AH 79-100 B AIRFOIL (ah79100b-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 79-100 B AIRFOIL (ah79100b-il) Reynolds number: 50,000 Max Cl/Cd: 32.9 at α=9.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah79100b-il-50000-n5.txt Download as CSV file: xf-ah79100b-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 79-100 B AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.000 -0.2286 0.10784 0.10165 -0.0509 0.9598 0.0979
-6.750 -0.2315 0.10684 0.10071 -0.0544 0.9503 0.1016
-6.500 -0.2250 0.10504 0.09894 -0.0639 0.9400 0.1028
-6.250 -0.2060 0.09970 0.09358 -0.0573 0.9390 0.1085
-6.000 -0.1987 0.09733 0.09123 -0.0601 0.9307 0.1150
-5.750 -0.1920 0.09502 0.08898 -0.0706 0.9196 0.1186
-5.500 -0.1780 0.09098 0.08493 -0.0660 0.9166 0.1220
-5.250 -0.1620 0.08780 0.08173 -0.0685 0.9113 0.1266
-5.000 -0.1452 0.08451 0.07843 -0.0804 0.9017 0.1342
-4.750 -0.0992 0.07416 0.06772 -0.0966 0.8963 0.0723
-4.500 -0.0918 0.07174 0.06535 -0.0940 0.8899 0.0704
-4.250 -0.0566 0.06657 0.06002 -0.1023 0.8857 0.0694
-4.000 -0.0237 0.06178 0.05506 -0.1098 0.8802 0.0679
-3.750 0.0241 0.05564 0.04857 -0.1210 0.8754 0.0642
-3.500 0.0855 0.04966 0.04204 -0.1338 0.8727 0.0644
-3.250 0.1491 0.04483 0.03649 -0.1451 0.8708 0.0674
-3.000 0.2086 0.04094 0.03181 -0.1537 0.8689 0.0680
-2.750 0.2468 0.03902 0.02921 -0.1573 0.8629 0.0716
-2.500 0.2890 0.03712 0.02691 -0.1610 0.8593 0.0750
-2.250 0.3306 0.03561 0.02506 -0.1639 0.8563 0.0779
-2.000 0.3614 0.03482 0.02397 -0.1648 0.8511 0.0824
-1.750 0.3919 0.03418 0.02308 -0.1656 0.8455 0.0892
-1.500 0.4292 0.03335 0.02211 -0.1673 0.8420 0.0962
-1.250 0.4613 0.03290 0.02150 -0.1684 0.8369 0.1070
-1.000 0.4923 0.03260 0.02112 -0.1694 0.8306 0.1231
-0.750 0.5371 0.03175 0.02040 -0.1729 0.8272 0.1686
-0.500 0.5799 0.03048 0.02052 -0.1761 0.8240 0.5429
-0.250 0.5931 0.03073 0.02103 -0.1730 0.8155 0.6739
0.250 0.6141 0.03036 0.02098 -0.1650 0.8009 1.0000
0.500 0.6551 0.03049 0.02072 -0.1676 0.7969 1.0000
0.750 0.6795 0.03118 0.02119 -0.1678 0.7886 1.0000
1.000 0.7151 0.03138 0.02114 -0.1694 0.7833 1.0000
1.250 0.7436 0.03183 0.02140 -0.1699 0.7761 1.0000
1.500 0.7741 0.03215 0.02156 -0.1706 0.7692 1.0000
1.750 0.8152 0.03203 0.02127 -0.1726 0.7655 1.0000
2.000 0.8306 0.03296 0.02214 -0.1712 0.7548 1.0000
2.250 0.8698 0.03289 0.02196 -0.1729 0.7510 1.0000
2.500 0.8841 0.03391 0.02294 -0.1714 0.7403 1.0000
2.750 0.9220 0.03385 0.02282 -0.1728 0.7362 1.0000
3.250 0.9744 0.03472 0.02368 -0.1726 0.7212 1.0000
3.500 0.9881 0.03575 0.02472 -0.1709 0.7101 1.0000
3.750 1.0280 0.03544 0.02441 -0.1723 0.7060 1.0000
4.000 1.0401 0.03652 0.02557 -0.1703 0.6944 1.0000
4.500 1.0902 0.03739 0.02654 -0.1696 0.6785 1.0000
4.750 1.1060 0.03837 0.02759 -0.1681 0.6683 1.0000
5.000 1.1400 0.03826 0.02760 -0.1687 0.6627 1.0000
5.250 1.1523 0.03941 0.02885 -0.1668 0.6514 1.0000
5.500 1.1919 0.03886 0.02842 -0.1678 0.6468 1.0000
5.750 1.2022 0.04006 0.02972 -0.1656 0.6346 1.0000
6.000 1.2176 0.04097 0.03079 -0.1641 0.6236 1.0000
6.250 1.2544 0.04046 0.03044 -0.1645 0.6177 1.0000
6.500 1.2639 0.04177 0.03189 -0.1624 0.6056 1.0000
6.750 1.2808 0.04258 0.03286 -0.1610 0.5950 1.0000
7.000 1.3188 0.04178 0.03229 -0.1613 0.5882 1.0000
7.250 1.3304 0.04282 0.03350 -0.1592 0.5756 1.0000
7.500 1.3455 0.04368 0.03454 -0.1575 0.5640 1.0000
7.750 1.3888 0.04246 0.03360 -0.1581 0.5575 1.0000
8.000 1.3982 0.04364 0.03498 -0.1558 0.5443 1.0000
8.250 1.4116 0.04451 0.03605 -0.1538 0.5313 1.0000
8.500 1.4285 0.04508 0.03685 -0.1521 0.5184 1.0000
8.750 1.4482 0.04533 0.03732 -0.1504 0.5049 1.0000
9.000 1.4709 0.04475 0.03697 -0.1484 0.4864 1.0000
9.250 1.4801 0.04503 0.03735 -0.1452 0.4624 1.0000
9.500 1.4895 0.04528 0.03764 -0.1420 0.4348 1.0000
9.750 1.4960 0.04623 0.03864 -0.1392 0.4087 1.0000
10.000 1.4970 0.04811 0.04069 -0.1366 0.3859 1.0000
10.250 1.5025 0.04961 0.04228 -0.1342 0.3618 1.0000
10.500 1.5010 0.05185 0.04464 -0.1318 0.3338 1.0000
10.750 1.4955 0.05459 0.04737 -0.1294 0.3004 1.0000
11.000 1.4872 0.05776 0.05039 -0.1271 0.2609 1.0000
11.250 1.4760 0.06159 0.05401 -0.1252 0.2205 1.0000
11.500 1.4626 0.06599 0.05816 -0.1237 0.1840 1.0000
11.750 1.4491 0.07076 0.06271 -0.1226 0.1544 1.0000
12.000 1.4367 0.07566 0.06745 -0.1219 0.1320 1.0000
12.250 1.4265 0.08050 0.07221 -0.1215 0.1149 1.0000
12.500 1.4176 0.08531 0.07695 -0.1213 0.1015 1.0000
12.750 1.4103 0.09000 0.08161 -0.1213 0.0903 1.0000
13.000 1.4042 0.09457 0.08613 -0.1214 0.0815 1.0000
13.250 1.4008 0.09884 0.09048 -0.1215 0.0729 1.0000
13.500 1.3997 0.10278 0.09450 -0.1215 0.0657 1.0000
13.750 1.3988 0.10662 0.09835 -0.1217 0.0599 1.0000
14.000 1.4036 0.10967 0.10162 -0.1212 0.0547 1.0000
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Polar data table (+)
Polar graphs
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