AH 88-K-136/16 (ah88k136-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 88-K-136/16 (ah88k136-il) Reynolds number: 100,000 Max Cl/Cd: 38.69 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah88k136-il-100000-n5.txt Download as CSV file: xf-ah88k136-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 88-K-136/16
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.2682 0.12143 0.11576 -0.0768 0.8658 0.0322
-12.500 -0.2668 0.11725 0.11161 -0.0789 0.8650 0.0323
-12.250 -0.2665 0.11313 0.10752 -0.0811 0.8640 0.0325
-12.000 -0.2613 0.10960 0.10400 -0.0823 0.8630 0.0322
-11.750 -0.2628 0.10518 0.09961 -0.0844 0.8619 0.0324
-11.500 -0.2599 0.10157 0.09602 -0.0857 0.8610 0.0321
-11.250 -0.2581 0.09792 0.09239 -0.0872 0.8602 0.0318
-11.000 -0.2567 0.09435 0.08883 -0.0885 0.8593 0.0313
-10.750 -0.2594 0.09014 0.08465 -0.0904 0.8585 0.0310
-10.500 -0.2641 0.08571 0.08027 -0.0925 0.8575 0.0307
-10.250 -0.2707 0.08104 0.07565 -0.0950 0.8562 0.0304
-10.000 -0.2821 0.07568 0.07034 -0.0985 0.8544 0.0301
-9.750 -0.2983 0.07052 0.06518 -0.1012 0.8524 0.0296
-9.500 -0.3184 0.06602 0.06062 -0.1016 0.8507 0.0293
-9.250 -0.3398 0.06213 0.05665 -0.0998 0.8488 0.0292
-9.000 -0.3602 0.05912 0.05353 -0.0964 0.8468 0.0288
-8.750 -0.3768 0.05603 0.05025 -0.0928 0.8447 0.0287
-8.500 -0.3893 0.05287 0.04687 -0.0892 0.8423 0.0287
-8.250 -0.3980 0.04983 0.04355 -0.0856 0.8401 0.0289
-8.000 -0.4021 0.04713 0.04052 -0.0820 0.8384 0.0295
-7.750 -0.4046 0.04442 0.03743 -0.0783 0.8362 0.0306
-7.500 -0.4058 0.04164 0.03410 -0.0742 0.8337 0.0319
-7.250 -0.4015 0.03916 0.03104 -0.0706 0.8316 0.0327
-7.000 -0.3906 0.03746 0.02916 -0.0685 0.8295 0.0336
-6.750 -0.3767 0.03614 0.02761 -0.0667 0.8276 0.0345
-6.500 -0.3603 0.03490 0.02612 -0.0650 0.8257 0.0360
-6.250 -0.3442 0.03384 0.02479 -0.0632 0.8233 0.0387
-6.000 -0.3255 0.03263 0.02316 -0.0617 0.8210 0.0412
-5.750 -0.3045 0.03147 0.02194 -0.0609 0.8193 0.0432
-5.500 -0.2823 0.03074 0.02108 -0.0602 0.8177 0.0463
-5.250 -0.2623 0.03012 0.02023 -0.0590 0.8150 0.0506
-5.000 -0.2417 0.02930 0.01939 -0.0581 0.8124 0.0539
-4.750 -0.2205 0.02881 0.01886 -0.0572 0.8104 0.0588
-4.500 -0.1972 0.02826 0.01818 -0.0565 0.8087 0.0650
-4.250 -0.1814 0.02794 0.01787 -0.0547 0.8056 0.0708
-4.000 -0.1659 0.02769 0.01756 -0.0528 0.8024 0.0783
-3.750 -0.1476 0.02739 0.01727 -0.0513 0.7999 0.0871
-3.500 -0.1266 0.02708 0.01695 -0.0501 0.7979 0.0998
-3.250 -0.1150 0.02698 0.01686 -0.0476 0.7941 0.1118
-3.000 -0.1022 0.02686 0.01679 -0.0452 0.7902 0.1296
-2.750 -0.0823 0.02660 0.01663 -0.0440 0.7874 0.1596
-2.500 0.0839 0.02476 0.01745 -0.0696 0.7932 0.8298
-2.250 0.0905 0.02544 0.01801 -0.0651 0.7891 0.8782
-2.000 0.1338 0.02634 0.01873 -0.0672 0.7875 0.9191
-1.750 0.2095 0.02693 0.01909 -0.0760 0.7872 0.9493
-1.500 0.2938 0.02694 0.01889 -0.0873 0.7871 0.9745
-1.250 0.3356 0.02690 0.01872 -0.0906 0.7854 0.9833
-1.000 0.3703 0.02686 0.01858 -0.0928 0.7827 0.9880
-0.750 0.3995 0.02699 0.01866 -0.0943 0.7782 0.9939
-0.500 0.4331 0.02693 0.01854 -0.0963 0.7750 0.9983
-0.250 0.4596 0.02695 0.01848 -0.0965 0.7723 1.0000
0.000 0.4748 0.02718 0.01868 -0.0948 0.7680 1.0000
0.250 0.4867 0.02749 0.01897 -0.0926 0.7621 1.0000
0.500 0.5072 0.02753 0.01898 -0.0914 0.7587 1.0000
0.750 0.5232 0.02771 0.01914 -0.0897 0.7542 1.0000
1.000 0.5343 0.02801 0.01945 -0.0873 0.7476 1.0000
1.250 0.5563 0.02797 0.01939 -0.0863 0.7443 1.0000
1.500 0.5666 0.02830 0.01973 -0.0837 0.7376 1.0000
1.750 0.5830 0.02841 0.01984 -0.0820 0.7322 1.0000
2.000 0.6077 0.02825 0.01969 -0.0812 0.7293 1.0000
2.250 0.6113 0.02875 0.02022 -0.0777 0.7203 1.0000
2.500 0.6345 0.02859 0.02008 -0.0767 0.7163 1.0000
3.000 0.6618 0.02885 0.02042 -0.0722 0.7030 1.0000
3.250 0.6892 0.02851 0.02012 -0.0718 0.7001 1.0000
3.500 0.6893 0.02903 0.02068 -0.0676 0.6892 1.0000
3.750 0.7173 0.02861 0.02032 -0.0672 0.6860 1.0000
4.000 0.7172 0.02910 0.02088 -0.0628 0.6750 1.0000
4.250 0.7458 0.02861 0.02046 -0.0625 0.6714 1.0000
4.500 0.7448 0.02905 0.02095 -0.0579 0.6601 1.0000
4.750 0.7746 0.02847 0.02046 -0.0577 0.6565 1.0000
5.000 0.7696 0.02886 0.02089 -0.0523 0.6445 1.0000
5.250 0.7973 0.02824 0.02039 -0.0516 0.6402 1.0000
5.500 0.7959 0.02853 0.02072 -0.0468 0.6285 1.0000
5.750 0.8007 0.02870 0.02096 -0.0430 0.6175 1.0000
6.000 0.8280 0.02800 0.02038 -0.0421 0.6119 1.0000
6.250 0.8336 0.02819 0.02065 -0.0385 0.5995 1.0000
6.500 0.8469 0.02811 0.02066 -0.0359 0.5884 1.0000
6.750 0.8768 0.02729 0.01996 -0.0353 0.5808 1.0000
7.250 0.9083 0.02700 0.01987 -0.0306 0.5536 1.0000
7.500 0.9309 0.02658 0.01957 -0.0291 0.5391 1.0000
7.750 0.9605 0.02575 0.01878 -0.0282 0.5180 1.0000
8.000 0.9777 0.02527 0.01809 -0.0253 0.4728 1.0000
8.250 0.9808 0.02561 0.01808 -0.0210 0.4193 1.0000
8.500 0.9781 0.02639 0.01858 -0.0164 0.3709 1.0000
8.750 0.9755 0.02733 0.01929 -0.0122 0.3312 1.0000
9.000 0.9707 0.02849 0.02019 -0.0080 0.2875 1.0000
9.250 0.9674 0.02970 0.02120 -0.0041 0.2473 1.0000
9.500 0.9612 0.03120 0.02239 -0.0003 0.1984 1.0000
9.750 0.9530 0.03301 0.02380 0.0036 0.1402 1.0000
10.000 0.9460 0.03495 0.02532 0.0070 0.0895 1.0000
10.250 0.9422 0.03682 0.02694 0.0101 0.0624 1.0000
10.500 0.9419 0.03849 0.02855 0.0127 0.0513 1.0000
10.750 0.9416 0.04023 0.03031 0.0151 0.0454 1.0000
11.000 0.9438 0.04181 0.03198 0.0172 0.0416 1.0000
11.250 0.9451 0.04353 0.03379 0.0193 0.0382 1.0000
11.500 0.9435 0.04557 0.03587 0.0213 0.0356 1.0000
11.750 0.9463 0.04734 0.03775 0.0230 0.0336 1.0000
12.000 0.9485 0.04921 0.03975 0.0247 0.0319 1.0000
12.250 0.9516 0.05105 0.04169 0.0262 0.0306 1.0000
12.500 0.9542 0.05299 0.04368 0.0276 0.0290 1.0000
12.750 0.9574 0.05494 0.04564 0.0291 0.0278 1.0000
13.000 0.9656 0.05653 0.04739 0.0303 0.0263 1.0000
13.250 0.9737 0.05818 0.04916 0.0314 0.0249 1.0000
13.500 0.9835 0.05979 0.05087 0.0326 0.0240 1.0000
13.750 0.9931 0.06148 0.05266 0.0337 0.0231 1.0000
14.000 1.0038 0.06322 0.05448 0.0347 0.0224 1.0000
14.250 1.0178 0.06504 0.05629 0.0357 0.0215 1.0000
14.500 1.0247 0.06732 0.05882 0.0366 0.0213 1.0000
14.750 1.0233 0.07028 0.06210 0.0374 0.0206 1.0000
15.000 1.0188 0.07350 0.06559 0.0378 0.0196 1.0000
15.250 1.0168 0.07685 0.06919 0.0383 0.0195 1.0000
15.500 1.0115 0.08049 0.07305 0.0384 0.0193 1.0000
15.750 1.0030 0.08441 0.07717 0.0380 0.0186 1.0000
16.000 0.9940 0.08865 0.08162 0.0375 0.0183 1.0000
16.250 0.9823 0.09349 0.08670 0.0364 0.0182 1.0000
16.500 0.9688 0.09875 0.09217 0.0349 0.0181 1.0000
16.750 0.9525 0.10474 0.09838 0.0328 0.0181 1.0000
17.000 0.9336 0.11155 0.10542 0.0299 0.0182 1.0000
17.250 0.9132 0.11913 0.11322 0.0262 0.0183 1.0000
17.500 0.8883 0.12828 0.12258 0.0212 0.0187 1.0000
17.750 0.8602 0.13917 0.13365 0.0150 0.0191 1.0000
18.000 0.8278 0.15275 0.14734 0.0073 0.0195 1.0000
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Polar data table (+)
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