YS-915 (ys915-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: YS-915 (ys915-il) Reynolds number: 50,000 Max Cl/Cd: 20.38 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ys915-il-50000.txt Download as CSV file: xf-ys915-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: YS-915
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.6125 0.08093 0.07503 -0.0261 1.0000 0.1817
-6.750 -0.6479 0.06639 0.06013 -0.0329 1.0000 0.1311
-6.500 -0.6557 0.05991 0.05318 -0.0336 1.0000 0.1151
-6.250 -0.6514 0.05485 0.04766 -0.0329 1.0000 0.1033
-6.000 -0.6431 0.05025 0.04245 -0.0317 1.0000 0.0940
-5.750 -0.6328 0.04667 0.03771 -0.0296 1.0000 0.0853
-5.500 -0.6153 0.04263 0.03354 -0.0284 1.0000 0.0823
-5.250 -0.5970 0.03940 0.02984 -0.0268 1.0000 0.0802
-5.000 -0.5771 0.03670 0.02658 -0.0252 1.0000 0.0822
-4.750 -0.5551 0.03448 0.02375 -0.0236 1.0000 0.0847
-4.500 -0.5306 0.03177 0.02080 -0.0223 1.0000 0.0875
-4.250 -0.5053 0.02963 0.01855 -0.0208 1.0000 0.0905
-4.000 -0.4807 0.02785 0.01657 -0.0189 1.0000 0.0973
-3.750 -0.4594 0.02599 0.01478 -0.0172 1.0000 0.1144
-3.500 -0.4361 0.02320 0.01259 -0.0164 1.0000 0.1843
-3.250 -0.4419 0.02159 0.01331 -0.0071 1.0000 0.5963
-3.000 -0.4478 0.02185 0.01405 0.0038 1.0000 0.7109
-2.750 -0.4482 0.02186 0.01413 0.0135 1.0000 0.7896
-2.500 -0.4255 0.02139 0.01339 0.0153 1.0000 0.8286
-2.250 -0.3880 0.02111 0.01284 0.0139 1.0000 0.8777
-2.000 -0.2790 0.02170 0.01273 -0.0022 1.0000 0.9486
-1.750 -0.2051 0.02093 0.01128 -0.0163 1.0000 1.0000
-1.500 -0.2056 0.02010 0.01011 -0.0139 1.0000 1.0000
-1.250 -0.1900 0.01994 0.00961 -0.0129 1.0000 1.0000
-1.000 -0.1715 0.01992 0.00929 -0.0120 1.0000 1.0000
-0.750 -0.1521 0.01997 0.00908 -0.0112 1.0000 1.0000
-0.500 -0.1322 0.02007 0.00896 -0.0104 1.0000 1.0000
-0.250 -0.1120 0.02019 0.00890 -0.0096 1.0000 1.0000
0.000 -0.0917 0.02035 0.00884 -0.0088 1.0000 1.0000
0.250 -0.0712 0.02053 0.00888 -0.0081 1.0000 1.0000
0.500 -0.0508 0.02074 0.00898 -0.0073 1.0000 1.0000
0.750 -0.0303 0.02097 0.00912 -0.0066 1.0000 1.0000
1.000 -0.0098 0.02122 0.00932 -0.0059 1.0000 1.0000
1.250 0.0106 0.02150 0.00956 -0.0052 1.0000 1.0000
1.500 0.0309 0.02181 0.00985 -0.0045 1.0000 1.0000
1.750 0.0510 0.02214 0.01017 -0.0038 1.0000 1.0000
2.000 0.0711 0.02250 0.01055 -0.0032 1.0000 1.0000
2.250 0.0910 0.02289 0.01097 -0.0025 1.0000 1.0000
2.500 0.1106 0.02331 0.01145 -0.0019 1.0000 1.0000
2.750 0.1300 0.02377 0.01199 -0.0013 1.0000 1.0000
3.000 0.1492 0.02427 0.01267 -0.0007 1.0000 1.0000
3.250 0.1680 0.02480 0.01332 -0.0001 1.0000 1.0000
3.500 0.1865 0.02539 0.01404 0.0004 1.0000 1.0000
3.750 0.2046 0.02602 0.01484 0.0009 1.0000 1.0000
4.000 0.2223 0.02672 0.01572 0.0014 1.0000 1.0000
4.250 0.2394 0.02748 0.01668 0.0019 1.0000 1.0000
4.500 0.2560 0.02831 0.01773 0.0023 1.0000 1.0000
4.750 0.2719 0.02924 0.01902 0.0026 1.0000 1.0000
5.000 0.2870 0.03027 0.02032 0.0029 1.0000 1.0000
5.250 0.3012 0.03141 0.02176 0.0031 1.0000 1.0000
5.500 0.7217 0.03542 0.02425 -0.0355 0.0853 1.0000
5.750 0.7524 0.03878 0.02814 -0.0344 0.0878 1.0000
6.000 0.7779 0.04264 0.03237 -0.0330 0.0916 1.0000
6.250 0.7959 0.04563 0.03615 -0.0298 0.0991 1.0000
6.500 0.8144 0.05006 0.04084 -0.0279 0.1054 1.0000
6.750 0.8240 0.05343 0.04498 -0.0241 0.1166 1.0000
7.000 0.8320 0.05766 0.04998 -0.0207 0.1399 1.0000
7.250 0.8383 0.06352 0.05663 -0.0188 0.1887 1.0000
7.500 0.8132 0.07294 0.06697 -0.0240 0.3052 1.0000
7.750 0.7725 0.07636 0.07045 -0.0227 0.3093 1.0000
8.000 0.7331 0.08163 0.07563 -0.0242 0.3284 1.0000
8.250 0.6593 0.07467 0.06897 -0.0106 0.2676 1.0000
8.500 0.6219 0.08092 0.07513 -0.0134 0.2704 1.0000
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Polar data table (+)
Polar graphs
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