AH-6-40-7 AIRFOIL (ah6407-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH-6-40-7 AIRFOIL (ah6407-il) Reynolds number: 200,000 Max Cl/Cd: 91.54 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah6407-il-200000.txt Download as CSV file: xf-ah6407-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: AH-6-40-7 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
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3344 0.09738 0.09408 -0.0223 1.0000 0.0319
-7.250 -0.3430 0.09599 0.09275 -0.0194 1.0000 0.0323
-7.000 -0.3487 0.09432 0.09114 -0.0175 1.0000 0.0328
-6.750 -0.3527 0.09249 0.08935 -0.0162 1.0000 0.0333
-6.500 -0.3555 0.09053 0.08744 -0.0154 1.0000 0.0339
-6.250 -0.3565 0.08842 0.08537 -0.0152 1.0000 0.0346
-6.000 -0.3552 0.08611 0.08310 -0.0157 1.0000 0.0356
-5.750 -0.3508 0.08357 0.08059 -0.0172 1.0000 0.0367
-5.500 -0.2948 0.07860 0.07552 -0.0372 0.9965 0.0398
-5.250 -0.2576 0.07104 0.06791 -0.0480 0.9933 0.0408
-5.000 -0.2448 0.06791 0.06480 -0.0462 0.9897 0.0424
-4.750 -0.2120 0.06413 0.06098 -0.0515 0.9862 0.0447
-4.500 -0.1623 0.05916 0.05589 -0.0625 0.9837 0.0493
-4.250 -0.0909 0.05081 0.04726 -0.0814 0.9797 0.0541
-4.000 -0.0658 0.04847 0.04494 -0.0826 0.9757 0.0567
-3.750 -0.0012 0.04248 0.03862 -0.0959 0.9736 0.0682
-3.500 0.0353 0.04021 0.03632 -0.0993 0.9713 0.0735
-2.500 0.2625 0.02051 0.01408 -0.1285 0.9607 0.0651
-2.250 0.3115 0.01849 0.01159 -0.1326 0.9584 0.0653
-2.000 0.3591 0.01686 0.00970 -0.1365 0.9566 0.0689
-1.750 0.3941 0.01596 0.00873 -0.1378 0.9493 0.0710
-1.500 0.4382 0.01508 0.00779 -0.1408 0.9460 0.0747
-1.250 0.4828 0.01428 0.00696 -0.1439 0.9432 0.0813
-1.000 0.5168 0.01370 0.00644 -0.1449 0.9351 0.0886
-0.750 0.5567 0.01302 0.00581 -0.1469 0.9298 0.1065
-0.500 0.5899 0.01228 0.00557 -0.1478 0.9211 0.2403
-0.250 0.6247 0.01174 0.00529 -0.1489 0.9142 0.3315
0.000 0.6522 0.01093 0.00524 -0.1487 0.9033 0.5888
0.250 0.6723 0.01008 0.00492 -0.1460 0.8919 1.0000
0.500 0.7008 0.00998 0.00470 -0.1455 0.8805 1.0000
0.750 0.7287 0.00990 0.00450 -0.1449 0.8680 1.0000
1.000 0.7559 0.00985 0.00436 -0.1441 0.8539 1.0000
1.250 0.7828 0.00983 0.00426 -0.1434 0.8384 1.0000
1.500 0.8095 0.00983 0.00418 -0.1427 0.8213 1.0000
1.750 0.8363 0.00984 0.00412 -0.1419 0.8025 1.0000
2.000 0.8628 0.00989 0.00406 -0.1412 0.7811 1.0000
2.250 0.8891 0.00997 0.00403 -0.1403 0.7567 1.0000
2.500 0.9150 0.01011 0.00405 -0.1395 0.7285 1.0000
2.750 0.9406 0.01029 0.00411 -0.1387 0.6965 1.0000
3.000 0.9657 0.01055 0.00420 -0.1378 0.6588 1.0000
3.250 0.9902 0.01091 0.00433 -0.1368 0.6163 1.0000
3.500 1.0140 0.01136 0.00453 -0.1358 0.5715 1.0000
3.750 1.0376 0.01187 0.00482 -0.1348 0.5299 1.0000
4.000 1.0614 0.01241 0.00515 -0.1340 0.4958 1.0000
4.250 1.0857 0.01293 0.00551 -0.1333 0.4680 1.0000
4.500 1.1103 0.01344 0.00591 -0.1327 0.4452 1.0000
4.750 1.1350 0.01396 0.00636 -0.1321 0.4258 1.0000
5.000 1.1599 0.01446 0.00680 -0.1316 0.4096 1.0000
5.250 1.1849 0.01496 0.00725 -0.1311 0.3946 1.0000
5.500 1.2096 0.01543 0.00769 -0.1306 0.3796 1.0000
5.750 1.2343 0.01587 0.00817 -0.1300 0.3657 1.0000
6.000 1.2582 0.01630 0.00858 -0.1293 0.3497 1.0000
6.250 1.2815 0.01663 0.00894 -0.1286 0.3300 1.0000
6.500 1.3046 0.01696 0.00931 -0.1278 0.3107 1.0000
6.750 1.3273 0.01737 0.00974 -0.1269 0.2922 1.0000
7.000 1.3503 0.01772 0.01016 -0.1261 0.2713 1.0000
7.250 1.3721 0.01817 0.01061 -0.1251 0.2468 1.0000
7.500 1.3922 0.01880 0.01114 -0.1239 0.1959 1.0000
7.750 1.3912 0.02221 0.01335 -0.1200 0.0533 1.0000
8.000 1.4029 0.02401 0.01514 -0.1173 0.0397 1.0000
8.250 1.4179 0.02525 0.01656 -0.1151 0.0353 1.0000
8.500 1.4283 0.02681 0.01820 -0.1123 0.0323 1.0000
8.750 1.4337 0.02875 0.02023 -0.1088 0.0301 1.0000
9.000 1.4454 0.03001 0.02164 -0.1063 0.0282 1.0000
9.250 1.4536 0.03156 0.02330 -0.1032 0.0268 1.0000
9.500 1.4595 0.03320 0.02504 -0.0999 0.0258 1.0000
9.750 1.4660 0.03501 0.02693 -0.0968 0.0250 1.0000
10.000 1.4741 0.03707 0.02909 -0.0941 0.0242 1.0000
10.250 1.4863 0.03965 0.03174 -0.0920 0.0235 1.0000
10.500 1.5085 0.04393 0.03620 -0.0917 0.0226 1.0000
10.750 1.5121 0.04543 0.03795 -0.0883 0.0220 1.0000
11.000 1.5173 0.04756 0.04034 -0.0855 0.0215 1.0000
11.250 1.5226 0.05047 0.04353 -0.0829 0.0213 1.0000
11.500 1.5236 0.05365 0.04701 -0.0801 0.0212 1.0000
11.750 1.5202 0.05709 0.05075 -0.0771 0.0213 1.0000
12.000 1.5127 0.06080 0.05475 -0.0742 0.0214 1.0000
12.250 1.5021 0.06482 0.05906 -0.0717 0.0215 1.0000
12.500 1.4886 0.06918 0.06370 -0.0695 0.0217 1.0000
12.750 1.4728 0.07395 0.06872 -0.0680 0.0219 1.0000
13.000 1.4551 0.07921 0.07423 -0.0671 0.0221 1.0000
13.250 1.4459 0.08574 0.08094 -0.0665 0.0228 1.0000
13.500 1.4332 0.08955 0.08497 -0.0667 0.0230 1.0000
13.750 1.4180 0.09407 0.08970 -0.0677 0.0232 1.0000
14.000 1.3989 0.09961 0.09551 -0.0700 0.0236 1.0000
14.250 1.3707 0.10766 0.10385 -0.0745 0.0242 1.0000
14.500 1.3389 0.11756 0.11404 -0.0813 0.0245 1.0000
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Polar data table (+)
Polar graphs
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