AH 81-131 (ah81131-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 81-131 (ah81131-il) Reynolds number: 200,000 Max Cl/Cd: 72.21 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah81131-il-200000.txt Download as CSV file: xf-ah81131-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: AH 81-131
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3713 0.09213 0.08889 -0.0439 0.8335 0.0392
-9.000 -0.3753 0.08643 0.08323 -0.0514 0.8312 0.0403
-8.750 -0.3822 0.08111 0.07788 -0.0579 0.8291 0.0404
-8.500 -0.3959 0.07741 0.07407 -0.0605 0.8269 0.0408
-8.250 -0.4120 0.07526 0.07174 -0.0596 0.8249 0.0411
-8.000 -0.4215 0.07350 0.06976 -0.0580 0.8230 0.0415
-7.750 -0.3618 0.05363 0.05031 -0.0643 0.8174 0.0438
-7.500 -0.3574 0.05033 0.04698 -0.0640 0.8153 0.0450
-7.250 -0.3570 0.04717 0.04373 -0.0630 0.8132 0.0463
-7.000 -0.3580 0.04409 0.04051 -0.0612 0.8111 0.0479
-6.750 -0.3574 0.04104 0.03728 -0.0593 0.8094 0.0501
-6.500 -0.3511 0.04063 0.03621 -0.0577 0.8057 0.0547
-6.000 -0.3658 0.04687 0.04190 -0.0545 0.8050 0.0576
-5.750 -0.3497 0.04482 0.03979 -0.0541 0.8027 0.0606
-5.250 -0.3273 0.04112 0.03556 -0.0495 0.7982 0.0724
-5.000 -0.3129 0.04038 0.03456 -0.0468 0.7965 0.0799
-4.750 -0.2965 0.03809 0.03218 -0.0472 0.7930 0.0884
-4.500 -0.2820 0.03682 0.03075 -0.0460 0.7899 0.1012
-4.250 -0.2424 0.03179 0.02460 -0.0422 0.7878 0.0368
-4.000 -0.2155 0.02993 0.02220 -0.0403 0.7858 0.0307
-3.750 -0.1905 0.02905 0.02113 -0.0392 0.7842 0.0300
-3.500 -0.1651 0.02727 0.01929 -0.0385 0.7831 0.0327
-3.250 -0.1429 0.02683 0.01883 -0.0392 0.7785 0.0339
-3.000 -0.1213 0.02613 0.01808 -0.0383 0.7753 0.0340
-2.750 -0.1012 0.02551 0.01741 -0.0367 0.7729 0.0348
-2.500 -0.0816 0.02506 0.01691 -0.0350 0.7712 0.0362
-2.250 -0.0617 0.02472 0.01648 -0.0330 0.7699 0.0393
-1.750 0.1232 0.02262 0.01752 -0.0532 0.7705 0.9490
-1.500 0.1617 0.02305 0.01782 -0.0563 0.7676 0.9590
-1.250 0.2102 0.02347 0.01810 -0.0617 0.7643 0.9666
-1.000 0.2554 0.02368 0.01820 -0.0658 0.7620 0.9749
-0.750 0.2980 0.02371 0.01813 -0.0692 0.7599 0.9833
-0.500 0.3409 0.02339 0.01770 -0.0720 0.7578 0.9891
-0.250 0.3791 0.02299 0.01721 -0.0736 0.7561 0.9954
0.000 0.4205 0.02318 0.01738 -0.0784 0.7482 1.0000
0.250 0.4377 0.02312 0.01728 -0.0767 0.7451 1.0000
0.500 0.4548 0.02301 0.01711 -0.0746 0.7432 1.0000
0.750 0.4732 0.02381 0.01793 -0.0752 0.7361 1.0000
1.000 0.4916 0.02389 0.01798 -0.0739 0.7326 1.0000
1.250 0.5109 0.02380 0.01786 -0.0721 0.7304 1.0000
1.500 0.5305 0.02365 0.01769 -0.0702 0.7289 1.0000
1.750 0.5452 0.02466 0.01874 -0.0704 0.7197 1.0000
2.000 0.5661 0.02452 0.01858 -0.0688 0.7174 1.0000
2.250 0.5878 0.02429 0.01835 -0.0671 0.7158 1.0000
2.500 0.5998 0.02527 0.01938 -0.0665 0.7065 1.0000
2.750 0.6226 0.02503 0.01916 -0.0651 0.7041 1.0000
3.000 0.6461 0.02469 0.01884 -0.0636 0.7025 1.0000
3.250 0.6572 0.02559 0.01978 -0.0624 0.6929 1.0000
3.500 0.6833 0.02498 0.01920 -0.0611 0.6906 1.0000
3.750 0.7074 0.02441 0.01869 -0.0596 0.6868 1.0000
4.000 0.7270 0.02427 0.01860 -0.0582 0.6788 1.0000
4.250 0.7544 0.02340 0.01777 -0.0568 0.6769 1.0000
4.500 0.7790 0.02281 0.01724 -0.0554 0.6739 1.0000
4.750 0.7993 0.02263 0.01714 -0.0541 0.6654 1.0000
5.000 0.8309 0.02076 0.01534 -0.0523 0.6635 1.0000
5.250 0.8607 0.01897 0.01359 -0.0503 0.6618 1.0000
5.500 0.8825 0.01869 0.01343 -0.0493 0.6513 1.0000
5.750 0.9081 0.01767 0.01250 -0.0478 0.6429 1.0000
6.000 0.9370 0.01596 0.01085 -0.0459 0.6356 1.0000
6.250 0.9609 0.01535 0.01036 -0.0447 0.6184 1.0000
6.500 0.9846 0.01497 0.01008 -0.0437 0.6004 1.0000
6.750 1.0085 0.01453 0.00968 -0.0424 0.5781 1.0000
7.000 1.0304 0.01427 0.00936 -0.0409 0.5396 1.0000
7.250 1.0452 0.01455 0.00926 -0.0384 0.4656 1.0000
7.500 1.0451 0.01599 0.01023 -0.0349 0.3894 1.0000
7.750 1.0312 0.01792 0.01174 -0.0300 0.3160 1.0000
8.000 1.0070 0.01948 0.01299 -0.0228 0.2701 1.0000
8.250 0.9843 0.02128 0.01439 -0.0162 0.2144 1.0000
8.500 0.9651 0.02334 0.01597 -0.0107 0.1491 1.0000
8.750 0.9554 0.02518 0.01749 -0.0066 0.1142 1.0000
9.000 0.9538 0.02670 0.01888 -0.0035 0.1001 1.0000
9.250 0.9576 0.02797 0.02015 -0.0011 0.0903 1.0000
9.500 0.9629 0.02920 0.02139 0.0010 0.0820 1.0000
9.750 0.9674 0.03054 0.02267 0.0030 0.0730 1.0000
10.000 0.9769 0.03156 0.02372 0.0044 0.0639 1.0000
10.250 0.9857 0.03268 0.02491 0.0060 0.0577 1.0000
10.500 0.9898 0.03418 0.02639 0.0077 0.0496 1.0000
10.750 0.9979 0.03552 0.02781 0.0093 0.0327 1.0000
11.000 0.9971 0.03760 0.02987 0.0115 0.0251 1.0000
11.250 1.0029 0.03922 0.03156 0.0131 0.0220 1.0000
11.500 1.0045 0.04128 0.03366 0.0150 0.0195 1.0000
11.750 1.0108 0.04312 0.03559 0.0169 0.0182 1.0000
12.000 1.0215 0.04458 0.03718 0.0183 0.0171 1.0000
12.250 1.0305 0.04610 0.03881 0.0193 0.0154 1.0000
12.500 1.0388 0.04779 0.04061 0.0205 0.0143 1.0000
12.750 1.0498 0.04957 0.04253 0.0219 0.0141 1.0000
13.000 1.0576 0.05165 0.04475 0.0231 0.0135 1.0000
13.250 1.0649 0.05394 0.04722 0.0244 0.0132 1.0000
13.500 1.0694 0.05668 0.05017 0.0256 0.0129 1.0000
13.750 1.0695 0.06001 0.05376 0.0268 0.0128 1.0000
14.000 1.0664 0.06347 0.05747 0.0277 0.0128 1.0000
14.250 1.0592 0.06734 0.06159 0.0284 0.0128 1.0000
14.500 1.0479 0.07173 0.06623 0.0288 0.0127 1.0000
14.750 1.0350 0.07642 0.07120 0.0287 0.0129 1.0000
15.000 1.0184 0.08184 0.07692 0.0280 0.0132 1.0000
15.250 1.0005 0.08765 0.08295 0.0267 0.0132 1.0000
15.500 0.9769 0.09493 0.09051 0.0244 0.0135 1.0000
15.750 0.9468 0.10407 0.09994 0.0207 0.0141 1.0000
16.000 0.9181 0.11373 0.10982 0.0158 0.0143 1.0000
16.250 0.8852 0.12560 0.12190 0.0092 0.0148 1.0000
16.500 0.8499 0.14009 0.13652 0.0008 0.0154 1.0000
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Polar data table (+)
Polar graphs
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