AH 80-140 (ah80140-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 80-140 (ah80140-il) Reynolds number: 500,000 Max Cl/Cd: 113.23 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah80140-il-500000-n5.txt Download as CSV file: xf-ah80140-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 80-140
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.7416 0.03957 0.03501 -0.0816 0.5790 0.0149
-12.250 -0.7480 0.03726 0.03260 -0.0810 0.5760 0.0150
-12.000 -0.7598 0.03498 0.03015 -0.0785 0.5730 0.0151
-11.750 -0.7647 0.03310 0.02810 -0.0759 0.5702 0.0153
-11.500 -0.7601 0.03149 0.02631 -0.0740 0.5670 0.0154
-11.250 -0.7510 0.03009 0.02473 -0.0724 0.5641 0.0157
-11.000 -0.7415 0.02851 0.02296 -0.0708 0.5617 0.0160
-10.750 -0.7307 0.02690 0.02113 -0.0693 0.5594 0.0162
-10.500 -0.7157 0.02565 0.01967 -0.0679 0.5569 0.0165
-10.250 -0.7000 0.02438 0.01816 -0.0666 0.5545 0.0168
-10.000 -0.6820 0.02331 0.01687 -0.0654 0.5521 0.0171
-9.750 -0.6631 0.02239 0.01581 -0.0644 0.5498 0.0174
-9.500 -0.6423 0.02171 0.01505 -0.0634 0.5476 0.0177
-9.250 -0.6202 0.02116 0.01442 -0.0626 0.5455 0.0181
-9.000 -0.5976 0.02056 0.01374 -0.0619 0.5438 0.0185
-8.750 -0.5748 0.01995 0.01304 -0.0611 0.5421 0.0189
-8.500 -0.5520 0.01930 0.01226 -0.0603 0.5402 0.0193
-8.250 -0.5290 0.01862 0.01144 -0.0595 0.5383 0.0197
-8.000 -0.5054 0.01802 0.01070 -0.0588 0.5365 0.0200
-7.750 -0.4816 0.01743 0.01000 -0.0581 0.5346 0.0204
-7.500 -0.4577 0.01691 0.00944 -0.0574 0.5327 0.0209
-7.250 -0.4328 0.01655 0.00901 -0.0569 0.5307 0.0213
-7.000 -0.4078 0.01617 0.00856 -0.0563 0.5288 0.0218
-6.750 -0.3828 0.01577 0.00808 -0.0557 0.5272 0.0224
-6.500 -0.3574 0.01535 0.00759 -0.0551 0.5260 0.0229
-6.250 -0.3319 0.01495 0.00712 -0.0546 0.5246 0.0234
-6.000 -0.3065 0.01455 0.00667 -0.0540 0.5233 0.0239
-5.750 -0.2807 0.01423 0.00634 -0.0535 0.5218 0.0246
-5.500 -0.2545 0.01397 0.00605 -0.0531 0.5203 0.0253
-5.250 -0.2282 0.01371 0.00575 -0.0527 0.5188 0.0262
-5.000 -0.2019 0.01344 0.00542 -0.0522 0.5171 0.0271
-4.750 -0.1758 0.01317 0.00513 -0.0517 0.5152 0.0280
-4.500 -0.1494 0.01295 0.00488 -0.0513 0.5135 0.0290
-4.250 -0.1229 0.01275 0.00463 -0.0509 0.5118 0.0302
-4.000 -0.0965 0.01257 0.00439 -0.0505 0.5101 0.0316
-3.750 -0.0698 0.01239 0.00421 -0.0501 0.5087 0.0332
-3.500 -0.0427 0.01222 0.00402 -0.0498 0.5073 0.0354
-3.250 -0.0159 0.01202 0.00384 -0.0494 0.5059 0.0377
-3.000 0.0112 0.01187 0.00368 -0.0491 0.5045 0.0401
-2.750 0.0381 0.01170 0.00351 -0.0488 0.5031 0.0427
-2.500 0.0652 0.01157 0.00337 -0.0485 0.5017 0.0455
-2.250 0.0923 0.01143 0.00325 -0.0482 0.5003 0.0489
-2.000 0.1195 0.01132 0.00315 -0.0479 0.4989 0.0531
-1.750 0.1466 0.01122 0.00305 -0.0476 0.4974 0.0580
-1.500 0.1738 0.01111 0.00295 -0.0473 0.4957 0.0644
-1.250 0.2008 0.01101 0.00286 -0.0470 0.4942 0.0738
-1.000 0.2276 0.01090 0.00280 -0.0467 0.4927 0.0888
-0.750 0.2543 0.01080 0.00275 -0.0464 0.4911 0.1120
-0.500 0.2809 0.01062 0.00271 -0.0461 0.4897 0.1457
-0.250 0.3072 0.01041 0.00267 -0.0457 0.4878 0.1946
0.000 0.3331 0.01017 0.00264 -0.0453 0.4858 0.2597
0.250 0.3580 0.00987 0.00261 -0.0447 0.4839 0.3471
0.500 0.3809 0.00945 0.00260 -0.0438 0.4820 0.4787
0.750 0.4022 0.00905 0.00261 -0.0424 0.4803 0.6150
1.000 0.4232 0.00874 0.00266 -0.0408 0.4787 0.7235
1.250 0.4459 0.00854 0.00273 -0.0394 0.4772 0.8122
1.500 0.4752 0.00844 0.00279 -0.0393 0.4755 0.8819
1.750 0.5281 0.00845 0.00287 -0.0444 0.4736 0.9413
2.000 0.5890 0.00849 0.00292 -0.0513 0.4716 0.9701
2.250 0.6315 0.00854 0.00296 -0.0543 0.4693 0.9814
2.500 0.6695 0.00859 0.00300 -0.0564 0.4669 0.9889
2.750 0.7042 0.00865 0.00305 -0.0578 0.4648 0.9937
3.000 0.7379 0.00872 0.00309 -0.0591 0.4624 0.9996
3.250 0.7635 0.00878 0.00312 -0.0587 0.4600 1.0000
3.500 0.7877 0.00886 0.00316 -0.0579 0.4575 1.0000
3.750 0.8125 0.00892 0.00324 -0.0573 0.4552 1.0000
4.000 0.8376 0.00900 0.00333 -0.0567 0.4527 1.0000
4.250 0.8630 0.00907 0.00342 -0.0562 0.4499 1.0000
4.500 0.8884 0.00914 0.00349 -0.0556 0.4466 1.0000
4.750 0.9138 0.00921 0.00354 -0.0551 0.4433 1.0000
5.000 0.9393 0.00930 0.00362 -0.0547 0.4397 1.0000
5.250 0.9653 0.00937 0.00374 -0.0543 0.4351 1.0000
5.500 0.9910 0.00945 0.00383 -0.0539 0.4305 1.0000
5.750 1.0164 0.00955 0.00390 -0.0534 0.4257 1.0000
6.000 1.0424 0.00965 0.00404 -0.0531 0.4205 1.0000
6.250 1.0682 0.00975 0.00417 -0.0527 0.4153 1.0000
6.500 1.0934 0.00988 0.00428 -0.0522 0.4102 1.0000
6.750 1.1191 0.01001 0.00444 -0.0519 0.4035 1.0000
7.000 1.1441 0.01016 0.00459 -0.0514 0.3968 1.0000
7.250 1.1692 0.01033 0.00477 -0.0510 0.3901 1.0000
7.500 1.1934 0.01054 0.00496 -0.0504 0.3812 1.0000
7.750 1.2173 0.01078 0.00520 -0.0499 0.3701 1.0000
8.000 1.2406 0.01106 0.00546 -0.0492 0.3586 1.0000
8.250 1.2627 0.01142 0.00577 -0.0484 0.3422 1.0000
8.500 1.2844 0.01182 0.00613 -0.0476 0.3276 1.0000
8.750 1.3052 0.01228 0.00654 -0.0467 0.3120 1.0000
9.000 1.3256 0.01276 0.00698 -0.0458 0.2963 1.0000
9.250 1.3441 0.01336 0.00752 -0.0447 0.2762 1.0000
9.500 1.3600 0.01413 0.00819 -0.0433 0.2550 1.0000
9.750 1.3743 0.01498 0.00894 -0.0417 0.2308 1.0000
10.000 1.3851 0.01601 0.00987 -0.0399 0.2085 1.0000
10.250 1.3953 0.01704 0.01082 -0.0380 0.1902 1.0000
10.500 1.4024 0.01814 0.01189 -0.0358 0.1739 1.0000
10.750 1.4052 0.01942 0.01313 -0.0334 0.1616 1.0000
11.000 1.4061 0.02136 0.01509 -0.0325 0.1514 1.0000
11.250 1.4090 0.02388 0.01764 -0.0330 0.1416 1.0000
11.500 1.4110 0.02653 0.02032 -0.0334 0.1316 1.0000
11.750 1.4088 0.02950 0.02328 -0.0336 0.1211 1.0000
12.000 1.4054 0.03246 0.02623 -0.0335 0.1120 1.0000
12.250 1.4009 0.03546 0.02922 -0.0332 0.1032 1.0000
12.500 1.3981 0.03824 0.03202 -0.0329 0.0945 1.0000
12.750 1.3911 0.04142 0.03517 -0.0326 0.0839 1.0000
13.000 1.3848 0.04454 0.03827 -0.0323 0.0750 1.0000
13.250 1.3792 0.04761 0.04133 -0.0320 0.0676 1.0000
13.500 1.3757 0.05055 0.04428 -0.0318 0.0601 1.0000
13.750 1.3727 0.05358 0.04730 -0.0318 0.0525 1.0000
14.000 1.3683 0.05684 0.05054 -0.0319 0.0459 1.0000
14.250 1.3678 0.05974 0.05346 -0.0320 0.0420 1.0000
14.500 1.3674 0.06266 0.05641 -0.0321 0.0391 1.0000
14.750 1.3688 0.06544 0.05923 -0.0323 0.0365 1.0000
15.000 1.3689 0.06839 0.06222 -0.0325 0.0340 1.0000
15.250 1.3702 0.07125 0.06513 -0.0328 0.0320 1.0000
15.500 1.3717 0.07408 0.06801 -0.0330 0.0302 1.0000
15.750 1.3713 0.07722 0.07119 -0.0335 0.0289 1.0000
16.000 1.3727 0.08015 0.07418 -0.0339 0.0274 1.0000
16.250 1.3722 0.08338 0.07745 -0.0343 0.0260 1.0000
16.500 1.3718 0.08658 0.08071 -0.0349 0.0253 1.0000
16.750 1.3717 0.08982 0.08401 -0.0354 0.0245 1.0000
17.000 1.3717 0.09305 0.08731 -0.0361 0.0238 1.0000
17.250 1.3712 0.09641 0.09074 -0.0368 0.0232 1.0000
17.500 1.3694 0.09994 0.09433 -0.0376 0.0225 1.0000
17.750 1.3669 0.10362 0.09807 -0.0385 0.0219 1.0000
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Polar data table (+)
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