本文選題：高超聲速空氣動力學(xué) + 完全氣體��； 參考：《戰(zhàn)術(shù)導(dǎo)彈技術(shù)》2017年05期

【摘要】：為了驗證牛頓流理論的效度,在高超聲速高溫氣體效應(yīng)下設(shè)計驗證模型,對比牛頓流理論解析解和數(shù)值模擬結(jié)果,證明牛頓流理論在高溫氣體效應(yīng)下仍然具有相當(dāng)高的效度。研究表明完全氣體模式下的牛頓理論仍然可以移植到高溫氣體情形下,在高溫氣體效應(yīng)下為飛行器設(shè)計提供前期的概念指導(dǎo)。
[Abstract]:In order to verify the validity of Newtonian flow theory, a validation model was designed under hypersonic and high-temperature gas effects. Compared with the analytical solution of Newtonian flow theory and numerical simulation results, it is proved that Newtonian flow theory still has high validity under high temperature gas effect. It is shown that Newtonian theory in complete gas mode can still be transplanted to the case of high temperature gas, and it can provide conceptual guidance for aircraft design in the case of high temperature gas effect.
【作者單位】： 國防科技大學(xué)航天科學(xué)與工程學(xué)院;
【分類號】：V211
，

本文編號：2046944