搜索资源列表
bpm
- BPM_free_space.m - Propagation of a gaussian pulse in free space BPM_free_space.m - 传播的高斯脉冲在自由空间 BPM_triangle.m - Propagation of a gaussian pulse in a triangle index profile waveguide BPM_triangle.m - 传播中的一个三角形折射率分布波导高斯脉冲 BPM_2step.m - Demons
weno-codes
- weno code, 计算经典的双马赫数反射的问题-WENO code double mach refelct
ch5soft
- These codes require an ASCII input file called input.dat of the following form: Lower Limit on x Upper Limit on x Final Time Pressure for x<0 when t=0 Density for x<0 when t=0 Speed for x<0 when t=0 Pressure for x>0 when t=0 D
sup.vec.mach
- 这里上载的是一个支持向量机算法程序，欢迎使用，欢迎评定。-support vector machine program
Aero_spin
- spin of rotating body at mach more than 5
DistributedFilberOpticSensorSystem
- 本文基于马赫-泽德干涉结构的分布式光纤传感系统，采用模式识别的思想，详细论述了信号特征辨识和提取方法，提高了定位准确度，减少了误报！-Based on Mach- Zehnder interferometer structure of the distributed optical fiber sensing system, using pattern recognition idea, discussed in detail the signal feature recognition and
sdfsd
- 一类可压缩流的马赫数极限.A class of compressible flow Mach number limit.-A class of compressible flow Mach number limit.
w
- CFD经典算例：双马赫反射，采用五阶WENO格式，可作为测试算例，激波分辨率-CFD classic example: the double Mach reflection，Fifth-order WENO scheme can be used as the test example。Shock resolution
WENOPLFPRK
- 利用5阶有限差分weno结合LF流通量分裂，3阶runge-kutta求解双马赫反射、黎曼问题、界面不稳定性问题-Order finite difference weno combination of LF liquidity split third-order runge-kutta to solve the double-Mach reflection, the Riemann problem for interface instability
k_pohlhausen
- 已知翼型坐标及其各点的马赫数分布用波豪森近似方法求解层流附面层厚度-The known airfoil coordinates of its point of Mach number distribution wave the Stockhausen approximation method for solving laminar flow boundary layer thickness
xie-shock
- 计算二维斜激波各个变量之间的关系，输入波前马赫数，sita,beta之中的任何两个，可以求出压力，密度，马赫数等波后量与波前量的比值-Relationship between the variables of the calculation of two-dimensional oblique shock, out of any two of the Mach number, sita, beta, the input wavefront, which can be determined pre
Flutter
- 这个程序演示了如何应用耦合结构空气动力问题，通过Matlab编程，分析了飞行器机翼颤振等问题。-This model demonstrates how to implement a coupled structural-aerodynamic problem. The wing, otherwise rigid, is allowed to pitch and plunge. The motion of the wing is defined using SimMechanics bloc
SciDAC-June-2005.pdf
- This is a good descr iption of computational effort to simulate turbulent reacitng flows at high mach nunbers and is about 7 years old.
CFD
- 这是一个求解NACA0012翼型在不同马赫数与攻角下的流场的Fortran源代码。计算格式采用了原始AUSM、AUSMDV以及AUSM+格式。为了提高计算精度，使用了不同限制器的MUSCL插值。-This is a Fortran source code for solving the flow field around the NACA0012 airfoil at different Mach numbers and angles of attack. The scheme of AUSM,
aos
- 基于带有环形谐振腔的马赫增德尔干涉仪实现全光比较处理-Comparison of all-optical processing based Mach Zehnder interferometer with a ring resonator
order
- a function that classifies a flow according to the values of its Reynolds (Re) and Mach (Ma) numbers, such that if Re < 2000, the flow is laminar if 2000 < Re < 5000, the flow is transitional if Re > 5000, the flow is turbulent if M
CKLIB
- Reaction mach for fortran
zulixishu
- 使用插值法计算阻力系数，给出不同马赫数下的阻力系数，然后对给定马赫数进行插值-Drag coefficient is calculated using the interpolation method, the drag coefficient is given under different Mach number, and then interpolate a given Mach
mach-synch_bo
- this is model of open loop control of synchronous motor
Task3B
- 安德森的空气动力学大作业。计算扩压器中背压改变引起的流动中马赫数的变化。和激波位置的移动。matlab编。-Anderson s book. Aerodynamic.When back pressure changes, Mach number changes.