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Results of tests on a 0.04 scale Space Shuttle Orbiter forebody model (83-0) in the AEDC VKF hypersonic wind tunnel B to obtain aerodynamic heating distribution on lower fuselage and RCS nozzle area (OH103A)

机译：在aEDC VKF高超音速风洞B中对0.04比例的航天飞机轨道飞行器前体模型（83-0）进行测试的结果，以获得机身下部和RCs喷嘴区域的空气动力学热分布（OH103a）

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Lemoine, P. L.; Nakamoto, J. R.;
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年度 1982
页码 1-410
总页数 410
原文格式 PDF
正文语种 eng
中图分类工业技术;
关键词
AEROTHERMODYNAMICS; HYPERSONIC WIND TUNNELS; SCALE MODELS; SPACE SHUTTLE ORBITERS; WIND TUNNEL TESTS; AERODYNAMIC HEATING; FUSELAGES; HYPERSONIC SPEED; ROCKET NOZZLES; TABLES (DATA);

机译：气动热力学;超级风洞;尺度模型; spaCE sHUTTLE ORBITERs;风洞隧道测试;空气动力加热;机身;超速的;火箭喷嘴;表（数据）;

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2. Pyrotechnic approach to space debris destruction: From thermal modeling to hypersonic wind tunnel tests [J] . Monogarov K. A., Melnikov I. N., Drozdov S. M., Acta astronautica . 2020,第Jula期

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3. Feasibility investigation of large-scale model suspended by cable-driven parallel robot in hypersonic wind tunnel test [J] . Wang Xiaoguang, Peng Miaojiao, Hu Zhenghong, Proceedings of the Institution of Mechanical Engineers . 2017,第G13期

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4. Estimation of the Unsteady Aerodynamic Load on Space Shuttle External Tank Protuberances from a Component Wind Tunnel Test [C] . J. Panda, F. Martin, D. Sutcliff AIAA Aerospace Sciences Meeting and Exhibit . 2008

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5. Comparison of the Results of Hypersonic Numerical Simulation about a Space Plane and Its Force, Pressure and Aerodynamic Heating Measurement at a Hypersonic Wind Tunnel. [O] . Tadashi KATSURAHARA, Masahiro NAKAO, Yukimitsu YAMAMOTO, 1993

机译：超声波风隧道对空间平面及其力，压力和空气动力学测量的超声数值模拟结果的比较。
6. VOLUME 2 OF 3 TEST RESULTS FROM THE NASA/ROCKWELL INTERNATIONAL SPACE SHUTTLE 0.0175-SCALE ORBITER MODELS 56-0/60-0 AND 0.04-SCALE ORBITER FOREBODY MODEL 83-0 CONDUCTED IN THE AEDC/VKF-Bn50-INCH HYPERSONIC WIND TUNNEL (TESTS OH109 AND OH109B) [R] . J. Gee, J. Nakamoto 1982

机译：2卷3个测试结果进行FROm IN THE aEDC / VKF-Bn50英寸高超声速风洞Nasa / ROCKWELL INTERNaTIONaL航天飞机0.0175尺度ORBITER模型56-0 / 60-0和0.04尺度ORBITER船首mODEL 83-0（测试OH109和OH109B）

Results of tests on a 0.04 scale Space Shuttle Orbiter forebody model (83-0) in the AEDC VKF hypersonic wind tunnel B to obtain aerodynamic heating distribution on lower fuselage and RCS nozzle area (OH103A)

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