AH 88-K-136/16 (ah88k136-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 88-K-136/16 (ah88k136-il) Reynolds number: 200,000 Max Cl/Cd: 72.32 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah88k136-il-200000-n5.txt Download as CSV file: xf-ah88k136-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.3216 0.08290 0.07869 -0.0843 0.8088 0.0160
-10.750 -0.3396 0.07618 0.07203 -0.0876 0.8080 0.0160
-10.500 -0.3655 0.06777 0.06369 -0.0935 0.8066 0.0159
-10.250 -0.3901 0.06178 0.05765 -0.0955 0.8045 0.0157
-10.000 -0.4171 0.05666 0.05244 -0.0944 0.8025 0.0156
-9.750 -0.4498 0.05137 0.04695 -0.0905 0.8008 0.0155
-9.500 -0.4831 0.04713 0.04245 -0.0843 0.7992 0.0154
-9.250 -0.5198 0.04128 0.03601 -0.0771 0.7978 0.0157
-9.000 -0.5312 0.03765 0.03186 -0.0722 0.7965 0.0159
-8.750 -0.5316 0.03487 0.02866 -0.0686 0.7943 0.0163
-8.500 -0.5182 0.03408 0.02781 -0.0669 0.7926 0.0168
-8.250 -0.5030 0.03351 0.02714 -0.0654 0.7911 0.0176
-8.000 -0.4902 0.03211 0.02548 -0.0634 0.7897 0.0184
-7.750 -0.4771 0.03020 0.02316 -0.0612 0.7884 0.0193
-7.500 -0.4606 0.02838 0.02090 -0.0594 0.7871 0.0202
-7.250 -0.4413 0.02700 0.01928 -0.0581 0.7860 0.0209
-7.000 -0.4210 0.02629 0.01849 -0.0571 0.7849 0.0219
-6.750 -0.3999 0.02582 0.01791 -0.0561 0.7841 0.0235
-6.500 -0.3770 0.02501 0.01690 -0.0556 0.7822 0.0252
-6.250 -0.3540 0.02406 0.01582 -0.0551 0.7803 0.0265
-6.000 -0.3318 0.02346 0.01519 -0.0544 0.7784 0.0279
-5.750 -0.3091 0.02294 0.01461 -0.0538 0.7766 0.0299
-5.500 -0.2856 0.02253 0.01405 -0.0531 0.7752 0.0325
-5.250 -0.2638 0.02196 0.01349 -0.0523 0.7739 0.0352
-5.000 -0.2412 0.02155 0.01303 -0.0515 0.7728 0.0380
-4.750 -0.2185 0.02115 0.01255 -0.0506 0.7717 0.0419
-4.500 -0.1962 0.02078 0.01216 -0.0496 0.7707 0.0463
-4.250 -0.1751 0.02063 0.01196 -0.0488 0.7679 0.0510
-4.000 -0.1547 0.02038 0.01176 -0.0479 0.7653 0.0572
-3.750 -0.1328 0.02019 0.01152 -0.0470 0.7630 0.0642
-3.500 -0.1112 0.01993 0.01128 -0.0460 0.7612 0.0739
-3.250 -0.0893 0.01970 0.01107 -0.0450 0.7597 0.0849
-3.000 -0.0669 0.01945 0.01085 -0.0441 0.7584 0.1008
-2.750 -0.0444 0.01920 0.01063 -0.0432 0.7573 0.1218
-2.500 -0.0254 0.01908 0.01063 -0.0419 0.7544 0.1518
-2.250 -0.0085 0.01894 0.01068 -0.0404 0.7505 0.1976
-2.000 0.0068 0.01844 0.01056 -0.0384 0.7479 0.2944
-1.750 0.0078 0.01731 0.01036 -0.0333 0.7456 0.5294
-1.500 0.1345 0.01767 0.01182 -0.0518 0.7473 0.8829
-1.250 0.1690 0.01815 0.01221 -0.0525 0.7459 0.9060
-1.000 0.2122 0.01853 0.01249 -0.0552 0.7448 0.9219
-0.750 0.2635 0.01882 0.01269 -0.0595 0.7440 0.9349
-0.500 0.3139 0.01901 0.01279 -0.0639 0.7433 0.9470
-0.250 0.3492 0.01912 0.01286 -0.0659 0.7405 0.9521
0.000 0.3688 0.01935 0.01308 -0.0649 0.7356 0.9580
0.250 0.4039 0.01923 0.01291 -0.0667 0.7332 0.9600
0.500 0.4371 0.01903 0.01268 -0.0680 0.7313 0.9623
0.750 0.4684 0.01879 0.01241 -0.0687 0.7297 0.9650
1.000 0.4974 0.01854 0.01213 -0.0690 0.7284 0.9679
1.250 0.5187 0.01895 0.01258 -0.0687 0.7210 0.9720
1.500 0.5514 0.01873 0.01236 -0.0700 0.7183 0.9737
1.750 0.5832 0.01842 0.01206 -0.0709 0.7163 0.9756
2.000 0.6144 0.01805 0.01168 -0.0715 0.7148 0.9776
2.500 0.6648 0.01818 0.01190 -0.0716 0.7042 0.9830
2.750 0.6958 0.01777 0.01152 -0.0722 0.7019 0.9844
3.000 0.7279 0.01729 0.01107 -0.0730 0.7001 0.9858
3.250 0.7540 0.01756 0.01142 -0.0736 0.6915 0.9879
3.500 0.7835 0.01718 0.01111 -0.0739 0.6879 0.9895
3.750 0.8139 0.01669 0.01065 -0.0743 0.6854 0.9909
4.000 0.8372 0.01697 0.01104 -0.0743 0.6755 0.9929
4.250 0.8664 0.01649 0.01060 -0.0743 0.6713 0.9941
4.500 0.8937 0.01655 0.01079 -0.0749 0.6606 0.9958
4.750 0.9231 0.01615 0.01045 -0.0751 0.6534 0.9969
5.000 0.9504 0.01590 0.01028 -0.0751 0.6428 0.9981
5.250 0.9782 0.01569 0.01015 -0.0752 0.6304 0.9993
5.500 1.0051 0.01534 0.00985 -0.0749 0.6167 1.0000
5.750 1.0291 0.01487 0.00935 -0.0736 0.5974 1.0000
6.000 1.0494 0.01451 0.00878 -0.0715 0.5558 1.0000
6.250 1.0581 0.01488 0.00874 -0.0677 0.4958 1.0000
6.500 1.0574 0.01579 0.00928 -0.0629 0.4392 1.0000
6.750 1.0527 0.01681 0.01004 -0.0576 0.3923 1.0000
7.000 1.0450 0.01781 0.01084 -0.0520 0.3536 1.0000
7.250 1.0299 0.01869 0.01159 -0.0450 0.3267 1.0000
7.500 1.0132 0.01968 0.01244 -0.0381 0.2999 1.0000
7.750 1.0029 0.02066 0.01328 -0.0324 0.2709 1.0000
8.000 0.9938 0.02171 0.01415 -0.0271 0.2389 1.0000
8.250 0.9872 0.02276 0.01504 -0.0223 0.2057 1.0000
8.500 0.9776 0.02403 0.01605 -0.0173 0.1633 1.0000
8.750 0.9722 0.02522 0.01702 -0.0130 0.1251 1.0000
9.000 0.9636 0.02666 0.01817 -0.0084 0.0808 1.0000
9.250 0.9600 0.02794 0.01926 -0.0046 0.0541 1.0000
9.500 0.9600 0.02908 0.02033 -0.0013 0.0406 1.0000
9.750 0.9622 0.03015 0.02139 0.0017 0.0338 1.0000
10.000 0.9662 0.03116 0.02244 0.0044 0.0300 1.0000
10.250 0.9690 0.03234 0.02365 0.0071 0.0272 1.0000
10.500 0.9741 0.03341 0.02483 0.0094 0.0252 1.0000
10.750 0.9784 0.03461 0.02610 0.0117 0.0234 1.0000
11.000 0.9811 0.03599 0.02753 0.0139 0.0220 1.0000
11.250 0.9855 0.03734 0.02896 0.0159 0.0204 1.0000
11.500 0.9900 0.03879 0.03049 0.0177 0.0194 1.0000
11.750 0.9942 0.04032 0.03211 0.0194 0.0186 1.0000
12.000 0.9975 0.04199 0.03385 0.0210 0.0179 1.0000
12.250 1.0002 0.04377 0.03569 0.0225 0.0171 1.0000
12.500 1.0003 0.04586 0.03781 0.0242 0.0166 1.0000
12.750 1.0065 0.04747 0.03954 0.0254 0.0161 1.0000
13.000 1.0127 0.04912 0.04132 0.0265 0.0152 1.0000
13.250 1.0181 0.05089 0.04317 0.0277 0.0147 1.0000
13.500 1.0236 0.05268 0.04504 0.0286 0.0140 1.0000
13.750 1.0285 0.05457 0.04699 0.0294 0.0135 1.0000
14.000 1.0330 0.05655 0.04902 0.0303 0.0131 1.0000
14.250 1.0374 0.05859 0.05115 0.0313 0.0125 1.0000
14.500 1.0443 0.06041 0.05307 0.0321 0.0125 1.0000
14.750 1.0496 0.06253 0.05537 0.0329 0.0121 1.0000
15.000 1.0538 0.06481 0.05783 0.0337 0.0117 1.0000
15.250 1.0577 0.06717 0.06034 0.0344 0.0116 1.0000
15.500 1.0599 0.06978 0.06312 0.0349 0.0114 1.0000
15.750 1.0589 0.07281 0.06633 0.0351 0.0110 1.0000
16.000 1.0570 0.07604 0.06974 0.0351 0.0108 1.0000
16.250 1.0538 0.07943 0.07329 0.0348 0.0106 1.0000
16.500 1.0492 0.08311 0.07713 0.0343 0.0104 1.0000
16.750 1.0465 0.08647 0.08057 0.0332 0.0100 1.0000
17.000 1.0375 0.09117 0.08551 0.0325 0.0101 1.0000
17.250 1.0307 0.09550 0.08998 0.0312 0.0099 1.0000
17.500 1.0273 0.09921 0.09372 0.0298 0.0096 1.0000
17.750 1.0159 0.10459 0.09931 0.0280 0.0097 1.0000
18.000 0.9980 0.11148 0.10645 0.0249 0.0094 1.0000
18.250 0.9829 0.11812 0.11329 0.0218 0.0093 1.0000
18.500 0.9746 0.12334 0.11860 0.0196 0.0095 1.0000
18.750 0.9553 0.13146 0.12695 0.0152 0.0095 1.0000
19.000 0.9393 0.13921 0.13488 0.0108 0.0095 1.0000
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