AH21 7% version (Andrew Hollom) (ah21-7-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH21 7% version (Andrew Hollom) (ah21-7-il) Reynolds number: 100,000 Max Cl/Cd: 55.45 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah21-7-il-100000.txt Download as CSV file: xf-ah21-7-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4816 0.09336 0.08851 -0.0277 1.0000 0.1168
-8.000 -0.4965 0.09094 0.08618 -0.0274 1.0000 0.1203
-7.750 -0.5265 0.08856 0.08393 -0.0284 1.0000 0.1221
-7.500 -0.5630 0.08470 0.08002 -0.0350 1.0000 0.1234
-7.250 -0.5349 0.08139 0.07686 -0.0271 1.0000 0.1272
-7.000 -0.5345 0.07861 0.07410 -0.0258 1.0000 0.1318
-6.750 -0.5622 0.07354 0.06886 -0.0329 1.0000 0.1388
-6.500 -0.5471 0.07081 0.06628 -0.0280 1.0000 0.1419
-6.000 -0.5434 0.06392 0.05930 -0.0281 1.0000 0.1566
-5.750 -0.5405 0.06031 0.05552 -0.0295 1.0000 0.1692
-5.500 -0.5292 0.05778 0.05303 -0.0270 1.0000 0.1752
-5.250 -0.5204 0.05461 0.04979 -0.0269 1.0000 0.1882
-5.000 -0.4798 0.03870 0.03131 -0.0356 1.0000 0.0811
-4.750 -0.4595 0.03452 0.02697 -0.0355 1.0000 0.0791
-4.500 -0.4363 0.03130 0.02338 -0.0351 1.0000 0.0759
-4.250 -0.4108 0.02843 0.01994 -0.0345 1.0000 0.0726
-4.000 -0.3853 0.02631 0.01733 -0.0338 1.0000 0.0716
-3.750 -0.3607 0.02472 0.01546 -0.0330 1.0000 0.0724
-3.500 -0.3368 0.02360 0.01415 -0.0322 1.0000 0.0764
-3.250 -0.3124 0.02265 0.01295 -0.0312 1.0000 0.0802
-3.000 -0.2885 0.02125 0.01158 -0.0304 1.0000 0.0841
-2.750 -0.2651 0.02036 0.01071 -0.0295 1.0000 0.0914
-2.500 -0.2420 0.01951 0.00996 -0.0287 1.0000 0.1063
-2.250 -0.2180 0.01832 0.00905 -0.0281 1.0000 0.1514
-2.000 -0.2000 0.01574 0.00895 -0.0264 1.0000 0.6135
-1.750 -0.1941 0.01534 0.00938 -0.0196 1.0000 0.8729
-1.500 -0.1524 0.01520 0.00903 -0.0226 1.0000 1.0000
-1.250 -0.1304 0.01534 0.00890 -0.0221 1.0000 1.0000
-1.000 -0.1083 0.01553 0.00886 -0.0217 1.0000 1.0000
-0.750 -0.0863 0.01575 0.00889 -0.0213 1.0000 1.0000
-0.500 -0.0645 0.01600 0.00896 -0.0208 1.0000 1.0000
-0.250 -0.0429 0.01629 0.00910 -0.0204 1.0000 1.0000
0.000 -0.0214 0.01660 0.00928 -0.0199 1.0000 1.0000
0.250 -0.0002 0.01695 0.00952 -0.0194 1.0000 1.0000
0.500 0.0207 0.01732 0.00979 -0.0190 1.0000 1.0000
0.750 0.0414 0.01773 0.01013 -0.0185 1.0000 1.0000
1.000 0.0757 0.01844 0.01076 -0.0208 0.9953 1.0000
1.250 0.1224 0.01930 0.01155 -0.0253 0.9852 1.0000
1.500 0.1665 0.01997 0.01219 -0.0293 0.9741 1.0000
1.750 0.2094 0.02053 0.01274 -0.0329 0.9622 1.0000
2.000 0.2520 0.02100 0.01321 -0.0362 0.9500 1.0000
2.250 0.2957 0.02135 0.01360 -0.0396 0.9373 1.0000
2.500 0.3405 0.02157 0.01387 -0.0430 0.9241 1.0000
2.750 0.3858 0.02162 0.01400 -0.0462 0.9102 1.0000
3.000 0.4322 0.02145 0.01393 -0.0493 0.8954 1.0000
3.250 0.4796 0.02106 0.01367 -0.0523 0.8802 1.0000
3.500 0.5291 0.02035 0.01312 -0.0551 0.8642 1.0000
3.750 0.5800 0.01935 0.01230 -0.0578 0.8481 1.0000
4.000 0.6337 0.01792 0.01109 -0.0604 0.8316 1.0000
4.250 0.6726 0.01679 0.01015 -0.0605 0.8073 1.0000
4.500 0.7210 0.01547 0.00903 -0.0619 0.7736 1.0000
4.750 0.7638 0.01463 0.00823 -0.0627 0.7117 1.0000
5.000 0.8079 0.01457 0.00763 -0.0637 0.5717 1.0000
5.250 0.8193 0.01581 0.00795 -0.0599 0.4150 1.0000
5.500 0.8249 0.01743 0.00870 -0.0559 0.2926 1.0000
5.750 0.8361 0.01900 0.00967 -0.0530 0.2207 1.0000
6.000 0.8522 0.02041 0.01072 -0.0511 0.1803 1.0000
6.250 0.8717 0.02178 0.01186 -0.0497 0.1542 1.0000
6.500 0.8946 0.02310 0.01314 -0.0488 0.1351 1.0000
6.750 0.9191 0.02449 0.01447 -0.0483 0.1206 1.0000
7.000 0.9474 0.02621 0.01617 -0.0484 0.1101 1.0000
7.250 0.9757 0.02809 0.01793 -0.0488 0.1004 1.0000
7.500 1.0012 0.02965 0.01984 -0.0480 0.0939 1.0000
7.750 1.0293 0.03194 0.02209 -0.0484 0.0879 1.0000
8.000 1.0493 0.03381 0.02441 -0.0467 0.0831 1.0000
8.250 1.0705 0.03611 0.02706 -0.0455 0.0797 1.0000
8.500 1.0911 0.03853 0.02967 -0.0445 0.0766 1.0000
8.750 1.1063 0.04217 0.03358 -0.0431 0.0737 1.0000
9.000 1.1133 0.04474 0.03677 -0.0397 0.0719 1.0000
9.250 1.1183 0.04837 0.04092 -0.0365 0.0713 1.0000
9.500 1.1189 0.05235 0.04537 -0.0331 0.0712 1.0000
9.750 1.1150 0.05635 0.04980 -0.0295 0.0710 1.0000
10.000 1.1067 0.06039 0.05422 -0.0258 0.0710 1.0000
10.250 1.0937 0.06449 0.05865 -0.0222 0.0711 1.0000
10.500 1.0767 0.06845 0.06286 -0.0185 0.0715 1.0000
10.750 1.0577 0.07243 0.06702 -0.0151 0.0721 1.0000
11.000 1.0429 0.07693 0.07165 -0.0130 0.0729 1.0000
11.250 0.9638 0.08709 0.08223 -0.0131 0.0848 1.0000
11.500 0.9610 0.09277 0.08793 -0.0137 0.0864 1.0000
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Polar data table (+)
Polar graphs
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