AH 93-K-132/15 (ah93k132-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 93-K-132/15 (ah93k132-il) Reynolds number: 500,000 Max Cl/Cd: 99.14 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah93k132-il-500000-n5.txt Download as CSV file: xf-ah93k132-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 93-K-132/15
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4450 0.08594 0.08324 -0.0275 0.7809 0.0066
-9.000 -0.4506 0.07985 0.07718 -0.0327 0.7801 0.0066
-8.750 -0.4602 0.07267 0.07002 -0.0408 0.7784 0.0065
-8.500 -0.4726 0.06669 0.06399 -0.0443 0.7767 0.0065
-8.250 -0.4802 0.06015 0.05733 -0.0468 0.7754 0.0065
-8.000 -0.4859 0.05339 0.05036 -0.0477 0.7741 0.0064
-7.750 -0.4932 0.04518 0.04181 -0.0469 0.7729 0.0066
-7.500 -0.5081 0.03442 0.03035 -0.0431 0.7717 0.0067
-7.250 -0.5044 0.02905 0.02435 -0.0402 0.7707 0.0067
-7.000 -0.4913 0.02564 0.02041 -0.0382 0.7699 0.0067
-6.750 -0.4729 0.02328 0.01764 -0.0369 0.7692 0.0068
-6.500 -0.4517 0.02152 0.01555 -0.0359 0.7685 0.0068
-6.250 -0.4286 0.02016 0.01392 -0.0351 0.7679 0.0069
-6.000 -0.4058 0.01867 0.01218 -0.0343 0.7673 0.0071
-5.750 -0.3817 0.01766 0.01103 -0.0338 0.7667 0.0073
-5.500 -0.3547 0.01704 0.01036 -0.0341 0.7646 0.0076
-5.250 -0.3281 0.01650 0.00974 -0.0341 0.7628 0.0080
-5.000 -0.3018 0.01595 0.00913 -0.0340 0.7613 0.0084
-4.750 -0.2756 0.01541 0.00851 -0.0339 0.7599 0.0089
-4.500 -0.2494 0.01492 0.00795 -0.0337 0.7587 0.0095
-4.250 -0.2234 0.01444 0.00739 -0.0334 0.7577 0.0100
-4.000 -0.1974 0.01397 0.00689 -0.0332 0.7567 0.0109
-3.750 -0.1705 0.01367 0.00657 -0.0331 0.7559 0.0123
-3.500 -0.1436 0.01339 0.00623 -0.0331 0.7551 0.0136
-3.250 -0.1173 0.01296 0.00577 -0.0328 0.7543 0.0155
-3.000 -0.0905 0.01265 0.00542 -0.0327 0.7536 0.0176
-2.750 -0.0628 0.01242 0.00521 -0.0329 0.7515 0.0214
-2.500 -0.0347 0.01225 0.00507 -0.0332 0.7486 0.0275
-2.250 -0.0072 0.01202 0.00486 -0.0333 0.7466 0.0383
-2.000 0.0198 0.01174 0.00465 -0.0334 0.7450 0.0597
-1.750 0.0460 0.01133 0.00443 -0.0332 0.7436 0.1100
-1.500 0.0712 0.01083 0.00421 -0.0330 0.7424 0.1947
-1.250 0.0958 0.01028 0.00400 -0.0326 0.7412 0.2983
-1.000 0.1179 0.00956 0.00378 -0.0319 0.7402 0.4505
-0.750 0.1295 0.00839 0.00374 -0.0289 0.7372 0.7442
-0.500 0.1785 0.00839 0.00424 -0.0326 0.7351 0.9005
-0.250 0.2124 0.00865 0.00448 -0.0335 0.7328 0.9281
0.000 0.2403 0.00875 0.00453 -0.0334 0.7307 0.9409
0.250 0.2737 0.00877 0.00449 -0.0346 0.7291 0.9471
0.500 0.3035 0.00877 0.00444 -0.0349 0.7275 0.9540
0.750 0.3312 0.00887 0.00450 -0.0348 0.7255 0.9632
1.000 0.3790 0.00902 0.00465 -0.0393 0.7217 0.9668
1.250 0.4143 0.00902 0.00464 -0.0411 0.7185 0.9708
1.500 0.4415 0.00898 0.00456 -0.0410 0.7157 0.9746
1.750 0.4752 0.00883 0.00438 -0.0424 0.7135 0.9757
2.000 0.5086 0.00885 0.00441 -0.0440 0.7086 0.9767
2.250 0.5412 0.00878 0.00435 -0.0453 0.7037 0.9780
2.500 0.5725 0.00862 0.00416 -0.0461 0.6997 0.9795
2.750 0.6038 0.00864 0.00419 -0.0472 0.6924 0.9811
3.000 0.6332 0.00853 0.00405 -0.0477 0.6867 0.9831
3.250 0.6616 0.00854 0.00408 -0.0481 0.6791 0.9851
3.500 0.6937 0.00844 0.00395 -0.0492 0.6716 0.9858
3.750 0.7260 0.00841 0.00391 -0.0505 0.6612 0.9867
4.000 0.7580 0.00840 0.00388 -0.0517 0.6499 0.9878
4.250 0.7893 0.00843 0.00388 -0.0528 0.6370 0.9889
4.500 0.8198 0.00850 0.00390 -0.0537 0.6198 0.9900
4.750 0.8496 0.00866 0.00398 -0.0546 0.6004 0.9911
5.000 0.8794 0.00887 0.00414 -0.0555 0.5786 0.9924
5.250 0.9082 0.00925 0.00438 -0.0564 0.5469 0.9938
5.500 0.9371 0.00975 0.00473 -0.0576 0.5105 0.9948
5.750 0.9670 0.01025 0.00511 -0.0591 0.4785 0.9959
6.000 0.9956 0.01093 0.00563 -0.0605 0.4397 0.9972
6.250 1.0227 0.01170 0.00624 -0.0619 0.3987 0.9987
6.500 1.0463 0.01260 0.00695 -0.0627 0.3563 1.0000
6.750 1.0570 0.01356 0.00774 -0.0609 0.3195 1.0000
7.000 1.0629 0.01448 0.00852 -0.0581 0.2883 1.0000
7.250 1.0615 0.01533 0.00926 -0.0538 0.2632 1.0000
7.500 1.0529 0.01601 0.00985 -0.0478 0.2432 1.0000
7.750 1.0481 0.01679 0.01051 -0.0426 0.2184 1.0000
8.000 1.0455 0.01765 0.01121 -0.0381 0.1883 1.0000
8.250 1.0449 0.01855 0.01195 -0.0340 0.1593 1.0000
8.500 1.0471 0.01941 0.01267 -0.0305 0.1331 1.0000
8.750 1.0513 0.02026 0.01341 -0.0274 0.1114 1.0000
9.000 1.0576 0.02107 0.01414 -0.0247 0.0935 1.0000
9.250 1.0653 0.02185 0.01487 -0.0222 0.0788 1.0000
9.500 1.0744 0.02264 0.01562 -0.0200 0.0666 1.0000
9.750 1.0839 0.02348 0.01642 -0.0181 0.0558 1.0000
10.000 1.0942 0.02434 0.01725 -0.0163 0.0464 1.0000
10.250 1.1050 0.02523 0.01811 -0.0147 0.0386 1.0000
10.500 1.1167 0.02611 0.01900 -0.0133 0.0327 1.0000
10.750 1.1281 0.02705 0.01996 -0.0119 0.0273 1.0000
11.000 1.1387 0.02808 0.02099 -0.0105 0.0225 1.0000
11.250 1.1505 0.02906 0.02201 -0.0093 0.0194 1.0000
11.500 1.1610 0.03019 0.02315 -0.0081 0.0166 1.0000
11.750 1.1728 0.03127 0.02429 -0.0071 0.0150 1.0000
12.000 1.1838 0.03244 0.02551 -0.0060 0.0135 1.0000
12.250 1.1935 0.03374 0.02685 -0.0049 0.0120 1.0000
12.500 1.2034 0.03507 0.02826 -0.0040 0.0111 1.0000
12.750 1.2140 0.03636 0.02963 -0.0031 0.0103 1.0000
13.000 1.2234 0.03779 0.03113 -0.0022 0.0096 1.0000
13.250 1.2318 0.03933 0.03273 -0.0013 0.0089 1.0000
13.500 1.2377 0.04113 0.03461 -0.0003 0.0083 1.0000
13.750 1.2442 0.04294 0.03650 0.0005 0.0079 1.0000
14.000 1.2520 0.04466 0.03832 0.0011 0.0075 1.0000
14.250 1.2591 0.04647 0.04023 0.0018 0.0071 1.0000
14.500 1.2656 0.04838 0.04223 0.0023 0.0067 1.0000
14.750 1.2716 0.05041 0.04435 0.0028 0.0064 1.0000
15.000 1.2758 0.05265 0.04667 0.0032 0.0060 1.0000
15.250 1.2773 0.05522 0.04933 0.0036 0.0058 1.0000
15.500 1.2763 0.05816 0.05237 0.0040 0.0055 1.0000
15.750 1.2789 0.06075 0.05509 0.0041 0.0054 1.0000
16.000 1.2804 0.06356 0.05801 0.0042 0.0052 1.0000
16.250 1.2808 0.06653 0.06110 0.0041 0.0051 1.0000
16.500 1.2802 0.06969 0.06438 0.0039 0.0049 1.0000
16.750 1.2788 0.07302 0.06784 0.0036 0.0048 1.0000
17.000 1.2766 0.07655 0.07148 0.0031 0.0046 1.0000
17.250 1.2736 0.08027 0.07532 0.0024 0.0045 1.0000
17.500 1.2699 0.08413 0.07930 0.0017 0.0044 1.0000
17.750 1.2652 0.08821 0.08350 0.0007 0.0043 1.0000
18.000 1.2598 0.09250 0.08792 -0.0005 0.0042 1.0000
18.250 1.2535 0.09702 0.09256 -0.0018 0.0041 1.0000
18.500 1.2464 0.10175 0.09742 -0.0034 0.0041 1.0000
18.750 1.2384 0.10668 0.10247 -0.0051 0.0040 1.0000
19.000 1.2293 0.11192 0.10784 -0.0071 0.0039 1.0000
19.250 1.2195 0.11740 0.11343 -0.0093 0.0039 1.0000
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