The state ( or region ) of the operator has the responsibility for the approval of the method used to establish such minima , and for supervising compliance with those rules it may prescribe for the operator as a whole 营运人所属国家或地区对机场最低飞行条件的责任营运人所属国家或地区须负责批核用以确立最低飞行条件的方法，并且有责任监察有关运作规则的整体遵行情况。
In chapter 5 , the uh - 1 model rotor , the model rotor measured in the present work and the helicopter z - 8 rotor are taken as numerical examples , the calculations on rotor noise under different flight conditions are carried out for validation purposes 应用该模型，分别以uh - 1模型旋翼、本文试验的模型旋翼以及z - 8直升机旋翼为算例，对不同飞行条件下的旋翼气动噪声进行了计算，验证了本文的计算方法。
The state ( or region ) of the aerodrome has to provide data such as obstacle clearance altitude height ( oca h ) , details of electronic aids for an approach to landing , etc , to enable an operator to establish aom for each runway intended to be used at that particular aerodrome 机场所属国家或地区须提供资料，例如：超障安全高度、协助进场著陆的电子辅助设备的详细资料等，使营运人能够就某个机场内拟使用的每条跑道确立机场最低飞行条件。
This method not only have the high estimated precise in kinds of maneuvering fly and good robustness to atmosphere turbulence or the change of flight stat , but also have the good ability of real - time . this paper also gives a project for the engineering application . 4 对上面两种方法在带有大气紊流和阵风影响的飞行环境下，特别是针对第四代飞机中典型的超大迎角飞行过程进行了详细仿真计算验证，证明这两种方法能够在不同飞行条件下均具有很好的估计效果。
Thirdly , this dissertation briefly introduces the engineering estimation method of the aerodynamic heat and supplies the simplified formulas . not considering the rejection , the ablation and some other factors , the author calculates the stagnation heat flux and the non - stagnation field heat flux distribution of some fly situation as the example aerodynamic heat environment . finally , by using the ansys program , the thermal vibration characters of the plate and missile body structures with different materials is analyzed 这一方法提高了热振动的分析效率；第三，简要的介绍了工程上计算气动熟的估算方法及热流密度计算的简化公式，在不考虑烧蚀以及质量引射等影响下，本文计算了几种飞行条件下驻点和非驻点区的热流密度分布，作为本论文算例的气动加热环境。
The optimized shape in the parameter range was obtained . in order to studied the lightcraft ’ s flight performance , the 3 - d lightcraft aerodynamic performance research at different altitudes , velocity and angle of attack were simulated . in subsonic situation , the drag coefficient was reducing with the angle of attack increasing , but in supersonic situation , the drag coefficient was increasing with the angle of attack increasing 分析了激光推进技术的基本原理及其特点,对光船的气动性能进行了数值模拟,在流场分析的基础上,对光船的头部外形进行了优化,并给出了参数变化范围内的优化外形;为了进一步研究光船的飞行性能,对不同高度、不同速度和不同攻角等飞行条件下的三维光船气动性能进行了数值研究,研究表明:在亚声速情况下,阻力系数随攻角的增大而减小;超声速情况下,阻力系数随攻角增大而增大。
The effects of such elements as primary flow total pressure , flow rate , degree of fuel rich , nozzle structure , flying speed and secondary combustion on ejecting mode performance were researched . it was found that thrust augmentation can be achieved on the condition that the flying mach number is above 0 . 7 . to deeply analyze thrust augmentation mechanism in low speed range , the research was further continued by changing secondary combustion organization and aft - body configuration 研究了一次流总压、流量、富燃程度、喷管结构、二次流来流速度、二次燃烧组织对引射模态性能的影响，发现实验样机构型在0 . 7ma以上的飞行条件下可以获得推力增强，而在0 . 7ma以下无推力增强。
