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Supersonic and Hypersonic Slender Air-breathing Configurations Derived From 2D Flowfields

机译:Supersonic和Hypersonic细长空气呼吸配置衍生自2D流场

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This research explores the design of supersonic and hypersonic slender air-breating configurations from prescribed Two-Dimensional shock waves. Through the coupled use of the exact solutions of shock waves in an ideal gas, and the exact representations of planar and axisymmetiic geometric shapes, a series of elementary configurations are developed and analyzed. The design process is accomplished through the use of specially developed subroutines, programmed in FORTRAN, to manipulate and assemble these elementary configurations into either completed vehicle configurations or propulsion system configurations, The elementary shapes of interest to this study include the star-shaped leading edges, the caret-shaped inlets, and cylindrical combustors, convergent and divergent nozzles and plug nozzle after-bodies. This paper describes the generation of these elementary shapes, the aerodynamic basis for their creation and the technical requirements used during the final configuration assembly process As part of this effort an existing FORTRAN code is modified and enhanced. As its output, the design code generates the aircraft configuration and analyzes its aerodynamic performance. Further, the algorithms used to evaluate the resulting aero-thermo-dynamic and geometric characteristics of the resulting configurations; such as the local heat fluxes, the lift and drag, the surface areas and the configuration volume, are based on empirical engineering correlations and strict geometric principles. In general, the code developed as part of this research effort was used to conduct the following studies: Generate propulsion systems configurations from prescribed 2-D shock waves; Evaluate the resulting vehicle wetted surface area and volume; Evaluate the thrust performance of the system; Conduct an aero-thermo-dynamic analysis of the resulting system, and; Identify the design parameters that affect the vehicle's overall performance and shape. The outcome of this research can be classified in the following two categories. First, the propulsion system design and assembly process led to the discovery of engineering parameters that directly influence the aerodynamic performance of the resulting configuration. These parameters were manipulated to generate configurations with superior aerodynamic and thrust properties. Second, routines were developed that led to the design and analysis of a morphing ramjet-to-scramjet configuration.
机译:该研究探讨了从规定的二维冲击波的超音速和高超声细长的空气 - 布置配置的设计。通过耦合使用冲击波的精确解,以及平面和轴对称几何形状的精确表示,开发并分析了一系列基本配置。设计过程是通过使用在Fortran中编程的特殊开发的子程序来实现的,以操纵和将这些基本配置进行操纵和组装成完成的车辆配置或推进系统配置,本研究的兴趣的基本形状包括星形前缘,敞篷形入口,圆柱形燃烧器,会聚和发散喷嘴和塞子喷嘴后面。本文介绍了这些基本形状的产生,它们的创建空气动力学依据以及作为本次努力的一部分的最终配置组装过程中使用的技术要求进行了修改和增强了现有的Fortran代码。作为其输出,设计代码会产生飞机配置并分析其空气动力学性能。此外,用于评估所得配置的产生的Aero-Thermo-动态和几何特性的算法;如局部热通量,电梯和拖动,表面区域和配置量,基于经验工程相关性和严格的几何原理。通常,作为本研究努力的一部分开发的代码用于进行以下研究:从规定的2-D冲击波产生推进系统配置;评估所得到的车辆湿润的表面积和体积;评估系统的推力表现;进行所得系统的航空热动力学分析,;确定影响车辆整体性能和形状的设计参数。该研究的结果可以分为以下两类。首先,推进系统设计和装配过程导致了直接影响所得配置的空气动力学性能的工程参数的发现。操纵这些参数以产生具有优异的空气动力学和推力性能的配置。其次,开发了例程,导致了变形式Ramjet-to-scramjet配置的设计和分析。

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