AH 80-140 (ah80140-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 80-140 (ah80140-il) Reynolds number: 500,000 Max Cl/Cd: 116.37 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah80140-il-500000.txt Download as CSV file: xf-ah80140-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2615 0.08922 0.08519 -0.0485 0.5764 0.0320
-9.500 -0.2545 0.08663 0.08260 -0.0493 0.5746 0.0323
-9.250 -0.3936 0.05302 0.04901 -0.0732 0.5783 0.0273
-9.000 -0.3995 0.05146 0.04744 -0.0715 0.5765 0.0275
-8.750 -0.4034 0.04881 0.04472 -0.0709 0.5746 0.0276
-8.500 -0.4043 0.04613 0.04193 -0.0701 0.5729 0.0278
-8.250 -0.4274 0.03875 0.03417 -0.0685 0.5718 0.0263
-8.000 -0.4584 0.02887 0.02331 -0.0647 0.5712 0.0262
-7.750 -0.4519 0.02529 0.01905 -0.0623 0.5695 0.0270
-7.500 -0.4359 0.02321 0.01657 -0.0608 0.5677 0.0275
-7.250 -0.4135 0.02231 0.01560 -0.0602 0.5654 0.0281
-7.000 -0.3899 0.02161 0.01483 -0.0596 0.5637 0.0286
-6.750 -0.3664 0.02076 0.01386 -0.0589 0.5623 0.0292
-6.500 -0.3427 0.01989 0.01282 -0.0581 0.5606 0.0300
-6.250 -0.3186 0.01906 0.01177 -0.0573 0.5588 0.0309
-6.000 -0.2942 0.01815 0.01067 -0.0566 0.5570 0.0315
-5.750 -0.2692 0.01734 0.00985 -0.0561 0.5550 0.0323
-5.500 -0.2436 0.01682 0.00927 -0.0557 0.5530 0.0330
-5.250 -0.2177 0.01632 0.00870 -0.0551 0.5511 0.0339
-5.000 -0.1917 0.01585 0.00812 -0.0546 0.5493 0.0349
-4.750 -0.1658 0.01541 0.00756 -0.0541 0.5473 0.0361
-4.500 -0.1403 0.01498 0.00715 -0.0536 0.5455 0.0373
-4.250 -0.1140 0.01461 0.00678 -0.0532 0.5442 0.0386
-4.000 -0.0877 0.01426 0.00639 -0.0527 0.5426 0.0402
-3.750 -0.0624 0.01376 0.00589 -0.0521 0.5409 0.0418
-3.500 -0.0362 0.01347 0.00562 -0.0516 0.5392 0.0440
-3.250 -0.0100 0.01319 0.00530 -0.0511 0.5376 0.0467
-3.000 0.0163 0.01294 0.00509 -0.0507 0.5361 0.0500
-2.750 0.0426 0.01269 0.00482 -0.0503 0.5345 0.0540
-2.500 0.0696 0.01256 0.00468 -0.0499 0.5329 0.0583
-2.250 0.0960 0.01235 0.00448 -0.0495 0.5313 0.0630
-2.000 0.1227 0.01225 0.00435 -0.0491 0.5294 0.0686
-1.750 0.1493 0.01222 0.00432 -0.0488 0.5274 0.0750
-1.500 0.1758 0.01201 0.00418 -0.0484 0.5262 0.0850
-1.250 0.2021 0.01179 0.00407 -0.0480 0.5248 0.1055
-1.000 0.2272 0.01145 0.00398 -0.0474 0.5231 0.1628
-0.750 0.2505 0.01094 0.00391 -0.0467 0.5209 0.2876
-0.500 0.2712 0.01030 0.00384 -0.0454 0.5189 0.4631
-0.250 0.2889 0.00968 0.00385 -0.0433 0.5169 0.6515
0.000 0.3089 0.00935 0.00390 -0.0413 0.5152 0.7722
0.250 0.3342 0.00921 0.00394 -0.0403 0.5134 0.8496
0.500 0.3679 0.00920 0.00401 -0.0411 0.5115 0.9048
0.750 0.4131 0.00941 0.00420 -0.0445 0.5091 0.9410
1.000 0.4639 0.00943 0.00422 -0.0491 0.5075 0.9621
1.250 0.5104 0.00950 0.00427 -0.0528 0.5056 0.9775
1.500 0.5586 0.00958 0.00432 -0.0569 0.5033 0.9870
1.750 0.6163 0.00963 0.00432 -0.0630 0.5006 0.9974
2.000 0.6515 0.00965 0.00430 -0.0646 0.4984 1.0000
2.250 0.6737 0.00969 0.00430 -0.0635 0.4965 1.0000
2.500 0.6964 0.00976 0.00432 -0.0625 0.4946 1.0000
2.750 0.7194 0.00990 0.00441 -0.0616 0.4924 1.0000
3.000 0.7423 0.01003 0.00454 -0.0606 0.4900 1.0000
3.250 0.7656 0.01004 0.00458 -0.0597 0.4876 1.0000
3.500 0.7896 0.01009 0.00464 -0.0589 0.4850 1.0000
3.750 0.8141 0.01015 0.00470 -0.0582 0.4826 1.0000
4.000 0.8392 0.01020 0.00474 -0.0576 0.4802 1.0000
4.250 0.8648 0.01024 0.00475 -0.0571 0.4779 1.0000
4.500 0.8905 0.01033 0.00480 -0.0566 0.4752 1.0000
4.750 0.9156 0.01044 0.00493 -0.0561 0.4723 1.0000
5.000 0.9409 0.01045 0.00499 -0.0555 0.4690 1.0000
5.250 0.9666 0.01045 0.00501 -0.0551 0.4654 1.0000
5.500 0.9928 0.01045 0.00499 -0.0547 0.4621 1.0000
5.750 1.0191 0.01048 0.00498 -0.0543 0.4587 1.0000
6.000 1.0447 0.01056 0.00511 -0.0539 0.4551 1.0000
6.250 1.0703 0.01061 0.00522 -0.0535 0.4514 1.0000
6.500 1.0963 0.01064 0.00527 -0.0531 0.4475 1.0000
6.750 1.1224 0.01066 0.00529 -0.0527 0.4436 1.0000
7.000 1.1480 0.01076 0.00540 -0.0524 0.4395 1.0000
7.250 1.1735 0.01081 0.00554 -0.0519 0.4345 1.0000
7.500 1.1992 0.01084 0.00559 -0.0516 0.4291 1.0000
7.750 1.2245 0.01090 0.00566 -0.0511 0.4227 1.0000
8.000 1.2498 0.01096 0.00577 -0.0507 0.4149 1.0000
8.250 1.2745 0.01105 0.00588 -0.0502 0.4062 1.0000
8.500 1.2990 0.01119 0.00602 -0.0497 0.3973 1.0000
8.750 1.3231 0.01137 0.00623 -0.0492 0.3879 1.0000
9.000 1.3461 0.01163 0.00647 -0.0485 0.3781 1.0000
9.250 1.3691 0.01190 0.00676 -0.0479 0.3670 1.0000
9.500 1.3916 0.01221 0.00708 -0.0472 0.3551 1.0000
9.750 1.4126 0.01261 0.00746 -0.0463 0.3404 1.0000
10.000 1.4326 0.01307 0.00789 -0.0454 0.3255 1.0000
10.250 1.4511 0.01362 0.00841 -0.0442 0.3092 1.0000
10.500 1.4680 0.01426 0.00902 -0.0430 0.2909 1.0000
10.750 1.4820 0.01507 0.00975 -0.0414 0.2711 1.0000
11.000 1.4938 0.01598 0.01060 -0.0396 0.2508 1.0000
11.250 1.5012 0.01712 0.01167 -0.0375 0.2292 1.0000
11.500 1.5005 0.01851 0.01298 -0.0344 0.2117 1.0000
11.750 1.4976 0.02041 0.01488 -0.0325 0.1973 1.0000
12.000 1.4938 0.02339 0.01786 -0.0328 0.1829 1.0000
12.250 1.4903 0.02659 0.02106 -0.0332 0.1700 1.0000
12.500 1.4834 0.02998 0.02444 -0.0333 0.1584 1.0000
12.750 1.4765 0.03323 0.02770 -0.0331 0.1484 1.0000
13.000 1.4672 0.03665 0.03109 -0.0328 0.1374 1.0000
13.250 1.4585 0.03998 0.03440 -0.0325 0.1259 1.0000
13.750 1.4390 0.04686 0.04123 -0.0318 0.1043 1.0000
14.000 1.4281 0.05053 0.04486 -0.0316 0.0911 1.0000
14.250 1.4180 0.05429 0.04856 -0.0316 0.0782 1.0000
14.500 1.4076 0.05823 0.05245 -0.0317 0.0675 1.0000
14.750 1.3993 0.06201 0.05618 -0.0318 0.0574 1.0000
15.000 1.3907 0.06591 0.06005 -0.0321 0.0500 1.0000
15.250 1.3857 0.06950 0.06365 -0.0324 0.0458 1.0000
15.500 1.3805 0.07313 0.06731 -0.0328 0.0428 1.0000
15.750 1.3775 0.07657 0.07080 -0.0332 0.0406 1.0000
16.000 1.3697 0.08069 0.07494 -0.0338 0.0385 1.0000
16.250 1.3693 0.08391 0.07824 -0.0342 0.0367 1.0000
16.500 1.3682 0.08721 0.08161 -0.0348 0.0356 1.0000
16.750 1.3629 0.09117 0.08561 -0.0355 0.0343 1.0000
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