登入選單
返回Google圖書搜尋
A Program for Computing Steady Inviscid Three-dimensional Supersonic Flow on Reentry Vehicles
J. M. SolomonM. CimentR. E. FergusonJ. B. BellA. B Wardlaw (Jr)
其他書名
Volume I : Analysis and Programming
出版Naval Surface Weapons Center, White Oak Laboratory, 1977
URLhttp://books.google.com.hk/books?id=Ui2Dg5qU78UC&hl=&source=gbs_api
EBookFULL_PUBLIC_DOMAIN
註釋A comprehensive computational procedure is presented for predicting the supersonic region of the flow field on advanced reentry vehicle shapes in steady flight at pitch and yaw. The procedure utilizes explicit second order accurate finite difference methods applied to the conservation law form of the steady inviscid flow equations. Improved numerical methods are used at the body surface and the bow shock wave. Provisions for treating body geometries with discontinuous slopes are also included. Either perfect gas or real gas equilibrium thermodynamic properties can be used. The computational procedure is implemented as a FORTRAN computer code which provides a practicable representation of the inviscid flow field and the resulting aerodynamic force and moment on the vehicle. In this report (Vol. I) the analytical and numerical development of the procedure is presented and the associated computer code is described. A comparison report (Vol. II User's Manual) contains detailed instructions for operating the code and interpreting the output results. (Author).