AH21 7% version (Andrew Hollom) (ah21-7-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH21 7% version (Andrew Hollom) (ah21-7-il) Reynolds number: 200,000 Max Cl/Cd: 78.13 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah21-7-il-200000.txt Download as CSV file: xf-ah21-7-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: AH21 7% version (Andrew Hollom)
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5078 0.09191 0.08847 -0.0351 1.0000 0.0541
-8.500 -0.5282 0.08854 0.08519 -0.0362 1.0000 0.0542
-8.250 -0.5495 0.08441 0.08106 -0.0382 1.0000 0.0543
-8.000 -0.5644 0.08053 0.07711 -0.0392 1.0000 0.0545
-7.750 -0.5762 0.07695 0.07340 -0.0392 1.0000 0.0546
-7.500 -0.5782 0.07051 0.06711 -0.0377 1.0000 0.0559
-7.250 -0.5736 0.06825 0.06489 -0.0355 1.0000 0.0568
-7.000 -0.5708 0.06586 0.06250 -0.0339 1.0000 0.0581
-6.750 -0.5689 0.06281 0.05940 -0.0333 1.0000 0.0597
-6.500 -0.5662 0.05912 0.05560 -0.0334 1.0000 0.0622
-6.250 -0.5691 0.05330 0.04895 -0.0360 1.0000 0.0681
-6.000 -0.5577 0.04916 0.04500 -0.0352 1.0000 0.0696
-5.750 -0.5450 0.04684 0.04270 -0.0342 1.0000 0.0716
-5.500 -0.5307 0.04451 0.04021 -0.0336 1.0000 0.0766
-5.250 -0.5002 0.02977 0.02558 -0.0320 1.0000 0.0845
-5.000 -0.4843 0.02754 0.02326 -0.0313 1.0000 0.0893
-4.750 -0.4808 0.03612 0.03107 -0.0331 1.0000 0.0986
-4.500 -0.4382 0.02480 0.01769 -0.0319 1.0000 0.0420
-4.250 -0.4146 0.02297 0.01556 -0.0312 1.0000 0.0420
-4.000 -0.3915 0.02227 0.01458 -0.0303 1.0000 0.0431
-3.750 -0.3675 0.02020 0.01230 -0.0297 1.0000 0.0441
-3.500 -0.3439 0.01898 0.01100 -0.0290 1.0000 0.0450
-3.250 -0.3160 0.01812 0.01011 -0.0292 0.9989 0.0467
-3.000 -0.2807 0.01755 0.00952 -0.0308 0.9959 0.0496
-2.750 -0.2453 0.01729 0.00918 -0.0324 0.9925 0.0545
-2.500 -0.2121 0.01656 0.00851 -0.0338 0.9889 0.0632
-2.250 -0.1765 0.01584 0.00798 -0.0356 0.9857 0.1022
-2.000 -0.1438 0.01458 0.00803 -0.0377 0.9835 0.3859
-1.750 -0.1189 0.01383 0.00815 -0.0374 0.9782 0.6005
-1.500 -0.0961 0.01351 0.00861 -0.0354 0.9737 0.8044
-1.250 -0.0542 0.01362 0.00893 -0.0372 0.9716 0.9491
-1.000 -0.0086 0.01360 0.00876 -0.0413 0.9669 1.0000
-0.750 0.0276 0.01376 0.00877 -0.0434 0.9615 1.0000
-0.500 0.0697 0.01402 0.00891 -0.0466 0.9581 1.0000
-0.250 0.0982 0.01402 0.00882 -0.0470 0.9501 1.0000
0.000 0.1389 0.01417 0.00888 -0.0498 0.9458 1.0000
0.250 0.1713 0.01422 0.00886 -0.0509 0.9387 1.0000
0.500 0.2104 0.01424 0.00884 -0.0532 0.9331 1.0000
0.750 0.2494 0.01425 0.00881 -0.0555 0.9276 1.0000
1.000 0.2846 0.01415 0.00869 -0.0569 0.9199 1.0000
1.250 0.3337 0.01397 0.00851 -0.0609 0.9162 1.0000
1.500 0.3638 0.01377 0.00831 -0.0611 0.9058 1.0000
1.750 0.4152 0.01335 0.00793 -0.0653 0.9020 1.0000
2.000 0.4470 0.01301 0.00762 -0.0656 0.8911 1.0000
2.250 0.4865 0.01252 0.00717 -0.0673 0.8822 1.0000
2.500 0.5352 0.01178 0.00651 -0.0705 0.8756 1.0000
2.750 0.5714 0.01126 0.00605 -0.0714 0.8637 1.0000
3.000 0.6099 0.01071 0.00557 -0.0727 0.8496 1.0000
3.250 0.6505 0.01019 0.00512 -0.0744 0.8314 1.0000
3.500 0.6857 0.00985 0.00481 -0.0751 0.8035 1.0000
3.750 0.7244 0.00962 0.00452 -0.0765 0.7595 1.0000
4.000 0.7586 0.00971 0.00435 -0.0771 0.6853 1.0000
4.250 0.7775 0.01023 0.00442 -0.0747 0.5914 1.0000
4.500 0.7873 0.01102 0.00468 -0.0709 0.4924 1.0000
4.750 0.7957 0.01191 0.00506 -0.0671 0.3944 1.0000
5.000 0.8059 0.01287 0.00552 -0.0639 0.3034 1.0000
5.250 0.8189 0.01385 0.00607 -0.0614 0.2251 1.0000
5.500 0.8342 0.01480 0.00667 -0.0593 0.1706 1.0000
5.750 0.8516 0.01566 0.00733 -0.0575 0.1357 1.0000
6.000 0.8689 0.01657 0.00805 -0.0558 0.1141 1.0000
6.250 0.8878 0.01741 0.00884 -0.0542 0.0993 1.0000
6.500 0.9068 0.01828 0.00967 -0.0527 0.0881 1.0000
6.750 0.9280 0.01899 0.01044 -0.0515 0.0795 1.0000
7.000 0.9479 0.02019 0.01160 -0.0503 0.0730 1.0000
7.250 0.9701 0.02094 0.01244 -0.0493 0.0672 1.0000
7.500 0.9932 0.02256 0.01397 -0.0489 0.0616 1.0000
7.750 1.0170 0.02346 0.01505 -0.0481 0.0585 1.0000
8.000 1.0403 0.02452 0.01622 -0.0474 0.0548 1.0000
8.250 1.0644 0.02607 0.01774 -0.0472 0.0510 1.0000
8.500 1.0892 0.02800 0.01994 -0.0467 0.0486 1.0000
8.750 1.1112 0.02954 0.02174 -0.0457 0.0464 1.0000
9.000 1.1309 0.03086 0.02323 -0.0445 0.0438 1.0000
9.250 1.1497 0.03221 0.02465 -0.0434 0.0415 1.0000
9.500 1.1669 0.03696 0.02970 -0.0427 0.0396 1.0000
9.750 1.1771 0.03831 0.03145 -0.0398 0.0386 1.0000
10.000 1.1849 0.04019 0.03374 -0.0368 0.0370 1.0000
10.250 1.1900 0.04262 0.03653 -0.0337 0.0356 1.0000
10.500 1.1902 0.04564 0.03991 -0.0303 0.0348 1.0000
10.750 1.1864 0.04869 0.04328 -0.0266 0.0342 1.0000
11.000 1.1820 0.05100 0.04579 -0.0229 0.0334 1.0000
11.250 1.1847 0.05261 0.04746 -0.0203 0.0325 1.0000
11.500 1.1798 0.05501 0.04996 -0.0174 0.0317 1.0000
11.750 1.1636 0.05869 0.05383 -0.0140 0.0312 1.0000
12.000 1.1435 0.06243 0.05781 -0.0108 0.0312 1.0000
12.250 1.1210 0.06658 0.06219 -0.0087 0.0311 1.0000
12.500 1.0971 0.07116 0.06698 -0.0077 0.0311 1.0000
12.750 1.0736 0.07597 0.07201 -0.0080 0.0312 1.0000
13.000 0.8248 0.10594 0.10289 -0.0257 0.0413 1.0000
13.250 0.7281 0.14006 0.13699 -0.0417 0.0739 1.0000
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Polar data table (+)
Polar graphs
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