首页> 美国政府科技报告 >Data Report of JPL wind tunnel tests of a 0.030-scale Apollo dynamic stability model (FD-1) in the 20-inch supersonic (test no. 20-516) and the 21-inch hypersonic (test no. 21-113) tunnels

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Data Report of JPL wind tunnel tests of a 0.030-scale Apollo dynamic stability model (FD-1) in the 20-inch supersonic (test no. 20-516) and the 21-inch hypersonic (test no. 21-113) tunnels

机译：在20英寸超音速（测试号20-516）和21英寸高超音速（测试号21-113）隧道中的0.030比例apollo动态稳定性模型（FD-1）的JpL风洞试验数据报告

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年度 1963
页码 1-434
总页数 434
原文格式 PDF
正文语种 eng
中图分类工业技术;
关键词
APOLLO SPACECRAFT; WIND TUNNEL MODELS; WIND TUNNEL STABILITY TESTS; HYPERSONIC SPEED; SPACECRAFT PERFORMANCE; SPACECRAFT STABILITY; TEST FACILITIES;

机译：apOLLO spaCECRaFT;风洞模型;风洞稳定性试验;超速的;航天器性能;航天器稳定性;测试设施;

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2. HB-2 high-velocity correlation model at high angles of attack in supersonic wind tunnel tests [J] . Djordje VUKOVIC, Dijana DAMLJANOVIC 中国航空学报（英文版） . 2019,第007期

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3. New Flutter Prediction Method Based on ARMA Model (Part 2) Application to Supersonic Wind Tunnel Flutter Testing [J] . Hiroshi Torii, Yuji Matsuzaki 日本航空宇宙学会論文集 . 2000,第558期

机译：基于ARMA模型的颤振预测新方法（第二部分）在超音速风洞颤振测试中的应用
4. Experimental study of boundary conditions on the perforated walls of test sections no. 1 and 2 of T-128 transonic wind tunnel [C] . S. A. Glazkov, A. R. Gorbushin, A. V. Semenov International Conference on the Methods of Aerophysical Research . 2018

机译：试验部分穿孔壁边界条件的实验研究NO。 T-128跨音隧道的1和2
5. Development and testing of a new optimum design code for hypersonic wind tunnel nozzles, including boundary layer, turbulence, and real gas effects. [D] . Tolle, Ralph Charles. 1995

机译：开发和测试用于超音速风洞喷嘴的新的最佳设计规范，包括边界层，湍流和实际气体效应。
6. Wind Tunnel Tests for Wind Pressure Distribution on Gable Roof Buildings [O] . Xiao-kun Jing, Yuan-qi Li 2013

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7. MAGNUS FORCE TESTS FOR SANDIA CORPORTION, 1971--72. Wind-Tunnel Report No. 59. [O] . W.C. Ragsdale 1972

机译：MAGNUS Force Tests andia Corporation，1971--72。风隧道报告第59号。

Data Report of JPL wind tunnel tests of a 0.030-scale Apollo dynamic stability model (FD-1) in the 20-inch supersonic (test no. 20-516) and the 21-inch hypersonic (test no. 21-113) tunnels

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