AH 79-100 B AIRFOIL (ah79100b-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 79-100 B AIRFOIL (ah79100b-il) Reynolds number: 200,000 Max Cl/Cd: 99.97 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah79100b-il-200000.txt Download as CSV file: xf-ah79100b-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.1345 0.10095 0.09756 -0.0788 0.9612 0.0351
-8.000 -0.1175 0.09763 0.09423 -0.0859 0.9561 0.0354
-7.750 -0.1080 0.09469 0.09130 -0.0901 0.9474 0.0356
-7.500 -0.0915 0.08871 0.08533 -0.0916 0.9451 0.0363
-7.250 -0.0677 0.08475 0.08134 -0.0925 0.9436 0.0374
-7.000 -0.0442 0.08114 0.07772 -0.0964 0.9415 0.0392
-6.750 -0.0371 0.07872 0.07530 -0.0975 0.9320 0.0402
-6.500 -0.0147 0.07491 0.07148 -0.1032 0.9286 0.0419
-6.250 0.0067 0.07101 0.06758 -0.1157 0.9176 0.0456
-6.000 0.0427 0.06361 0.06013 -0.1304 0.9144 0.0468
-5.750 0.0602 0.06182 0.05834 -0.1256 0.9136 0.0494
-5.500 0.0738 0.05928 0.05579 -0.1277 0.9049 0.0518
-5.000 0.1770 0.04496 0.04115 -0.1615 0.8988 0.0612
-4.750 0.1904 0.04332 0.03950 -0.1608 0.8899 0.0640
-4.500 0.2522 0.03636 0.03204 -0.1768 0.8868 0.0752
-3.500 0.4391 0.02052 0.01396 -0.2002 0.8723 0.0603
-3.250 0.4802 0.01885 0.01204 -0.2033 0.8696 0.0626
-3.000 0.5076 0.01780 0.01074 -0.2033 0.8628 0.0618
-2.750 0.5421 0.01679 0.00956 -0.2046 0.8585 0.0628
-2.500 0.5792 0.01599 0.00864 -0.2064 0.8551 0.0662
-2.250 0.6046 0.01564 0.00823 -0.2059 0.8477 0.0702
-2.000 0.6382 0.01495 0.00747 -0.2069 0.8427 0.0738
-1.750 0.6726 0.01436 0.00691 -0.2083 0.8383 0.0829
-1.500 0.7012 0.01406 0.00664 -0.2087 0.8317 0.1010
-1.250 0.7426 0.01272 0.00648 -0.2125 0.8275 0.4784
-1.000 0.7706 0.01274 0.00663 -0.2123 0.8219 0.5817
-0.750 0.7967 0.01276 0.00671 -0.2117 0.8152 0.6328
-0.500 0.8272 0.01269 0.00664 -0.2118 0.8104 0.6787
-0.250 0.8489 0.01280 0.00684 -0.2103 0.8027 0.7199
0.000 0.8747 0.01277 0.00686 -0.2095 0.7976 0.7653
0.250 0.8980 0.01280 0.00694 -0.2082 0.7920 0.8031
0.500 0.9205 0.01278 0.00697 -0.2070 0.7854 0.8378
0.750 0.9420 0.01259 0.00680 -0.2052 0.7807 0.8900
1.000 0.9648 0.01258 0.00682 -0.2043 0.7731 1.0000
1.250 0.9987 0.01264 0.00675 -0.2056 0.7673 1.0000
1.500 1.0273 0.01281 0.00685 -0.2059 0.7600 1.0000
1.750 1.0573 0.01289 0.00686 -0.2064 0.7534 1.0000
2.000 1.0862 0.01305 0.00696 -0.2067 0.7471 1.0000
2.250 1.1134 0.01321 0.00710 -0.2066 0.7401 1.0000
2.500 1.1446 0.01330 0.00711 -0.2072 0.7348 1.0000
2.750 1.1689 0.01350 0.00736 -0.2066 0.7263 1.0000
3.000 1.1999 0.01357 0.00735 -0.2071 0.7206 1.0000
3.250 1.2237 0.01376 0.00759 -0.2064 0.7116 1.0000
3.500 1.2537 0.01381 0.00760 -0.2067 0.7048 1.0000
3.750 1.2779 0.01395 0.00779 -0.2059 0.6952 1.0000
4.000 1.3051 0.01407 0.00791 -0.2058 0.6872 1.0000
4.250 1.3316 0.01417 0.00803 -0.2054 0.6782 1.0000
4.500 1.3561 0.01431 0.00822 -0.2047 0.6679 1.0000
4.750 1.3830 0.01439 0.00830 -0.2044 0.6585 1.0000
5.000 1.4083 0.01448 0.00840 -0.2038 0.6475 1.0000
5.250 1.4316 0.01460 0.00857 -0.2028 0.6348 1.0000
5.500 1.4549 0.01472 0.00873 -0.2017 0.6211 1.0000
5.750 1.4777 0.01485 0.00890 -0.2006 0.6067 1.0000
6.000 1.5004 0.01503 0.00911 -0.1995 0.5924 1.0000
6.250 1.5225 0.01523 0.00932 -0.1983 0.5767 1.0000
6.500 1.5440 0.01548 0.00960 -0.1970 0.5600 1.0000
6.750 1.5647 0.01579 0.00991 -0.1956 0.5427 1.0000
7.000 1.5837 0.01614 0.01030 -0.1939 0.5238 1.0000
7.250 1.6013 0.01655 0.01070 -0.1919 0.5027 1.0000
7.500 1.6164 0.01704 0.01119 -0.1895 0.4780 1.0000
7.750 1.6286 0.01765 0.01172 -0.1866 0.4497 1.0000
8.000 1.6375 0.01839 0.01236 -0.1831 0.4179 1.0000
8.250 1.6409 0.01928 0.01312 -0.1788 0.3834 1.0000
8.500 1.6419 0.02034 0.01403 -0.1742 0.3475 1.0000
8.750 1.6409 0.02162 0.01515 -0.1695 0.3087 1.0000
9.000 1.6363 0.02325 0.01658 -0.1647 0.2638 1.0000
9.250 1.6274 0.02537 0.01842 -0.1596 0.2140 1.0000
9.500 1.6155 0.02799 0.02070 -0.1548 0.1617 1.0000
9.750 1.6033 0.03095 0.02333 -0.1504 0.1137 1.0000
10.000 1.5944 0.03389 0.02605 -0.1467 0.0841 1.0000
10.250 1.5882 0.03679 0.02887 -0.1436 0.0667 1.0000
10.500 1.5812 0.03992 0.03201 -0.1407 0.0539 1.0000
10.750 1.5722 0.04343 0.03555 -0.1379 0.0456 1.0000
11.000 1.5679 0.04660 0.03879 -0.1358 0.0396 1.0000
11.250 1.5601 0.05028 0.04256 -0.1336 0.0363 1.0000
11.500 1.5614 0.05309 0.04550 -0.1320 0.0330 1.0000
11.750 1.5615 0.05607 0.04856 -0.1307 0.0307 1.0000
12.000 1.5546 0.06003 0.05256 -0.1290 0.0288 1.0000
12.250 1.5601 0.06256 0.05524 -0.1280 0.0272 1.0000
12.500 1.5637 0.06537 0.05817 -0.1269 0.0258 1.0000
12.750 1.5677 0.06819 0.06109 -0.1259 0.0247 1.0000
13.000 1.5726 0.07094 0.06391 -0.1249 0.0238 1.0000
13.250 1.5793 0.07360 0.06660 -0.1236 0.0228 1.0000
13.500 1.5965 0.07564 0.06873 -0.1215 0.0219 1.0000
13.750 1.6040 0.07834 0.07166 -0.1206 0.0213 1.0000
14.000 1.6101 0.08126 0.07482 -0.1198 0.0207 1.0000
14.250 1.6132 0.08449 0.07827 -0.1193 0.0198 1.0000
14.500 1.6174 0.08780 0.08181 -0.1187 0.0194 1.0000
14.750 1.6197 0.09153 0.08579 -0.1181 0.0191 1.0000
15.000 1.6189 0.09571 0.09023 -0.1179 0.0189 1.0000
15.250 1.6142 0.10045 0.09526 -0.1180 0.0188 1.0000
15.500 1.6068 0.10550 0.10058 -0.1186 0.0186 1.0000
15.750 1.5943 0.11154 0.10695 -0.1198 0.0187 1.0000
16.000 1.5799 0.11794 0.11365 -0.1217 0.0189 1.0000
16.250 1.5626 0.12507 0.12109 -0.1244 0.0191 1.0000
16.500 1.5445 0.13262 0.12893 -0.1279 0.0192 1.0000
16.750 1.5259 0.14058 0.13714 -0.1321 0.0195 1.0000
17.000 1.5060 0.14926 0.14608 -0.1373 0.0198 1.0000
17.250 1.4858 0.15848 0.15552 -0.1434 0.0199 1.0000
17.500 1.4661 0.16818 0.16542 -0.1501 0.0203 1.0000
17.750 1.4461 0.17863 0.17603 -0.1578 0.0207 1.0000
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