AH21 9% version (Andrew Hollom) (ah21-9-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH21 9% version (Andrew Hollom) (ah21-9-il) Reynolds number: 100,000 Max Cl/Cd: 51.14 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah21-9-il-100000.txt Download as CSV file: xf-ah21-9-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: AH21 9% version (Andrew Hollom)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4015 0.09669 0.09189 -0.0254 1.0000 0.0932
-9.000 -0.4125 0.09366 0.08892 -0.0272 1.0000 0.0963
-8.750 -0.4306 0.09091 0.08627 -0.0299 1.0000 0.0973
-8.500 -0.4166 0.08575 0.08108 -0.0272 1.0000 0.1007
-8.250 -0.4123 0.08245 0.07781 -0.0261 1.0000 0.1048
-8.000 -0.4220 0.07923 0.07466 -0.0267 1.0000 0.1087
-7.750 -0.4435 0.07654 0.07208 -0.0279 1.0000 0.1104
-7.500 -0.5258 0.08298 0.07833 -0.0271 1.0000 0.1008
-7.250 -0.5224 0.08014 0.07552 -0.0258 1.0000 0.1057
-7.000 -0.5352 0.07623 0.07155 -0.0324 1.0000 0.1107
-6.750 -0.5332 0.07189 0.06726 -0.0315 1.0000 0.1138
-6.500 -0.5255 0.06918 0.06455 -0.0290 1.0000 0.1190
-6.250 -0.5277 0.06471 0.05990 -0.0331 1.0000 0.1271
-6.000 -0.5177 0.06192 0.05719 -0.0302 1.0000 0.1333
-5.750 -0.4750 0.04657 0.04223 -0.0271 1.0000 0.1480
-5.500 -0.5029 0.05477 0.04981 -0.0316 1.0000 0.1561
-5.250 -0.4920 0.05171 0.04667 -0.0311 1.0000 0.1703
-5.000 -0.4798 0.04884 0.04377 -0.0300 1.0000 0.1858
-4.750 -0.4678 0.04632 0.04118 -0.0292 1.0000 0.2122
-4.500 -0.4561 0.04415 0.03906 -0.0269 1.0000 0.2414
-4.250 -0.3906 0.03076 0.02308 -0.0350 1.0000 0.0814
-4.000 -0.3622 0.02797 0.01938 -0.0337 1.0000 0.0703
-3.750 -0.3371 0.02500 0.01612 -0.0332 1.0000 0.0686
-3.500 -0.3113 0.02301 0.01376 -0.0324 1.0000 0.0682
-3.250 -0.2855 0.02147 0.01191 -0.0317 1.0000 0.0721
-3.000 -0.2601 0.01998 0.01036 -0.0310 1.0000 0.0747
-2.750 -0.2350 0.01883 0.00916 -0.0301 1.0000 0.0780
-2.500 -0.2105 0.01790 0.00815 -0.0291 1.0000 0.0835
-2.250 -0.1867 0.01693 0.00728 -0.0283 1.0000 0.0961
-2.000 -0.1621 0.01577 0.00636 -0.0277 1.0000 0.1375
-1.750 -0.1367 0.01246 0.00624 -0.0248 1.0000 1.0000
-1.500 -0.1141 0.01251 0.00596 -0.0241 1.0000 1.0000
-1.250 -0.0914 0.01259 0.00578 -0.0235 1.0000 1.0000
-1.000 -0.0686 0.01269 0.00564 -0.0229 1.0000 1.0000
-0.750 -0.0459 0.01281 0.00558 -0.0223 1.0000 1.0000
-0.500 -0.0232 0.01296 0.00557 -0.0217 1.0000 1.0000
-0.250 -0.0006 0.01313 0.00561 -0.0212 1.0000 1.0000
0.000 0.0218 0.01332 0.00569 -0.0206 1.0000 1.0000
0.250 0.0441 0.01354 0.00579 -0.0200 1.0000 1.0000
0.500 0.0662 0.01378 0.00596 -0.0195 1.0000 1.0000
0.750 0.0881 0.01404 0.00617 -0.0189 1.0000 1.0000
1.000 0.1097 0.01433 0.00642 -0.0184 1.0000 1.0000
1.250 0.1311 0.01466 0.00672 -0.0178 1.0000 1.0000
1.500 0.1522 0.01501 0.00707 -0.0173 1.0000 1.0000
1.750 0.1729 0.01541 0.00747 -0.0168 1.0000 1.0000
2.000 0.1931 0.01584 0.00792 -0.0163 1.0000 1.0000
2.250 0.2247 0.01646 0.00859 -0.0181 0.9956 1.0000
2.500 0.2820 0.01723 0.00949 -0.0247 0.9805 1.0000
2.750 0.3387 0.01767 0.01007 -0.0308 0.9625 1.0000
3.000 0.4042 0.01778 0.01043 -0.0379 0.9436 1.0000
3.250 0.4620 0.01735 0.01024 -0.0428 0.9197 1.0000
3.500 0.5236 0.01640 0.00959 -0.0475 0.8933 1.0000
3.750 0.5902 0.01472 0.00831 -0.0519 0.8608 1.0000
4.000 0.6330 0.01354 0.00738 -0.0520 0.8037 1.0000
4.250 0.6889 0.01347 0.00628 -0.0534 0.5087 1.0000
4.500 0.6904 0.01616 0.00711 -0.0485 0.2322 1.0000
4.750 0.7048 0.01805 0.00836 -0.0461 0.1551 1.0000
5.000 0.7236 0.01955 0.00956 -0.0445 0.1226 1.0000
5.250 0.7470 0.02115 0.01110 -0.0434 0.1045 1.0000
5.500 0.7720 0.02271 0.01262 -0.0428 0.0904 1.0000
5.750 0.7995 0.02489 0.01474 -0.0427 0.0814 1.0000
6.000 0.8275 0.02680 0.01703 -0.0419 0.0767 1.0000
6.250 0.8529 0.02876 0.01915 -0.0413 0.0712 1.0000
6.500 0.8759 0.03162 0.02231 -0.0403 0.0671 1.0000
6.750 0.8972 0.03459 0.02583 -0.0386 0.0661 1.0000
7.000 0.9153 0.03818 0.02995 -0.0366 0.0663 1.0000
7.250 0.9294 0.04173 0.03407 -0.0341 0.0656 1.0000
7.500 0.9400 0.04547 0.03839 -0.0315 0.0647 1.0000
7.750 0.9498 0.05044 0.04368 -0.0295 0.0670 1.0000
9.250 0.9098 0.09175 0.08718 -0.0227 0.1351 1.0000
9.500 0.8707 0.09535 0.09084 -0.0236 0.1345 1.0000
9.750 0.8324 0.10193 0.09736 -0.0316 0.1332 1.0000
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Polar data table (+)
Polar graphs
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