| 1. | Departures form the ideal practice followed by the wright have been particularly noticeable in the development of supersonic and hypersonic vehicles .
特别值得注意的是在发展超音速和高超音速飞行器的过程中，偏离了莱特理想的工作方式。 |
| 2. | A numerical method for hypersonic aerothermoelasticity
一种高超音速热气动弹性数值研究方法 |
| 3. | The computed flutter speeds are within 10 % of experimentally determined ones
并在时间域内分析了高超音速气动弹性的非线性。 |
| 4. | Using local piston theory based on cfd to solve hypersonic unsteady aerodynamic loads , the hypersonic aerothermoelasticity is simulated in time domain
在时间域内实现了高超音速热气动弹性的仿真。 |
| 5. | Cross - section design of a controllable hypersonic inlet . the research is being done at the nanjing university of aeronautics and astronautics
南京航空航天大学正在进行一个可控高超音速进气道断面设计研究。 |
| 6. | With high temperature and high pressure in nozzle of wind tunnel , the effect of variable specific heat on nozzle design must be considered
本文针对超音速、高超音速喷管内马赫数、温度变化剧烈的特点，研究了比热容变化对设计喷管型面产生的影响。 |
| 7. | Using the 3d program , hyten ( hypersonic , throat - ejecting ) nozzle , which is one of the three latest nozzles first designed in this paper , has been simulated
利用建立的三维模拟程序，对本文设计的新喷管? ?喉部引射注入的高超音速喷管( hyten )和光腔进行了数值模拟。 |
| 8. | Using above methods to solve unsteady pressure distribution , coupling structure equations , the supersonic or hypersonic aeroelasticity is simulated in time - domain
运用上述的非定常气动力求解方法，耦合结构动力学方程，实现超音速、高超音速气动弹性的模拟。 |
| 9. | Analyzing existing engineering methods , we combine them in such a way to make computing aerodynamic characteristics possible for arbitrarily shaped body
验证、分析了各种超音速、高超音速气动力工程计算方法，将各种工程方法统一起来，用于求解任意外形的飞行器气动力。 |
| 10. | Employing euler based steady solution and piston theory , a new method ( we call it local piston theory in this paper ) to solve supersonic or hypersonic unsteady loads has been developed
发展了一种运用定常cfd方法和活塞理论求解超音速、高超音速非定常气动力的新方法?当地流活塞理论。 |
