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Variable-Pressure Wind Tunnel Test of Airfoils at Low Reynolds Numbers Designed for Mars Exploration Aircraft

机译：用于火星勘探机设计的低雷诺数翼型的可变压力风隧道试验

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Hirotoshi TSUKAMOTO; Koichi YONEMOTO; Takahiro MAKIZONO; Gaku SASAKI; Kota TANAKA; Keisuke IKEDA; Hiroshi OCHI;
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1. Analysis of the high Reynolds number 2D tests on a wind turbine airfoil performed at two different wind tunnels [J] . O Pires, X Munduate, O Ceyhan, Journal of Physics: Conference Series . 2016,第1期

机译：在两个不同的风隧道中进行风力涡轮机翼型上的高雷诺数2D试验的分析
2. Two-dimensional Low-reynolds Number Wind Tunnel Results For Airfoil Naca 0018 [J] . W.A. Timmer Wind Engineering . 2008,第6期

机译：翼型Naca 0018的二维低雷诺数风洞结果
3. Two-dimensional Low-reynolds Number Wind Tunnel Results For Airfoil Naca 0018 [J] . W.A. Timmer Wind Engineering . 2008,第6期

机译：翼型Naca 0018的二维低雷诺数风洞结果
4. Low Reynolds Number Airfoil Testing in a Mars Wind Tunnel [C] . M. Anyoji, K. Nose, S. Ida, AIAA Fluid Dynamics Conference and Exhibit;AIAA/ASME Joint Thermophysics and Heat Transfer Conference;AIAA CFD High-Lift Prediction Workshop;HILIFTPW-1;AIAA Aerodynamic Measurement Technology and Ground Testing Conference;AIAA Applied Aerodynamics Conference;Plasmadynamics and Lasers Conference;Flow Control Conference . 2010

机译：火星风洞中的低雷诺数翼型测试
5. AN INVESTIGATION OF THE THEORETICAL AND EXPERIMENTAL AERODYNAMIC CHARACTERISTICS OF A LOW-CORRECTION WIND TUNNEL WALL CONFIGURATION FOR AIRFOIL TESTING. [D] . MALEK, AHMED FOUAD HASSAN. 1983

机译：用于翼型测试的低校正风洞墙构型的理论和实验气动特性研究。
6. Design Manufacturing and Testing of a New Concept for a Morphing Leading Edge using a Subsonic Blow Down Wind Tunnel [O] . David Communier, Franck Le Besnerais, Ruxandra Mihaela Botez, 2019

机译：设计制造和测试使用亚音速放空风洞的变形前沿的新概念
7. Low Reynolds Number Airfoil Design for a Mars Exploration Airplane Using a Transition Model [O] . Jongho JUNG, Kwanjung YEE, Takashi MISAKA, 2017

机译：低雷诺数翼型设计MARS勘探飞机使用过渡模型
8. Wind-tunnel Tests on an Aircraft Designed for Supersonic Speeds PART I High-speed Wind-tunnel Tests on 1/6.15-Scale Model Aircraft PART II No. 2 II1/2 -ft. Wind-tunnel Tests on a 1/4-Scale Model Wing [R] . S. P. HUTTON, M. Eng., A. D. Young 1950

机译：针对超音速设计的飞机的风洞测试第一部分1 / 6.15比例模型飞机的高速风洞试验第II部分第2号II1 / 2英尺。风洞测试1/4比例模型翼

Variable-Pressure Wind Tunnel Test of Airfoils at Low Reynolds Numbers Designed for Mars Exploration Aircraft

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