，本方法是透平機械內部跨音速流動(dòng)計算的強有力的手段。
- An effective multigrid method has been developed to accelerate the Euler solution of transonic flow for a helicopter rotor in hover. 發(fā)展了一種加快懸停旋翼無(wú)粘流場(chǎng)計算收斂速度的多重網(wǎng)格方法。
- Witcomb notes that "you could write lots of equations for subsonic flow and lots for supersonic flow, but for transonic flow things got so complicated that nobody could write any equations for it. 惠特科姆指出，“人們能夠寫(xiě)出許多關(guān)于亞聲速流動(dòng)的方程，寫(xiě)出許多關(guān)于超聲速流動(dòng)的方程，但是，對于跨聲速流動(dòng)，由于情況極其復雜，當時(shí)還沒(méi)有人能夠寫(xiě)出有關(guān)跨聲速流動(dòng)的任何形式的方程。
- As examples, an quasi-one-dimensional nozzle flow with shock and the subsonic and transonic flow about NACA-0012 and NACA64A-10 airfoils are calculated. The results are compared with the experimental data and the other computed results. 文中分別對一維管流,二維繞NACA-0012和NACA64A-10翼型在亞聲速和超聲速來(lái)流的跨聲速流場(chǎng)進(jìn)行了計算,并將所得結果與有關(guān)實(shí)驗和計算結果進(jìn)行了比較,均符合良好。
- The theory of S1 and S2 stream surface was applied to calculate and analyze the internal transonic flow field for a two-stage axial turbine used in turbopump for liquid rocket engine. 摘要應用S1,S2流面理論對某大型液氫／液氧火箭發(fā)動(dòng)機渦輪泵的兩級軸流式渦輪內部跨聲速流場(chǎng)進(jìn)行計算和分析。
- In this paper, the adaptive parallel Multigrid algorithm is applied in solving transonic flow equation with large disturbance in the axial direction and small disturbance in the transverse direction. 本文運用自適應并行多重網(wǎng)格法求解了軸向大擾動(dòng)、徑向小擾動(dòng)的跨音速方程。
- As validated in the present work in a number of transonic flows this method showed very promising performance. 本文對全速解法在二維層流的計算效果進(jìn)行了考核,而后又將此算法在湍流跨音速流動(dòng)中應用。
- The applications as carried out by DLR range from low speed flows to transonic flows, from high lift configurations to propellers and rotor. 德國宇航研究院)對這些技術(shù)的應用包括從低速流到跨聲速流、從增升裝置到螺旋槳和旋翼、從彈射裝置和水塔儲水罐尾跡流旋渦到三角翼上渦破裂現象等的研究。
- The present thesis summarizes the author's work on the shock wave/boundary layer inferaction phenomena and the associated passive controls in transonic flows. 本文作者對跨音速流動(dòng)中的激波/邊界層相互干擾及其控制進(jìn)行了研 究。
- Traditional gust responses are mainly analyzed based on linear aerodynamic load calculations in frequency-domain,which is unsuitable for and the viscous and transonic flows. 傳統的陣風(fēng)響應主要在頻域內進(jìn)行分析,氣動(dòng)載荷基于線(xiàn)性方法計算,不能考慮黏性和跨聲速流動(dòng)影響。
