OAF102 AIRFOIL (oaf102-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: OAF102 AIRFOIL (oaf102-il) Reynolds number: 100,000 Max Cl/Cd: 61.91 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-oaf102-il-100000.txt Download as CSV file: xf-oaf102-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: OAF102 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4560 0.09879 0.09401 -0.0293 1.0000 0.1427
-8.250 -0.4253 0.09427 0.08943 -0.0248 1.0000 0.1470
-8.000 -0.5030 0.05444 0.04947 -0.0731 1.0000 0.0735
-7.750 -0.4918 0.04493 0.03941 -0.0838 1.0000 0.0731
-7.500 -0.4667 0.03737 0.03086 -0.0925 1.0000 0.0747
-7.250 -0.4447 0.03337 0.02665 -0.0945 1.0000 0.0770
-7.000 -0.4217 0.03091 0.02396 -0.0955 1.0000 0.0803
-6.750 -0.3958 0.02852 0.02099 -0.0971 1.0000 0.0861
-6.500 -0.3736 0.02633 0.01862 -0.0975 1.0000 0.0910
-6.250 -0.3512 0.02503 0.01709 -0.0975 1.0000 0.0979
-6.000 -0.3290 0.02373 0.01572 -0.0975 1.0000 0.1062
-5.750 -0.3045 0.02252 0.01428 -0.0978 1.0000 0.1166
-5.500 -0.2807 0.02173 0.01344 -0.0980 1.0000 0.1305
-5.250 -0.2567 0.02111 0.01287 -0.0982 1.0000 0.1470
-5.000 -0.2318 0.02075 0.01248 -0.0986 1.0000 0.1694
-4.750 -0.2066 0.02050 0.01233 -0.0990 1.0000 0.1946
-4.500 -0.1812 0.02040 0.01226 -0.0995 1.0000 0.2218
-4.250 -0.1554 0.02043 0.01228 -0.1000 0.9997 0.2487
-4.000 -0.1118 0.02039 0.01228 -0.1036 0.9944 0.2804
-3.750 -0.0703 0.02038 0.01224 -0.1067 0.9881 0.3091
-3.500 -0.0255 0.02037 0.01218 -0.1104 0.9832 0.3372
-3.250 0.0124 0.02037 0.01226 -0.1127 0.9759 0.3586
-3.000 0.0576 0.02027 0.01205 -0.1165 0.9711 0.3835
-2.750 0.0948 0.02021 0.01204 -0.1186 0.9637 0.4027
-2.500 0.1386 0.02007 0.01189 -0.1219 0.9585 0.4249
-2.250 0.1783 0.01996 0.01175 -0.1245 0.9518 0.4464
-2.000 0.2199 0.01978 0.01162 -0.1273 0.9458 0.4674
-1.750 0.2658 0.01953 0.01135 -0.1310 0.9417 0.4917
-1.500 0.2964 0.01953 0.01141 -0.1317 0.9324 0.5107
-1.250 0.3380 0.01931 0.01121 -0.1344 0.9275 0.5343
-1.000 0.3674 0.01933 0.01129 -0.1349 0.9184 0.5536
-0.750 0.4049 0.01914 0.01117 -0.1366 0.9128 0.5749
-0.500 0.4334 0.01924 0.01131 -0.1370 0.9038 0.5966
-0.250 0.4673 0.01908 0.01127 -0.1379 0.8978 0.6188
0.000 0.4944 0.01920 0.01147 -0.1379 0.8886 0.6425
0.250 0.5258 0.01906 0.01147 -0.1382 0.8824 0.6690
0.500 0.5506 0.01920 0.01175 -0.1376 0.8730 0.6983
0.750 0.5793 0.01902 0.01174 -0.1371 0.8667 0.7364
1.000 0.5997 0.01906 0.01205 -0.1355 0.8567 0.7876
1.250 0.6149 0.01860 0.01192 -0.1319 0.8492 1.0000
1.500 0.6487 0.01898 0.01218 -0.1338 0.8399 1.0000
1.750 0.6797 0.01927 0.01240 -0.1345 0.8323 1.0000
2.000 0.7088 0.01959 0.01269 -0.1348 0.8238 1.0000
2.250 0.7368 0.01998 0.01309 -0.1349 0.8153 1.0000
2.500 0.7657 0.02021 0.01334 -0.1347 0.8075 1.0000
2.750 0.7924 0.02068 0.01386 -0.1347 0.7981 1.0000
3.000 0.8214 0.02081 0.01404 -0.1343 0.7911 1.0000
3.250 0.8473 0.02134 0.01465 -0.1341 0.7807 1.0000
3.500 0.8761 0.02143 0.01480 -0.1335 0.7738 1.0000
3.750 0.9021 0.02173 0.01522 -0.1329 0.7623 1.0000
4.000 0.9278 0.02097 0.01447 -0.1300 0.7457 1.0000
4.250 0.9504 0.01983 0.01330 -0.1260 0.7192 1.0000
4.500 0.9745 0.01893 0.01236 -0.1228 0.6949 1.0000
4.750 0.9996 0.01849 0.01197 -0.1208 0.6724 1.0000
5.000 1.0246 0.01809 0.01163 -0.1189 0.6466 1.0000
5.250 1.0489 0.01766 0.01125 -0.1168 0.6125 1.0000
5.500 1.0711 0.01730 0.01085 -0.1143 0.5496 1.0000
5.750 1.0698 0.02002 0.01143 -0.1091 0.2189 1.0000
6.000 1.0767 0.02314 0.01365 -0.1065 0.1339 1.0000
6.250 1.0923 0.02489 0.01525 -0.1046 0.1122 1.0000
6.500 1.1091 0.02657 0.01685 -0.1027 0.1002 1.0000
6.750 1.1280 0.02836 0.01851 -0.1012 0.0913 1.0000
7.000 1.1500 0.02996 0.02005 -0.1002 0.0835 1.0000
7.250 1.1766 0.03215 0.02221 -0.0995 0.0787 1.0000
7.500 1.2023 0.03384 0.02403 -0.0988 0.0735 1.0000
7.750 1.2297 0.03637 0.02643 -0.0988 0.0690 1.0000
8.000 1.2572 0.03927 0.02959 -0.0983 0.0671 1.0000
8.250 1.2803 0.04167 0.03241 -0.0970 0.0653 1.0000
8.500 1.3007 0.04417 0.03530 -0.0957 0.0628 1.0000
8.750 1.3196 0.04721 0.03871 -0.0942 0.0615 1.0000
9.000 1.3352 0.05104 0.04302 -0.0924 0.0617 1.0000
9.250 1.3458 0.05545 0.04796 -0.0901 0.0629 1.0000
9.500 1.3526 0.06010 0.05306 -0.0877 0.0642 1.0000
9.750 1.3554 0.06472 0.05811 -0.0853 0.0650 1.0000
10.000 1.3546 0.06946 0.06320 -0.0828 0.0658 1.0000
10.250 1.3535 0.07482 0.06880 -0.0809 0.0668 1.0000
10.500 1.2272 0.07093 0.06568 -0.0619 0.0710 1.0000
10.750 1.1683 0.07674 0.07192 -0.0566 0.0751 1.0000
11.000 1.1348 0.08230 0.07768 -0.0548 0.0767 1.0000
11.250 1.1067 0.08821 0.08374 -0.0541 0.0783 1.0000
11.500 1.0545 0.09622 0.09205 -0.0553 0.0843 1.0000
11.750 1.0062 0.10407 0.10004 -0.0582 0.0844 1.0000
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Polar data table (+)
Polar graphs
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