NACA 0010 1.0000 0.00105 0.9500 0.00672 0.9000 0.01207 0.8000 0.02187 0.7000 0.03053 0.6000 0.03803 0.5000 0.04412 0.4000 0.04837 0.3000 0.05002 0.2500 0.04952 0.2000 0.04782 0.1500 0.04455 0.1000 0.03902 0.0750 0.03500 0.0500 0.02962 0.0250 0.02178 0.0125 0.01578 0.0000 0.00000 0.0125 -0.01578 0.0250 -0.02178...
Airfoil (aerofoil) plot of NACA 0010 with ajustable chord width, camber and thickness and full size print out
XFOIL Version 6.96 Calculated polar for: NACA 0010 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr --- --- --- --- --- --- --- -10.500 -0.5558 0.10754 0.10264 -...
六图网提供精美好看的装饰装修素材模板下载,本次装饰装修作品主题是NACA 0010,编号是1624660,格式是,该NACA 0010素材大小是0.10 MB。NACA 0010是由装饰装修设计师泠吢上传. 浏览本次作品的您可能还对NACA感兴趣。
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翼型数据NACA0010,此数据可以直接导入到CATIA中,直接画出翼型 上传者:nihaosinsin时间:2012-12-20 NACA 翼型生成器及使用说明 比较方便的NACA系列翼型生成软件,支持坐标点导出功能 上传者:hutian1993时间:2024-03-26 各种类型的翼型数据库,包含NACA常用翼型,共1500组数据 ...
翼型数据NACA0010,此数据可以直接导入到CATIA中,直接画出翼型 上传者:nihaosinsin时间:2012-12-20 NACA 翼型生成器及使用说明 比较方便的NACA系列翼型生成软件,支持坐标点导出功能 上传者:hutian1993时间:2024-03-26 各种类型的翼型数据库,包含NACA常用翼型,共1500组数据 ...
A NACA 0010 airfoil with a trailing edge flap of 35% of the chord, in the range of angle of attack 0- 40 deg and flap deflections up to 30 deg was investigated. Computer tests were carried out in hypersonic, rarefied flow by... G Zuppardi,D Vangonea - 《Advances in Aircraft & Spa...
NACA 0010 1.000000, 0.001050 0.950000, 0.006720 0.900000, 0.012070 0.800000, 0.021870 0.700000, 0.030530 0.600000, 0.038030 0.500000, 0.044120 0.400000, 0.048370 0.300000, 0.050020 0.250000, 0.049520 0.200000, 0.047820 0.150000, 0.044550 0.100000, 0.039020 ...
NACA 0010 1.000000, 0.001050 0.950000, 0.006720 0.900000, 0.012070 0.800000, 0.021870 0.700000, 0.030530 0.600000, 0.038030 0.500000, 0.044120 0.400000, 0.048370 0.300000, 0.050020 0.250000, 0.049520 0.200000, 0.047820 0.150000, 0.044550 0.100000, 0.039020 ...