AH 80-140 (ah80140-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 80-140 (ah80140-il) Reynolds number: 1,000,000 Max Cl/Cd: 139 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah80140-il-1000000-n5.txt Download as CSV file: xf-ah80140-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.9856 0.03944 0.03535 -0.0855 0.5927 0.0112
-15.000 -0.9974 0.03522 0.03094 -0.0884 0.5880 0.0113
-14.750 -1.0056 0.03241 0.02796 -0.0886 0.5835 0.0114
-14.500 -1.0087 0.03051 0.02593 -0.0872 0.5796 0.0115
-14.250 -1.0083 0.02909 0.02439 -0.0849 0.5758 0.0115
-14.000 -1.0059 0.02793 0.02311 -0.0822 0.5716 0.0117
-13.750 -1.0024 0.02674 0.02179 -0.0796 0.5677 0.0117
-13.500 -0.9912 0.02576 0.02069 -0.0778 0.5640 0.0118
-13.250 -0.9804 0.02465 0.01948 -0.0760 0.5611 0.0120
-13.000 -0.9647 0.02386 0.01862 -0.0746 0.5577 0.0122
-12.750 -0.9481 0.02309 0.01777 -0.0733 0.5541 0.0123
-12.500 -0.9306 0.02236 0.01694 -0.0720 0.5503 0.0125
-12.000 -0.8916 0.02112 0.01554 -0.0698 0.5444 0.0129
-11.750 -0.8716 0.02048 0.01482 -0.0687 0.5421 0.0131
-11.500 -0.8505 0.01993 0.01419 -0.0677 0.5397 0.0133
-11.250 -0.8282 0.01947 0.01365 -0.0669 0.5373 0.0136
-11.000 -0.8068 0.01889 0.01297 -0.0659 0.5348 0.0138
-10.750 -0.7846 0.01837 0.01236 -0.0650 0.5324 0.0140
-10.500 -0.7614 0.01796 0.01185 -0.0643 0.5299 0.0142
-10.000 -0.7169 0.01683 0.01056 -0.0625 0.5263 0.0147
-9.750 -0.6935 0.01635 0.01004 -0.0617 0.5249 0.0149
-9.500 -0.6696 0.01593 0.00957 -0.0610 0.5234 0.0152
-9.250 -0.6452 0.01554 0.00912 -0.0603 0.5217 0.0154
-9.000 -0.6206 0.01517 0.00870 -0.0597 0.5201 0.0157
-8.750 -0.5957 0.01482 0.00829 -0.0591 0.5185 0.0160
-8.500 -0.5705 0.01452 0.00793 -0.0585 0.5168 0.0164
-8.250 -0.5453 0.01419 0.00754 -0.0579 0.5150 0.0167
-8.000 -0.5200 0.01389 0.00717 -0.0573 0.5132 0.0170
-7.750 -0.4945 0.01360 0.00681 -0.0567 0.5111 0.0172
-7.500 -0.4697 0.01322 0.00637 -0.0561 0.5092 0.0175
-7.250 -0.4442 0.01287 0.00600 -0.0555 0.5084 0.0178
-7.000 -0.4183 0.01258 0.00569 -0.0550 0.5074 0.0183
-6.750 -0.3921 0.01232 0.00540 -0.0546 0.5064 0.0187
-6.500 -0.3657 0.01208 0.00513 -0.0541 0.5053 0.0192
-6.250 -0.3393 0.01183 0.00485 -0.0537 0.5041 0.0195
-6.000 -0.3129 0.01160 0.00459 -0.0532 0.5029 0.0199
-5.750 -0.2862 0.01140 0.00434 -0.0528 0.5016 0.0203
-5.500 -0.2599 0.01115 0.00407 -0.0524 0.5000 0.0208
-5.250 -0.2333 0.01093 0.00384 -0.0520 0.4982 0.0214
-5.000 -0.2065 0.01075 0.00363 -0.0516 0.4964 0.0221
-4.750 -0.1797 0.01059 0.00345 -0.0512 0.4947 0.0229
-4.500 -0.1528 0.01045 0.00327 -0.0508 0.4927 0.0236
-4.250 -0.1260 0.01030 0.00311 -0.0504 0.4911 0.0246
-4.000 -0.0987 0.01015 0.00296 -0.0501 0.4903 0.0259
-3.750 -0.0713 0.01002 0.00282 -0.0498 0.4894 0.0272
-3.500 -0.0440 0.00988 0.00270 -0.0495 0.4885 0.0291
-3.250 -0.0165 0.00977 0.00259 -0.0493 0.4875 0.0311
-3.000 0.0109 0.00965 0.00248 -0.0490 0.4863 0.0332
-2.750 0.0386 0.00956 0.00238 -0.0488 0.4852 0.0355
-2.500 0.0660 0.00944 0.00228 -0.0485 0.4838 0.0381
-2.250 0.0936 0.00936 0.00219 -0.0483 0.4824 0.0403
-2.000 0.1211 0.00926 0.00209 -0.0480 0.4807 0.0427
-1.750 0.1486 0.00918 0.00201 -0.0477 0.4792 0.0452
-1.500 0.1760 0.00910 0.00194 -0.0475 0.4776 0.0486
-1.250 0.2034 0.00903 0.00188 -0.0472 0.4757 0.0537
-1.000 0.2307 0.00897 0.00184 -0.0470 0.4736 0.0617
-0.750 0.2584 0.00887 0.00178 -0.0468 0.4723 0.0704
-0.500 0.2858 0.00876 0.00174 -0.0466 0.4709 0.0849
-0.250 0.3130 0.00864 0.00170 -0.0463 0.4695 0.1097
0.000 0.3401 0.00852 0.00167 -0.0460 0.4681 0.1394
0.250 0.3670 0.00838 0.00165 -0.0457 0.4666 0.1749
0.500 0.3935 0.00823 0.00164 -0.0454 0.4651 0.2243
0.750 0.4197 0.00806 0.00163 -0.0450 0.4635 0.2829
1.000 0.4450 0.00783 0.00162 -0.0445 0.4618 0.3658
1.250 0.4683 0.00749 0.00163 -0.0436 0.4600 0.4915
1.500 0.4919 0.00725 0.00165 -0.0427 0.4579 0.5902
1.750 0.5154 0.00703 0.00169 -0.0417 0.4563 0.6749
2.000 0.5369 0.00679 0.00175 -0.0401 0.4549 0.7720
2.250 0.5595 0.00659 0.00182 -0.0388 0.4533 0.8532
2.500 0.5901 0.00649 0.00188 -0.0391 0.4509 0.9093
2.750 0.6578 0.00648 0.00193 -0.0477 0.4472 0.9609
3.000 0.7052 0.00654 0.00196 -0.0519 0.4444 0.9723
3.250 0.7429 0.00661 0.00201 -0.0540 0.4418 0.9799
3.500 0.7779 0.00666 0.00206 -0.0555 0.4391 0.9847
3.750 0.8114 0.00671 0.00210 -0.0567 0.4352 0.9886
4.000 0.8446 0.00677 0.00215 -0.0578 0.4310 0.9926
4.250 0.8757 0.00688 0.00223 -0.0585 0.4259 0.9993
4.500 0.9054 0.00695 0.00229 -0.0589 0.4218 1.0000
4.750 0.9306 0.00702 0.00236 -0.0584 0.4166 1.0000
5.000 0.9557 0.00712 0.00244 -0.0578 0.4110 1.0000
5.250 0.9812 0.00722 0.00253 -0.0573 0.4048 1.0000
5.500 1.0065 0.00734 0.00262 -0.0569 0.3971 1.0000
5.750 1.0320 0.00748 0.00274 -0.0564 0.3904 1.0000
6.000 1.0576 0.00762 0.00287 -0.0560 0.3838 1.0000
6.250 1.0828 0.00779 0.00301 -0.0555 0.3763 1.0000
6.500 1.1079 0.00798 0.00318 -0.0551 0.3666 1.0000
6.750 1.1331 0.00817 0.00335 -0.0547 0.3576 1.0000
7.000 1.1570 0.00846 0.00358 -0.0541 0.3419 1.0000
7.250 1.1808 0.00877 0.00382 -0.0535 0.3273 1.0000
7.500 1.2044 0.00909 0.00410 -0.0529 0.3133 1.0000
7.750 1.2274 0.00947 0.00440 -0.0523 0.2964 1.0000
8.000 1.2500 0.00988 0.00474 -0.0516 0.2781 1.0000
8.250 1.2723 0.01031 0.00510 -0.0509 0.2617 1.0000
8.500 1.2924 0.01091 0.00559 -0.0499 0.2390 1.0000
8.750 1.3108 0.01162 0.00616 -0.0487 0.2122 1.0000
9.000 1.3303 0.01223 0.00668 -0.0478 0.1951 1.0000
9.250 1.3481 0.01296 0.00730 -0.0466 0.1725 1.0000
9.500 1.3648 0.01373 0.00797 -0.0454 0.1541 1.0000
9.750 1.3834 0.01435 0.00854 -0.0444 0.1417 1.0000
10.000 1.4007 0.01503 0.00918 -0.0433 0.1287 1.0000
10.500 1.4275 0.01682 0.01084 -0.0404 0.1021 1.0000
10.750 1.4342 0.01788 0.01186 -0.0381 0.0895 1.0000
11.000 1.4352 0.01939 0.01334 -0.0360 0.0775 1.0000
11.250 1.4361 0.02185 0.01582 -0.0362 0.0692 1.0000
11.500 1.4373 0.02472 0.01871 -0.0369 0.0600 1.0000
11.750 1.4342 0.02787 0.02184 -0.0372 0.0499 1.0000
12.000 1.4332 0.03065 0.02463 -0.0371 0.0446 1.0000
12.250 1.4352 0.03305 0.02706 -0.0369 0.0416 1.0000
12.500 1.4335 0.03576 0.02979 -0.0367 0.0379 1.0000
12.750 1.4350 0.03814 0.03221 -0.0364 0.0354 1.0000
13.000 1.4346 0.04067 0.03478 -0.0361 0.0328 1.0000
13.250 1.4349 0.04316 0.03729 -0.0358 0.0300 1.0000
13.500 1.4342 0.04575 0.03992 -0.0355 0.0277 1.0000
13.750 1.4348 0.04822 0.04242 -0.0353 0.0260 1.0000
14.000 1.4353 0.05086 0.04508 -0.0352 0.0242 1.0000
14.250 1.4391 0.05318 0.04746 -0.0351 0.0237 1.0000
14.500 1.4409 0.05574 0.05005 -0.0351 0.0223 1.0000
14.750 1.4424 0.05843 0.05277 -0.0352 0.0216 1.0000
15.000 1.4464 0.06082 0.05521 -0.0353 0.0210 1.0000
15.250 1.4483 0.06351 0.05795 -0.0354 0.0201 1.0000
15.500 1.4518 0.06602 0.06051 -0.0356 0.0200 1.0000
15.750 1.4535 0.06876 0.06329 -0.0358 0.0192 1.0000
16.000 1.4540 0.07171 0.06630 -0.0361 0.0187 1.0000
16.250 1.4553 0.07453 0.06916 -0.0363 0.0182 1.0000
16.500 1.4574 0.07734 0.07204 -0.0367 0.0179 1.0000
16.750 1.4596 0.08014 0.07490 -0.0371 0.0175 1.0000
17.000 1.4612 0.08304 0.07785 -0.0375 0.0172 1.0000
17.250 1.4615 0.08614 0.08101 -0.0380 0.0169 1.0000
17.500 1.4626 0.08912 0.08405 -0.0385 0.0165 1.0000
17.750 1.4610 0.09256 0.08755 -0.0392 0.0162 1.0000
18.000 1.4609 0.09577 0.09081 -0.0398 0.0159 1.0000
18.250 1.4577 0.09949 0.09459 -0.0407 0.0156 1.0000
18.500 1.4578 0.10269 0.09785 -0.0414 0.0152 1.0000
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Polar data table (+)
Polar graphs
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