AH 79-100 C AIRFOIL (ah79100c-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 79-100 C AIRFOIL (ah79100c-il) Reynolds number: 200,000 Max Cl/Cd: 96.96 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah79100c-il-200000-n5.txt Download as CSV file: xf-ah79100c-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 79-100 C AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.1002 0.10324 0.09944 -0.0936 0.9456 0.0252
-8.750 -0.0903 0.09941 0.09561 -0.0978 0.9424 0.0253
-8.500 -0.0848 0.09653 0.09276 -0.0985 0.9362 0.0253
-8.250 -0.0746 0.09315 0.08937 -0.1005 0.9318 0.0253
-8.000 -0.0611 0.08932 0.08553 -0.1035 0.9292 0.0253
-7.750 -0.0502 0.08597 0.08217 -0.1015 0.9248 0.0197
-7.500 -0.0434 0.08295 0.07917 -0.1027 0.9190 0.0191
-7.250 -0.0316 0.07934 0.07556 -0.1058 0.9158 0.0182
-7.000 -0.0350 0.07663 0.07287 -0.1054 0.9065 0.0177
-6.750 -0.0253 0.07222 0.06846 -0.1093 0.9023 0.0173
-6.500 -0.0257 0.06674 0.06299 -0.1133 0.8922 0.0166
-6.250 -0.0062 0.06226 0.05849 -0.1193 0.8886 0.0168
-6.000 0.0076 0.05841 0.05462 -0.1237 0.8817 0.0170
-5.750 0.0312 0.05267 0.04882 -0.1321 0.8762 0.0172
-5.500 0.1093 0.02626 0.02107 -0.1713 0.8735 0.0210
-5.250 0.1366 0.02615 0.02095 -0.1719 0.8694 0.0226
-5.000 0.1750 0.02194 0.01585 -0.1770 0.8656 0.0261
-4.750 0.2074 0.02160 0.01544 -0.1784 0.8626 0.0285
-4.500 0.2475 0.01963 0.01287 -0.1817 0.8607 0.0315
-4.250 0.2853 0.01861 0.01171 -0.1843 0.8590 0.0332
-4.000 0.3251 0.01769 0.01055 -0.1871 0.8576 0.0353
-3.750 0.3475 0.01701 0.00969 -0.1862 0.8509 0.0363
-3.500 0.3824 0.01619 0.00867 -0.1878 0.8477 0.0377
-3.250 0.4201 0.01540 0.00773 -0.1900 0.8453 0.0392
-3.000 0.4601 0.01482 0.00712 -0.1928 0.8433 0.0422
-2.750 0.4858 0.01453 0.00678 -0.1925 0.8376 0.0452
-2.500 0.5183 0.01412 0.00628 -0.1936 0.8333 0.0485
-2.250 0.5554 0.01370 0.00583 -0.1957 0.8302 0.0546
-2.000 0.5946 0.01332 0.00540 -0.1982 0.8277 0.0641
-1.750 0.6173 0.01323 0.00531 -0.1972 0.8211 0.0754
-1.500 0.6500 0.01300 0.00512 -0.1984 0.8167 0.0976
-1.250 0.6870 0.01269 0.00492 -0.2005 0.8135 0.1400
-1.000 0.7127 0.01259 0.00493 -0.2003 0.8075 0.1855
-0.750 0.7425 0.01246 0.00488 -0.2008 0.8023 0.2323
-0.500 0.7780 0.01225 0.00479 -0.2026 0.7983 0.2980
0.000 0.8318 0.01194 0.00495 -0.2026 0.7864 0.4822
0.250 0.8619 0.01154 0.00503 -0.2030 0.7819 0.6741
0.500 0.8737 0.01130 0.00514 -0.1991 0.7746 0.8495
1.000 0.9298 0.01129 0.00503 -0.1990 0.7625 1.0000
1.250 0.9574 0.01140 0.00505 -0.1990 0.7562 1.0000
1.500 0.9883 0.01148 0.00506 -0.1997 0.7509 1.0000
1.750 1.0115 0.01164 0.00518 -0.1987 0.7433 1.0000
2.000 1.0426 0.01171 0.00517 -0.1994 0.7372 1.0000
2.250 1.0647 0.01188 0.00532 -0.1983 0.7290 1.0000
2.500 1.0938 0.01199 0.00539 -0.1986 0.7228 1.0000
2.750 1.1170 0.01215 0.00554 -0.1977 0.7150 1.0000
3.000 1.1448 0.01226 0.00560 -0.1977 0.7072 1.0000
3.250 1.1669 0.01243 0.00578 -0.1965 0.6979 1.0000
3.500 1.1939 0.01256 0.00589 -0.1963 0.6901 1.0000
3.750 1.2157 0.01274 0.00609 -0.1952 0.6810 1.0000
4.000 1.2396 0.01290 0.00625 -0.1944 0.6717 1.0000
4.250 1.2633 0.01306 0.00641 -0.1935 0.6611 1.0000
4.500 1.2836 0.01326 0.00663 -0.1920 0.6498 1.0000
4.750 1.3041 0.01345 0.00683 -0.1905 0.6375 1.0000
5.000 1.3238 0.01366 0.00703 -0.1889 0.6240 1.0000
5.250 1.3429 0.01389 0.00727 -0.1871 0.6096 1.0000
5.500 1.3622 0.01414 0.00752 -0.1854 0.5959 1.0000
5.750 1.3810 0.01442 0.00781 -0.1837 0.5814 1.0000
6.000 1.3984 0.01474 0.00812 -0.1816 0.5647 1.0000
6.250 1.4142 0.01511 0.00848 -0.1793 0.5451 1.0000
6.500 1.4289 0.01555 0.00885 -0.1768 0.5243 1.0000
6.750 1.4420 0.01605 0.00930 -0.1740 0.5012 1.0000
7.000 1.4527 0.01667 0.00983 -0.1709 0.4759 1.0000
7.250 1.4613 0.01740 0.01046 -0.1675 0.4483 1.0000
7.500 1.4689 0.01822 0.01116 -0.1640 0.4196 1.0000
7.750 1.4727 0.01924 0.01202 -0.1600 0.3869 1.0000
8.000 1.4760 0.02035 0.01297 -0.1560 0.3530 1.0000
8.250 1.4779 0.02162 0.01406 -0.1521 0.3170 1.0000
8.500 1.4799 0.02298 0.01524 -0.1483 0.2821 1.0000
8.750 1.4810 0.02450 0.01658 -0.1446 0.2467 1.0000
9.000 1.4818 0.02615 0.01802 -0.1411 0.2088 1.0000
9.250 1.4849 0.02775 0.01947 -0.1381 0.1779 1.0000
9.500 1.4880 0.02945 0.02102 -0.1352 0.1485 1.0000
9.750 1.4902 0.03128 0.02269 -0.1324 0.1157 1.0000
10.000 1.4898 0.03342 0.02464 -0.1295 0.0827 1.0000
10.250 1.4890 0.03571 0.02674 -0.1267 0.0531 1.0000
10.500 1.4876 0.03813 0.02906 -0.1240 0.0307 1.0000
10.750 1.4900 0.04029 0.03120 -0.1217 0.0228 1.0000
11.000 1.4945 0.04233 0.03330 -0.1198 0.0199 1.0000
11.250 1.5004 0.04427 0.03537 -0.1181 0.0182 1.0000
11.500 1.5050 0.04638 0.03760 -0.1164 0.0170 1.0000
11.750 1.5073 0.04881 0.04015 -0.1147 0.0160 1.0000
12.000 1.5118 0.05104 0.04253 -0.1132 0.0153 1.0000
12.250 1.5160 0.05336 0.04500 -0.1119 0.0146 1.0000
12.500 1.5190 0.05586 0.04764 -0.1107 0.0139 1.0000
12.750 1.5209 0.05857 0.05048 -0.1095 0.0134 1.0000
13.000 1.5215 0.06149 0.05354 -0.1084 0.0131 1.0000
13.250 1.5209 0.06465 0.05683 -0.1075 0.0128 1.0000
13.500 1.5189 0.06807 0.06037 -0.1067 0.0125 1.0000
13.750 1.5151 0.07181 0.06424 -0.1061 0.0123 1.0000
14.000 1.5131 0.07542 0.06799 -0.1056 0.0121 1.0000
14.250 1.5124 0.07893 0.07164 -0.1053 0.0120 1.0000
14.500 1.5115 0.08252 0.07537 -0.1051 0.0118 1.0000
14.750 1.5106 0.08615 0.07914 -0.1050 0.0116 1.0000
15.000 1.5101 0.08978 0.08291 -0.1050 0.0115 1.0000
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Polar data table (+)
Polar graphs
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