سال انتشار: ۱۳۸۹

محل انتشار: دهمین همایش انجمن هوافضای ایران

تعداد صفحات: ۲

نویسنده(ها):

Akbar Andalib – PreceptorQadr Aerodynamics Research Center, Imam Hussein University
Fata Mohammadi Fard – MSc. Aerospace, space engineering
Mahdi Karami – Student of PhD., Mechanical engineering
Mohammad Reza Heidari4 – Associate professor, Islamic Azad University

چکیده:

This research has been made in Qadr aerodynamics research center towards designing and manufacturing a laboratory hypersonic wind tunnel. In this article by using the geometry for nozzle, test section and diffuser which their geometries extracted before, and using HB-2 as a standard model, the CFD simulation has been made. The model has the 1% stockade to the nozzle exit area and has zero angle of attack. The wind tunnel includes a nozzle which is producing uniform flow at nominal mach 8 and the test section is free jet type. The CFD simulation has been made from beginning of the nozzle to the end of the diffuser for mach8. The CFD simulation is done under these conditions: viscose flow, adiabatic and second order equations. Contours for various properties are extracted and compared to practical results from a hypersonic facility JAXA in japan. In this case the goal is to demonstrate the ability of simulation a hypersonic flow regime for hypersonic wind tunnel. The results show rather good compatibilities and we can claim that good simulation have been made for specific conditions