AH 80-140 (ah80140-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 80-140 (ah80140-il) Reynolds number: 1,000,000 Max Cl/Cd: 149.19 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah80140-il-1000000.txt Download as CSV file: xf-ah80140-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.7873 0.04740 0.04377 -0.0761 0.6075 0.0146
-13.500 -0.8089 0.03938 0.03554 -0.0850 0.6029 0.0147
-13.250 -0.8321 0.03471 0.03064 -0.0870 0.5992 0.0147
-13.000 -0.8239 0.03375 0.02969 -0.0862 0.5940 0.0150
-12.750 -0.8306 0.03187 0.02766 -0.0839 0.5896 0.0150
-12.500 -0.8362 0.03036 0.02601 -0.0805 0.5851 0.0151
-12.250 -0.8255 0.02953 0.02513 -0.0788 0.5815 0.0153
-12.000 -0.8150 0.02850 0.02400 -0.0771 0.5782 0.0155
-11.750 -0.8068 0.02708 0.02242 -0.0752 0.5750 0.0157
-11.500 -0.7929 0.02611 0.02133 -0.0737 0.5717 0.0159
-11.250 -0.7762 0.02536 0.02046 -0.0725 0.5683 0.0163
-11.000 -0.7619 0.02425 0.01917 -0.0709 0.5644 0.0166
-10.750 -0.7456 0.02320 0.01796 -0.0696 0.5627 0.0168
-10.500 -0.7239 0.02276 0.01741 -0.0686 0.5605 0.0171
-10.250 -0.7058 0.02180 0.01629 -0.0674 0.5584 0.0172
-10.000 -0.6921 0.02017 0.01452 -0.0658 0.5562 0.0178
-9.750 -0.6693 0.01978 0.01411 -0.0650 0.5538 0.0182
-9.500 -0.6473 0.01921 0.01345 -0.0641 0.5515 0.0185
-9.250 -0.6247 0.01870 0.01284 -0.0633 0.5487 0.0188
-9.000 -0.6024 0.01813 0.01215 -0.0624 0.5459 0.0192
-8.750 -0.5790 0.01754 0.01148 -0.0616 0.5447 0.0196
-8.500 -0.5550 0.01705 0.01089 -0.0609 0.5432 0.0200
-8.250 -0.5306 0.01659 0.01033 -0.0602 0.5414 0.0202
-8.000 -0.5093 0.01558 0.00921 -0.0592 0.5398 0.0208
-7.750 -0.4851 0.01508 0.00868 -0.0585 0.5381 0.0212
-7.500 -0.4597 0.01475 0.00832 -0.0580 0.5364 0.0217
-7.250 -0.4343 0.01443 0.00794 -0.0574 0.5347 0.0222
-7.000 -0.4091 0.01405 0.00748 -0.0568 0.5330 0.0226
-6.750 -0.3837 0.01370 0.00707 -0.0562 0.5310 0.0231
-6.500 -0.3579 0.01345 0.00673 -0.0556 0.5288 0.0235
-6.250 -0.3336 0.01292 0.00615 -0.0549 0.5272 0.0241
-6.000 -0.3080 0.01255 0.00577 -0.0544 0.5263 0.0247
-5.750 -0.2816 0.01230 0.00551 -0.0539 0.5249 0.0254
-5.500 -0.2552 0.01202 0.00521 -0.0535 0.5234 0.0260
-5.250 -0.2288 0.01177 0.00492 -0.0530 0.5218 0.0266
-5.000 -0.2019 0.01157 0.00467 -0.0526 0.5202 0.0273
-4.750 -0.1764 0.01119 0.00429 -0.0520 0.5188 0.0283
-4.500 -0.1496 0.01100 0.00409 -0.0516 0.5171 0.0291
-4.250 -0.1225 0.01086 0.00392 -0.0513 0.5157 0.0304
-4.000 -0.0956 0.01071 0.00373 -0.0509 0.5142 0.0315
-3.750 -0.0693 0.01050 0.00352 -0.0504 0.5125 0.0331
-3.500 -0.0422 0.01042 0.00341 -0.0501 0.5105 0.0349
-3.250 -0.0156 0.01026 0.00324 -0.0497 0.5089 0.0372
-3.000 0.0117 0.01011 0.00310 -0.0494 0.5082 0.0398
-2.750 0.0387 0.00992 0.00293 -0.0490 0.5073 0.0433
-2.500 0.0662 0.00981 0.00281 -0.0488 0.5061 0.0464
-2.250 0.0934 0.00966 0.00269 -0.0485 0.5047 0.0505
-2.000 0.1208 0.00955 0.00259 -0.0482 0.5033 0.0542
-1.750 0.1484 0.00945 0.00251 -0.0479 0.5018 0.0583
-1.500 0.1757 0.00933 0.00241 -0.0477 0.5003 0.0644
-1.250 0.2030 0.00921 0.00231 -0.0474 0.4985 0.0735
-1.000 0.2298 0.00906 0.00223 -0.0470 0.4967 0.0925
-0.750 0.2563 0.00891 0.00218 -0.0466 0.4949 0.1258
-0.500 0.2818 0.00872 0.00217 -0.0462 0.4927 0.1892
-0.250 0.3064 0.00846 0.00220 -0.0455 0.4909 0.2828
0.000 0.3301 0.00805 0.00216 -0.0447 0.4901 0.4031
0.250 0.3516 0.00756 0.00215 -0.0435 0.4891 0.5599
0.500 0.3731 0.00721 0.00216 -0.0420 0.4879 0.6780
0.750 0.3951 0.00697 0.00220 -0.0405 0.4865 0.7659
1.000 0.4187 0.00682 0.00223 -0.0393 0.4850 0.8293
1.250 0.4450 0.00671 0.00226 -0.0387 0.4833 0.8822
1.500 0.4789 0.00665 0.00228 -0.0397 0.4815 0.9217
1.750 0.5248 0.00665 0.00230 -0.0435 0.4796 0.9484
2.000 0.5799 0.00670 0.00232 -0.0493 0.4775 0.9684
2.250 0.6247 0.00684 0.00240 -0.0529 0.4745 0.9797
2.500 0.6678 0.00689 0.00245 -0.0560 0.4726 0.9881
2.750 0.7110 0.00692 0.00248 -0.0591 0.4707 0.9939
3.000 0.7510 0.00695 0.00250 -0.0617 0.4686 0.9985
3.250 0.7856 0.00697 0.00251 -0.0631 0.4663 1.0000
3.500 0.8088 0.00697 0.00250 -0.0621 0.4637 1.0000
3.750 0.8323 0.00700 0.00251 -0.0612 0.4608 1.0000
4.000 0.8559 0.00711 0.00258 -0.0604 0.4575 1.0000
4.250 0.8809 0.00712 0.00261 -0.0597 0.4551 1.0000
4.500 0.9062 0.00714 0.00265 -0.0591 0.4523 1.0000
4.750 0.9317 0.00717 0.00269 -0.0586 0.4491 1.0000
5.000 0.9573 0.00722 0.00272 -0.0581 0.4458 1.0000
5.250 0.9825 0.00732 0.00279 -0.0576 0.4416 1.0000
5.500 1.0089 0.00736 0.00286 -0.0573 0.4382 1.0000
5.750 1.0354 0.00740 0.00293 -0.0570 0.4341 1.0000
6.000 1.0616 0.00747 0.00300 -0.0566 0.4300 1.0000
6.250 1.0873 0.00759 0.00309 -0.0562 0.4250 1.0000
6.500 1.1142 0.00764 0.00318 -0.0561 0.4194 1.0000
6.750 1.1403 0.00774 0.00327 -0.0558 0.4129 1.0000
7.000 1.1663 0.00785 0.00338 -0.0555 0.4045 1.0000
7.250 1.1916 0.00801 0.00351 -0.0551 0.3955 1.0000
7.500 1.2174 0.00816 0.00366 -0.0548 0.3865 1.0000
7.750 1.2422 0.00838 0.00385 -0.0543 0.3765 1.0000
8.000 1.2672 0.00860 0.00405 -0.0539 0.3671 1.0000
8.250 1.2923 0.00881 0.00426 -0.0536 0.3580 1.0000
8.500 1.3163 0.00910 0.00452 -0.0530 0.3456 1.0000
8.750 1.3397 0.00944 0.00481 -0.0525 0.3313 1.0000
9.000 1.3625 0.00982 0.00514 -0.0519 0.3171 1.0000
9.250 1.3847 0.01024 0.00551 -0.0512 0.2998 1.0000
9.500 1.4062 0.01072 0.00592 -0.0504 0.2804 1.0000
9.750 1.4258 0.01132 0.00643 -0.0494 0.2589 1.0000
10.000 1.4442 0.01201 0.00701 -0.0483 0.2366 1.0000
10.250 1.4596 0.01288 0.00774 -0.0469 0.2109 1.0000
10.500 1.4756 0.01368 0.00846 -0.0456 0.1911 1.0000
10.750 1.4897 0.01457 0.00925 -0.0441 0.1708 1.0000
11.000 1.5015 0.01558 0.01016 -0.0425 0.1538 1.0000
11.250 1.5134 0.01653 0.01106 -0.0409 0.1400 1.0000
11.500 1.5178 0.01767 0.01215 -0.0383 0.1255 1.0000
11.750 1.5170 0.01931 0.01377 -0.0362 0.1127 1.0000
12.000 1.5148 0.02214 0.01660 -0.0365 0.1020 1.0000
12.250 1.5120 0.02538 0.01984 -0.0372 0.0898 1.0000
12.500 1.5032 0.02902 0.02344 -0.0373 0.0772 1.0000
12.750 1.4956 0.03236 0.02678 -0.0370 0.0687 1.0000
13.000 1.4879 0.03564 0.03005 -0.0367 0.0603 1.0000
13.250 1.4766 0.03921 0.03359 -0.0362 0.0509 1.0000
13.500 1.4674 0.04258 0.03696 -0.0358 0.0449 1.0000
13.750 1.4632 0.04549 0.03989 -0.0355 0.0411 1.0000
14.000 1.4583 0.04850 0.04292 -0.0352 0.0372 1.0000
14.250 1.4572 0.05131 0.04577 -0.0351 0.0350 1.0000
14.500 1.4563 0.05412 0.04861 -0.0350 0.0323 1.0000
14.750 1.4564 0.05692 0.05144 -0.0351 0.0305 1.0000
15.000 1.4558 0.05982 0.05438 -0.0352 0.0288 1.0000
15.250 1.4580 0.06243 0.05703 -0.0353 0.0274 1.0000
15.500 1.4585 0.06530 0.05995 -0.0354 0.0268 1.0000
15.750 1.4592 0.06814 0.06282 -0.0356 0.0256 1.0000
16.000 1.4572 0.07141 0.06614 -0.0360 0.0247 1.0000
16.250 1.4593 0.07413 0.06892 -0.0362 0.0241 1.0000
16.500 1.4599 0.07712 0.07198 -0.0366 0.0236 1.0000
16.750 1.4592 0.08030 0.07520 -0.0370 0.0229 1.0000
17.000 1.4574 0.08366 0.07862 -0.0375 0.0224 1.0000
17.250 1.4538 0.08727 0.08228 -0.0381 0.0219 1.0000
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