Nonlinear turbulence models in shock boundary - layer interaction 邊界層相互作用的非線性湍流模式
Numerical simulation of two - dimensional shock boundary - layer interaction between a rocket and booster 助推器附近二維激波邊界層干擾的數(shù)值分析
The computed results compared favorably with measurements and the corresponding shock boundary - layer interaction and energy loose during transonic speed was described 以尋找出葉片對能量轉(zhuǎn)換過程中,因氣動力原因而造成能量損失的原因,進而提供改良建議。
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(guān)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(guān)系,以及流體黏滯性等影響下,引擎能量損失與效益分析。