AH 88-K-136/16 (ah88k136-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 88-K-136/16 (ah88k136-il) Reynolds number: 200,000 Max Cl/Cd: 73.32 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah88k136-il-200000.txt Download as CSV file: xf-ah88k136-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.2201 0.10549 0.10154 -0.0963 0.8894 0.0508
-11.500 -0.2287 0.10198 0.09808 -0.0997 0.8884 0.0512
-11.250 -0.2323 0.09828 0.09441 -0.1023 0.8876 0.0513
-11.000 -0.2366 0.09435 0.09052 -0.1049 0.8868 0.0514
-10.750 -0.2157 0.09048 0.08662 -0.1012 0.8865 0.0533
-10.500 -0.2065 0.08816 0.08431 -0.1009 0.8859 0.0550
-10.250 -0.2051 0.08506 0.08123 -0.1020 0.8852 0.0562
-10.000 -0.2075 0.08167 0.07788 -0.1035 0.8841 0.0575
-9.750 -0.2137 0.07800 0.07426 -0.1055 0.8827 0.0588
-9.500 -0.2272 0.07354 0.06985 -0.1089 0.8815 0.0596
-9.250 -0.2558 0.06928 0.06556 -0.1109 0.8800 0.0616
-9.000 -0.2748 0.06659 0.06282 -0.1092 0.8785 0.0618
-8.750 -0.3031 0.06532 0.06140 -0.1046 0.8764 0.0626
-8.500 -0.3279 0.06466 0.06047 -0.0998 0.8749 0.0633
-8.250 -0.2884 0.04658 0.04288 -0.0984 0.8725 0.0656
-8.000 -0.2741 0.04484 0.04120 -0.0977 0.8713 0.0683
-7.750 -0.2776 0.04260 0.03888 -0.0954 0.8700 0.0711
-7.500 -0.2899 0.04035 0.03640 -0.0917 0.8681 0.0749
-7.250 -0.3140 0.04009 0.03561 -0.0842 0.8656 0.0774
-7.000 -0.3686 0.03958 0.03355 -0.0766 0.8661 0.0414
-6.750 -0.3627 0.03773 0.03148 -0.0734 0.8641 0.0408
-6.500 -0.3602 0.03566 0.02912 -0.0695 0.8628 0.0407
-6.250 -0.3554 0.03441 0.02753 -0.0656 0.8608 0.0410
-6.000 -0.3431 0.03206 0.02496 -0.0635 0.8587 0.0431
-5.750 -0.4914 0.04008 0.03386 -0.0350 0.8916 0.0407
-5.500 -0.4694 0.03690 0.03020 -0.0340 0.8881 0.0405
-5.250 -0.4430 0.03401 0.02680 -0.0333 0.8774 0.0422
-5.000 -0.4132 0.03289 0.02559 -0.0338 0.8681 0.0449
-4.750 -0.3860 0.03165 0.02408 -0.0333 0.8607 0.0467
-4.500 -0.4525 0.03311 0.02568 -0.0187 0.8903 0.0456
-4.250 -0.4187 0.03193 0.02419 -0.0194 0.8804 0.0477
-4.000 -0.3823 0.03129 0.02324 -0.0204 0.8698 0.0518
-3.750 -0.3275 0.02980 0.02173 -0.0249 0.8543 0.0577
-3.500 -0.1929 0.02717 0.01896 -0.0419 0.8258 0.0779
-3.250 -0.1971 0.02709 0.01894 -0.0363 0.8196 0.0827
-3.000 -0.1530 0.02654 0.01842 -0.0392 0.8174 0.0998
-2.750 -0.1581 0.02672 0.01855 -0.0333 0.8100 0.1074
-2.500 -0.1213 0.02622 0.01819 -0.0349 0.8074 0.1351
-2.250 0.0032 0.02390 0.01903 -0.0532 0.8094 0.8764
-2.000 -0.0018 0.02479 0.01985 -0.0466 0.8022 0.9099
-1.750 0.1648 0.02593 0.02060 -0.0710 0.8082 0.9454
-1.500 0.2817 0.02607 0.02053 -0.0880 0.8086 0.9693
-1.250 0.3891 0.02537 0.01969 -0.1039 0.8086 0.9914
-1.000 0.4383 0.02510 0.01936 -0.1095 0.8042 1.0000
-0.750 0.4547 0.02527 0.01949 -0.1078 0.7995 1.0000
-0.500 0.4696 0.02551 0.01969 -0.1059 0.7944 1.0000
-0.250 0.4828 0.02575 0.01990 -0.1039 0.7884 1.0000
0.000 0.5057 0.02574 0.01984 -0.1028 0.7854 1.0000
0.250 0.5136 0.02613 0.02024 -0.1002 0.7777 1.0000
0.500 0.5344 0.02613 0.02020 -0.0990 0.7736 1.0000
0.750 0.5595 0.02602 0.02007 -0.0981 0.7713 1.0000
1.000 0.5658 0.02643 0.02049 -0.0953 0.7623 1.0000
1.250 0.5904 0.02626 0.02030 -0.0945 0.7591 1.0000
1.500 0.6174 0.02600 0.02003 -0.0938 0.7570 1.0000
1.750 0.6235 0.02642 0.02049 -0.0909 0.7473 1.0000
2.000 0.6499 0.02612 0.02018 -0.0903 0.7446 1.0000
2.250 0.6738 0.02590 0.01996 -0.0893 0.7411 1.0000
2.500 0.6853 0.02610 0.02020 -0.0870 0.7325 1.0000
2.750 0.7137 0.02561 0.01974 -0.0865 0.7300 1.0000
3.000 0.7404 0.02519 0.01934 -0.0858 0.7275 1.0000
3.250 0.7509 0.02542 0.01962 -0.0833 0.7177 1.0000
3.500 0.7810 0.02474 0.01900 -0.0830 0.7156 1.0000
3.750 0.8104 0.02406 0.01836 -0.0825 0.7137 1.0000
4.000 0.8211 0.02429 0.01866 -0.0800 0.7031 1.0000
4.250 0.8523 0.02341 0.01784 -0.0798 0.7010 1.0000
4.500 0.8663 0.02344 0.01794 -0.0776 0.6914 1.0000
4.750 0.8965 0.02254 0.01713 -0.0772 0.6883 1.0000
5.000 0.9292 0.02140 0.01607 -0.0770 0.6864 1.0000
5.250 0.9450 0.02130 0.01608 -0.0749 0.6764 1.0000
5.500 0.9765 0.02016 0.01504 -0.0745 0.6734 1.0000
5.750 1.0111 0.01879 0.01376 -0.0745 0.6709 1.0000
6.000 1.0325 0.01812 0.01320 -0.0728 0.6580 1.0000
6.250 1.0598 0.01686 0.01200 -0.0715 0.6378 1.0000
6.500 1.0861 0.01577 0.01085 -0.0700 0.6041 1.0000
6.750 1.1086 0.01512 0.00997 -0.0678 0.5577 1.0000
7.000 1.1194 0.01537 0.00992 -0.0644 0.5091 1.0000
7.250 1.1222 0.01606 0.01039 -0.0600 0.4654 1.0000
7.500 1.1157 0.01702 0.01110 -0.0543 0.4213 1.0000
7.750 1.1040 0.01798 0.01190 -0.0478 0.3862 1.0000
8.000 1.0836 0.01890 0.01268 -0.0400 0.3604 1.0000
8.250 1.0665 0.01997 0.01360 -0.0331 0.3312 1.0000
8.500 1.0482 0.02125 0.01465 -0.0264 0.2903 1.0000
8.750 1.0307 0.02265 0.01576 -0.0201 0.2442 1.0000
9.000 1.0062 0.02455 0.01719 -0.0131 0.1761 1.0000
9.250 0.9844 0.02663 0.01871 -0.0070 0.1038 1.0000
9.500 0.9688 0.02862 0.02033 -0.0017 0.0639 1.0000
9.750 0.9637 0.03014 0.02179 0.0023 0.0525 1.0000
10.000 0.9624 0.03149 0.02317 0.0056 0.0474 1.0000
10.250 0.9585 0.03312 0.02483 0.0090 0.0435 1.0000
10.500 0.9608 0.03443 0.02621 0.0116 0.0403 1.0000
10.750 0.9618 0.03591 0.02773 0.0142 0.0377 1.0000
11.000 0.9589 0.03782 0.02962 0.0170 0.0356 1.0000
11.250 0.9661 0.03911 0.03099 0.0190 0.0339 1.0000
11.500 0.9748 0.04038 0.03233 0.0208 0.0327 1.0000
11.750 0.9856 0.04159 0.03359 0.0225 0.0313 1.0000
12.000 0.9982 0.04278 0.03479 0.0240 0.0298 1.0000
12.250 1.0284 0.04404 0.03596 0.0247 0.0276 1.0000
12.500 1.0400 0.04532 0.03742 0.0261 0.0267 1.0000
12.750 1.0588 0.04675 0.03903 0.0272 0.0259 1.0000
13.000 1.0772 0.04851 0.04098 0.0283 0.0253 1.0000
13.250 1.0936 0.05067 0.04338 0.0294 0.0251 1.0000
13.500 1.1039 0.05327 0.04625 0.0309 0.0251 1.0000
13.750 1.1057 0.05580 0.04903 0.0326 0.0247 1.0000
14.000 1.1047 0.05830 0.05172 0.0342 0.0240 1.0000
14.250 1.0974 0.06222 0.05599 0.0361 0.0248 1.0000
14.500 1.0919 0.06463 0.05854 0.0374 0.0241 1.0000
14.750 1.0950 0.06674 0.06067 0.0381 0.0230 1.0000
15.000 1.0658 0.07221 0.06660 0.0398 0.0239 1.0000
15.250 1.0481 0.07663 0.07127 0.0405 0.0241 1.0000
15.500 1.0265 0.08205 0.07695 0.0406 0.0251 1.0000
15.750 1.0034 0.08770 0.08283 0.0400 0.0253 1.0000
16.000 0.9829 0.09352 0.08884 0.0388 0.0258 1.0000
16.250 0.9613 0.09974 0.09524 0.0368 0.0261 1.0000
16.500 0.9395 0.10653 0.10218 0.0343 0.0265 1.0000
16.750 0.9156 0.11404 0.10985 0.0306 0.0265 1.0000
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