超作用翼 的英文怎麼說
中文拼音 [chāozuòyòngyì]
超作用翼
英文
deployed foil-
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，並在此基礎上研究了彈性機翼的氣動彈性問題。This dissertation presents how to use the ultrasonic motor as an actuator to suppress the flutter of a two - dimensional airfoil section with a control surface. the ultrasonic motor, which features simple structure, high torque at low speed, small size, low weight and no electromagnetic contamination, is a promising actuator for the flutter suppression of small aircraft
超聲電機以其結構簡單緊湊、轉矩/質量比大、低速大扭矩、直接驅動，動態響應快、斷電自鎖和不產生磁場且不受外界磁場干擾等優點，有望成為一種非常有前途的作動器，用於小型飛機的機翼顫振主動抑制。The main work in this paper includes three parts : the theory research on partially - cavitating and super - cavitating axisymmetric bodies, the numerical computations and experimental investigations on partially - cavitation and super - cavitation on axisymmetric bodies. after finishing the study of theory and experiment on the partially - cavitation and super - cavitation for axisymmetric body, i use the potential flow theory to build the mathematical model on the partially - cavitation and super - cavitation for axisymmetric body. many cavity wake models, such as pressure recovery close model, riabouchinsky model and re - entrant jet model, are studied seriously
本文在深入研究了回轉體局部空化與超空化理論及實驗結果的基礎上，基於勢流理論，建立了回轉體局部空泡和超空泡流場的基本數學模型，通過對kinnas和fine 、 uhlman以及jiedang和gertkuiper等人基於二維水翼提出的壓力恢復閉合模型、鏡像板模型和回射流模型等空泡尾流模型進行了逐一的研究分析，發現其中的壓力恢復閉合模型較適用於模擬回轉體空泡尾部流場，並選用此空泡尾流模型作為求解回轉體空化流場正問題與逆問題的數學模型的組成部分。The investigation in this dissertation shows the capabilities of ausm + scheme, such as the exact resolution of shock, low numerical dissipation, simple and requiring less computational effort. the successful applications on supercritical airfoils and wings show that the present flow solvers based on ausm + scheme are of valuable and promising in practical application
通過本文的研究工作，展示了ausm +格式的激波高解析度、數值耗散小、編程簡潔、計算量較小等特性，同時，將其成功地應用於跨音速超臨界翼型、機翼的定常或非定常氣動特性的數值模擬和顫振研究中，具有一定的工程應用價值和良好的發展前景。分享友人