AH-7-47-6 AIRFOIL (ah7476-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH-7-47-6 AIRFOIL (ah7476-il) Reynolds number: 100,000 Max Cl/Cd: 74.44 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah7476-il-100000-n5.txt Download as CSV file: xf-ah7476-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH-7-47-6 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3438 0.11577 0.11104 -0.0218 1.0000 0.0294
-7.750 -0.3536 0.11491 0.11027 -0.0199 1.0000 0.0295
-7.500 -0.3637 0.11403 0.10946 -0.0180 1.0000 0.0295
-7.250 -0.3498 0.11110 0.10655 -0.0242 0.9962 0.0297
-7.000 -0.3389 0.10575 0.10121 -0.0221 0.9952 0.0303
-6.750 -0.3253 0.10202 0.09745 -0.0232 0.9924 0.0317
-6.500 -0.3082 0.09855 0.09398 -0.0271 0.9886 0.0336
-6.250 -0.2874 0.09496 0.09038 -0.0330 0.9838 0.0356
-6.000 -0.2454 0.09121 0.08658 -0.0499 0.9779 0.0370
-5.750 -0.2345 0.08695 0.08234 -0.0500 0.9740 0.0376
-5.500 -0.2223 0.08338 0.07877 -0.0491 0.9712 0.0391
-5.250 -0.1971 0.07984 0.07520 -0.0540 0.9682 0.0422
-5.000 -0.1546 0.07528 0.07057 -0.0676 0.9626 0.0469
-4.750 -0.1385 0.07218 0.06747 -0.0674 0.9600 0.0497
-4.500 -0.0722 0.06698 0.06207 -0.0869 0.9560 0.0567
-4.250 -0.0648 0.06420 0.05934 -0.0837 0.9522 0.0588
-4.000 -0.0045 0.05958 0.05453 -0.0982 0.9500 0.0687
-3.750 0.0179 0.05687 0.05182 -0.0989 0.9478 0.0737
-3.500 0.0731 0.05253 0.04727 -0.1110 0.9438 0.0820
-3.250 0.1374 0.04882 0.04322 -0.1238 0.9417 0.0941
-3.000 0.1569 0.04623 0.04074 -0.1232 0.9388 0.0986
-2.500 0.3133 0.03434 0.02753 -0.1504 0.9378 0.0572
-2.250 0.3648 0.03171 0.02435 -0.1562 0.9348 0.0559
-2.000 0.4044 0.02963 0.02208 -0.1596 0.9299 0.0544
-1.750 0.4517 0.02757 0.01963 -0.1641 0.9271 0.0521
-1.500 0.4997 0.02580 0.01741 -0.1683 0.9248 0.0504
-1.250 0.5343 0.02469 0.01597 -0.1697 0.9180 0.0494
-1.000 0.5758 0.02355 0.01455 -0.1723 0.9137 0.0490
-0.500 0.6439 0.02225 0.01305 -0.1747 0.9028 0.0529
-0.250 0.6815 0.02156 0.01230 -0.1765 0.8993 0.0530
0.000 0.7214 0.02088 0.01160 -0.1788 0.8967 0.0532
0.250 0.7470 0.02068 0.01141 -0.1783 0.8879 0.0536
0.500 0.7851 0.02017 0.01088 -0.1802 0.8839 0.0544
0.750 0.8158 0.01992 0.01061 -0.1806 0.8768 0.0554
1.000 0.8500 0.01959 0.01026 -0.1816 0.8706 0.0574
1.250 0.8885 0.01914 0.00982 -0.1833 0.8659 0.0621
1.500 0.9167 0.01898 0.00974 -0.1831 0.8559 0.0786
1.750 0.9486 0.01715 0.00968 -0.1839 0.8497 1.0000
2.250 1.0087 0.01699 0.00942 -0.1839 0.8284 1.0000
2.500 1.0424 0.01680 0.00918 -0.1846 0.8176 1.0000
2.750 1.0765 0.01660 0.00897 -0.1854 0.8054 1.0000
3.000 1.1041 0.01656 0.00895 -0.1848 0.7855 1.0000
3.250 1.1341 0.01639 0.00872 -0.1845 0.7582 1.0000
3.500 1.1600 0.01635 0.00863 -0.1834 0.7206 1.0000
3.750 1.1899 0.01633 0.00850 -0.1831 0.6803 1.0000
4.000 1.2198 0.01644 0.00845 -0.1830 0.6418 1.0000
4.250 1.2468 0.01675 0.00858 -0.1824 0.6047 1.0000
4.500 1.2714 0.01719 0.00888 -0.1814 0.5709 1.0000
4.750 1.2944 0.01773 0.00930 -0.1803 0.5376 1.0000
5.000 1.3161 0.01832 0.00976 -0.1789 0.5057 1.0000
5.250 1.3369 0.01896 0.01027 -0.1774 0.4754 1.0000
5.500 1.3574 0.01961 0.01083 -0.1759 0.4477 1.0000
5.750 1.3773 0.02028 0.01147 -0.1743 0.4213 1.0000
6.000 1.3962 0.02096 0.01211 -0.1726 0.3924 1.0000
6.250 1.4150 0.02160 0.01278 -0.1708 0.3621 1.0000
6.500 1.4325 0.02229 0.01345 -0.1689 0.3245 1.0000
6.750 1.4459 0.02326 0.01419 -0.1663 0.2733 1.0000
7.250 1.4701 0.02567 0.01618 -0.1611 0.1906 1.0000
7.500 1.4820 0.02696 0.01729 -0.1586 0.1541 1.0000
7.750 1.4940 0.02822 0.01842 -0.1561 0.1184 1.0000
8.250 1.5088 0.03134 0.02122 -0.1496 0.0596 1.0000
8.500 1.5135 0.03302 0.02291 -0.1458 0.0446 1.0000
8.750 1.5193 0.03466 0.02460 -0.1423 0.0347 1.0000
9.000 1.5258 0.03625 0.02629 -0.1390 0.0294 1.0000
9.250 1.5306 0.03798 0.02812 -0.1357 0.0267 1.0000
9.500 1.5334 0.03989 0.03018 -0.1321 0.0251 1.0000
9.750 1.5360 0.04184 0.03234 -0.1287 0.0238 1.0000
10.000 1.5381 0.04388 0.03458 -0.1254 0.0225 1.0000
10.250 1.5398 0.04602 0.03691 -0.1224 0.0211 1.0000
10.500 1.5397 0.04837 0.03942 -0.1194 0.0199 1.0000
10.750 1.5363 0.05115 0.04233 -0.1164 0.0190 1.0000
11.000 1.5325 0.05420 0.04552 -0.1134 0.0184 1.0000
11.250 1.5335 0.05690 0.04845 -0.1109 0.0181 1.0000
11.500 1.5346 0.05974 0.05152 -0.1086 0.0177 1.0000
11.750 1.5355 0.06274 0.05477 -0.1064 0.0174 1.0000
12.000 1.5357 0.06594 0.05822 -0.1044 0.0171 1.0000
12.250 1.5343 0.06939 0.06195 -0.1025 0.0168 1.0000
12.500 1.5306 0.07310 0.06594 -0.1008 0.0164 1.0000
12.750 1.5247 0.07709 0.07024 -0.0995 0.0161 1.0000
13.000 1.5165 0.08139 0.07482 -0.0986 0.0158 1.0000
13.250 1.5063 0.08600 0.07971 -0.0982 0.0154 1.0000
13.500 1.4946 0.09099 0.08497 -0.0984 0.0152 1.0000
13.750 1.4816 0.09644 0.09069 -0.0993 0.0150 1.0000
14.000 1.4676 0.10236 0.09687 -0.1009 0.0148 1.0000
14.250 1.4527 0.10886 0.10363 -0.1034 0.0147 1.0000
14.500 1.4370 0.11600 0.11103 -0.1068 0.0147 1.0000
14.750 1.4204 0.12388 0.11916 -0.1112 0.0147 1.0000
15.000 1.4025 0.13270 0.12821 -0.1167 0.0149 1.0000
15.250 1.3823 0.14290 0.13865 -0.1236 0.0152 1.0000
15.500 1.3601 0.15473 0.15067 -0.1320 0.0156 1.0000
15.750 1.3369 0.16835 0.16446 -0.1418 0.0163 1.0000
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Polar data table (+)
Polar graphs
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