by National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, For sale by the National Technical Information Service] in [Washington, DC], [Springfield, Va .
Written in English
|Other titles||Improved tangent cone method for the Aerodynamic Preliminary Analysis System (APAS) version of the hypersonic arbitrary-body program.|
|Statement||Christopher I. Cruz, Gregory J. Sova.|
|Series||NASA technical memorandum -- 4165.|
|Contributions||Sova, Gregory J., United States. National Aeronautics and Space Administration. Scientific and Technical Information Division.|
|The Physical Object|
Aerodynamic characteristics, including effect of body shape, of a Mach 6 aircraft concept [microform] / Aerodynamic heating rate distributions induced by trailing edge controls on hypersonic aircraft configur Improved tangent-cone method for the Aerodynamic Preliminary Analysis System (APAS) version of . This work examines the ability of the aerodynamic analysis methods contained in an industry standard conceptual design code, the Aerodynamic Preliminary Analysis System, to estimate the forces and. Continuous Aerodynamic Modelling of Entry Shapes. This paper describes the model of an aerodynamic analysis code, written for use in conceptual vehicle shape optimization, which includes an. SPREAD tool has been used to perform the nose-to-tail analysis of the LAPCAT-II Mach 8 MR vehicle configuration. The numerical results demonstrate SPREAD capability to quickly predict reliable values of aero-propulsive balance (i.e., net-thrust) and aerodynamic efficiency in a pre-design chevreschevalaosta.com by: 5.
The actual design process of the HCV clean configuration is driven by an optimization system. The optimization system has three main subsystems, namely: the parametric modelling system via the patched CST method, the hypersonic aerodynamic rapid prediction method (HARPM), and an improved genetic algorithm (GA).Cited by: 3. The combined tangent cone/tangent wedge theory (tangent cone for the fuselage and tangent wedge for the wing and tail) gave the least accurate prediction of lift and pitching moment. For all theories, the zero lift drag was overestimated especially for M tangent cone method predicted5/5(1). NASA Images Solar System Collection Ames Research Center. Brooklyn Museum. Full text of "DTIC ADA The Version of the NSWC Aeroprediction Code: Part I . A study of engine-nozzle airframe inte- gration at hypersonic speeds has been conducted by using a high-speed research- aircraft concept as a focus. Recently developed techniques for analysis of scramjet-nozzle exhaust flows provide a realistic analysis of complex forces resulting from the engine-nozzle airframe coupling.
McCandless and Cruz 33 used such techniques to compute the pressures acting on an advanced aerospace plane (see Fig. ). "Modified Newtonian theory was used for the nose region and the leading edge areas of the vehicle, and the tangent-cone method was applied to the top, wedge sides, and bottom ramp impact surfaces. For the shadow regions. book of abstracts may budapest hungary organized by partners iii international conference on engineering and natural sciences (icens) isbn book of abstracts of the iii international conference on engineering and natural sciences (icens) may , budapest. Large-Scale Nonlinear Optimization Gianni Pillo, Massimo Roma This book reviews and discusses recent advances in the development of methods and algorithms for nonlinear optimization and its applications, focusing on the large-dimensional case, the current forefront of much research. Neither this book nor any part may be reproduced or transmitted in any form or by any means, electronic or mechanical, including photocopying, microfilming, and recording, or by any information storage and retrieval system, without permission in writing from the publisher. Current printing (last digit): 10 9 .