سال انتشار: ۱۳۸۹
محل انتشار: دهمین همایش انجمن هوافضای ایران
تعداد صفحات: ۴
A Imani – Iran University of Science & Technology, Tehran, Iran
J Pirkandi – K. N. Toosi University of Technology, Tehran, Iran
M.H Roozbahani – Iran University of Science & Technology, Tehran, Iran
The U.S. Air Force Missile DATCOM (97 version) is widely used aerodynamic prediction code. This code predicts aerodynamic forces, moments, and stability derivatives as a function of angle of attack and Mach number for a wide range of axisymmetric and nonaxisymmetric missile configurations. The body configurations in this study include axisymmetric body without wing tail or body tail. This present article describes a two dimensional numerical investigation of subsonic, transonic and supersonic flow regimes around a body in ten different angles of attack with two methods. The Missile Datcom code (MD) is used as a Rapid Prediction code for solving the Compressible Flow. Studies were performing at 0.6, 1 and 1.5 Mach number. At the same conditions the body has been modeled in commercial computations fluid dynamics code –Fluent6.3- with k-ω turbulence model. A structured mesh was adopted to map the flow domain around of body. A finite volume approach has been used and the pressure–velocity coupling is resolved using the SIMPLE algorithm. Lift and drag coefficients of MD solution are compared with the Fluent solution and good trend are obtained. But in the transonic condition – mach 1- the error of result is higher. Based on the results obtained, the MD is better than fluent for this type of studies with significant saving in computational cost, time and simple in operations.