1.
A NEW TRANSITION/TURBULENCE MODEL FOR THE FLOW TRANSITION IN SUPERSONIC BOUNDARY LAYER
一种适用于超音速边界层的湍流转捩模式
2.
A Numerical Study for the Generation of Shocklet by 3-D Disturbance in Supersonic Boundary Layer;
超音速边界层中三维扰动引起小激波的数值研究
3.
The Study of Receptivity of Supersonic Boundary-layer to Local Periodic Disturbance in Free-stream;
超音速边界层对自由流中空间局部周期扰动感受性问题的研究
4.
A Numerical Study for the Resonant Triad Interaction and Secondary Instability in a Three-dimensional Supersonic Boundary Layer;
三维超音速边界层中三波共振和二次失稳机制的数值模拟研究
5.
A Numerical Study of the Evolution of the Disturbance in 2-D Supersonic Boundary Layer with Pressure Gradient;
具有压力梯度的二维超音速边界层扰动演化的数值模拟研究
6.
A Numerical Study of the Evolution of Perturbations in Hypersonic Flat Plate Boundary Layer at High Altitude;
高空高超音速平板边界层扰动演化的数值研究
7.
The Numerical Study of Evolution of Perturbations in the Supersonic Blunted Cone Boundary Layer Flow;
高超音速钝锥边界层中扰动演化的数值研究
8.
The Mechanism of Laminar-turbulent Transition and the Characteristics of Turbulence in a Supersonic Boundary Layer on a Flat Plate;
超音速平板边界层从层流到湍流的转捩机理及湍流特性
9.
Experimental Investigations of Hypersonic Boundary Layer Transition on a Sharp Cone Based on the Method of Wavelet Analysis;
基于小波分析方法的高超音速尖锥边界层转捩的实验研究
10.
The Effects of Thermophysical Parameters of Air on the Stability of Two-dimensional Supersonic Boundary Layer on a Flat Plate
热物性参数对超音速平板边界层稳定性影响研究
11.
Using Roughness Surface on Control of Supersonic Laminar Flow Boundary Layer
用表面粗糙度控制超声速层流边界层
12.
A study of the boundary condition in the DNS of the supersonic boundary layer flow
超声速边界层流动数值模拟的边界条件研究
13.
Stability Characteristics of the Boundary Layer of an Axisymmetric Blunt Nosed Cone in the Supersonic and Hypersonic Flow
超声速高超声速球锥绕流的边界层稳定性特点初探
14.
Analysis of dynamic images based on wavelet transform in a hypersonic boundary layer
基于小波变换的高超声速边界层动态图像分析
15.
Weak Nonlinear Evolution of Small Amplitude Disturbances in 2D Supersonic Boundary Layer
小扰动在二维超声速边界层中的弱非线性传播
16.
Examination of the application of BL model in supersonic turbulent boundary layers
BL模式在超声速湍流边界层中应用的检验
17.
Performance and boundary layer of flow in axisymmetric mixed-compression supersonic inlet with cavity
槽对超声速混压式进气道性能及边界层的影响
18.
It is also shown that the analytical solution to the case for hypersonic flow over a blunt nose body with smooth boundary is possible.
文中还指出了对高超音速绕流光滑边界问题解析求解是可能的。