AH 81-K-144/17 (ah81k144-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 81-K-144/17 (ah81k144-il) Reynolds number: 500,000 Max Cl/Cd: 117.28 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah81k144-il-500000-n5.txt Download as CSV file: xf-ah81k144-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 81-K-144/17
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
------ -------- --------- --------- -------- -------- --------
-12.250 -0.4843 0.04567 0.04163 -0.1188 0.7357 0.0068
-12.000 -0.4964 0.04065 0.03643 -0.1231 0.7345 0.0068
-11.750 -0.5000 0.03810 0.03386 -0.1242 0.7331 0.0071
-11.500 -0.5190 0.03441 0.02991 -0.1235 0.7318 0.0071
-11.250 -0.5345 0.03149 0.02672 -0.1210 0.7304 0.0069
-11.000 -0.5355 0.03011 0.02523 -0.1184 0.7292 0.0071
-10.750 -0.5346 0.02903 0.02403 -0.1155 0.7280 0.0072
-10.500 -0.5343 0.02723 0.02199 -0.1126 0.7269 0.0072
-10.250 -0.5272 0.02581 0.02038 -0.1105 0.7259 0.0073
-10.000 -0.5118 0.02515 0.01963 -0.1092 0.7249 0.0076
-9.750 -0.5003 0.02383 0.01808 -0.1074 0.7238 0.0078
-9.500 -0.4855 0.02276 0.01684 -0.1060 0.7227 0.0079
-9.250 -0.4696 0.02172 0.01564 -0.1046 0.7216 0.0082
-9.000 -0.4515 0.02084 0.01461 -0.1034 0.7205 0.0084
-8.750 -0.4336 0.01986 0.01349 -0.1023 0.7195 0.0084
-8.500 -0.4136 0.01909 0.01257 -0.1013 0.7183 0.0088
-8.250 -0.3935 0.01832 0.01169 -0.1004 0.7173 0.0088
-8.000 -0.3715 0.01772 0.01095 -0.0996 0.7162 0.0092
-7.750 -0.3496 0.01713 0.01026 -0.0989 0.7150 0.0093
-7.500 -0.3294 0.01630 0.00934 -0.0979 0.7138 0.0096
-7.250 -0.3071 0.01573 0.00870 -0.0972 0.7127 0.0100
-7.000 -0.2840 0.01524 0.00815 -0.0966 0.7117 0.0103
-6.750 -0.2598 0.01488 0.00773 -0.0962 0.7108 0.0112
-6.500 -0.2358 0.01447 0.00724 -0.0958 0.7100 0.0118
-6.250 -0.2113 0.01412 0.00681 -0.0954 0.7091 0.0125
-6.000 -0.1874 0.01369 0.00632 -0.0948 0.7081 0.0133
-5.750 -0.1632 0.01332 0.00594 -0.0944 0.7070 0.0145
-5.500 -0.1384 0.01303 0.00560 -0.0940 0.7057 0.0159
-5.250 -0.1133 0.01275 0.00529 -0.0936 0.7045 0.0171
-5.000 -0.0885 0.01245 0.00499 -0.0933 0.7034 0.0196
-4.750 -0.0632 0.01219 0.00473 -0.0929 0.7023 0.0241
-4.500 -0.0379 0.01194 0.00450 -0.0927 0.7011 0.0309
-4.250 -0.0123 0.01171 0.00429 -0.0924 0.6998 0.0401
-4.000 0.0134 0.01149 0.00410 -0.0922 0.6987 0.0508
-3.750 0.0393 0.01129 0.00392 -0.0920 0.6976 0.0626
-3.500 0.0652 0.01110 0.00375 -0.0918 0.6966 0.0771
-3.250 0.0910 0.01090 0.00361 -0.0916 0.6956 0.0998
-3.000 0.1166 0.01068 0.00348 -0.0914 0.6946 0.1282
-2.750 0.1422 0.01049 0.00337 -0.0912 0.6935 0.1599
-2.500 0.1670 0.01028 0.00330 -0.0909 0.6922 0.1946
-2.250 0.1921 0.01010 0.00324 -0.0906 0.6908 0.2302
-2.000 0.2170 0.00991 0.00318 -0.0902 0.6893 0.2717
-1.750 0.2410 0.00964 0.00311 -0.0897 0.6878 0.3343
-1.500 0.2631 0.00928 0.00305 -0.0889 0.6863 0.4259
-1.250 0.2833 0.00885 0.00298 -0.0876 0.6849 0.5367
-1.000 0.3033 0.00849 0.00293 -0.0862 0.6834 0.6337
-0.750 0.3230 0.00822 0.00302 -0.0843 0.6821 0.7355
-0.500 0.3484 0.00821 0.00309 -0.0837 0.6809 0.7775
-0.250 0.3752 0.00825 0.00310 -0.0835 0.6796 0.7989
0.000 0.4007 0.00831 0.00319 -0.0831 0.6780 0.8159
0.250 0.4263 0.00837 0.00325 -0.0827 0.6760 0.8274
0.500 0.4524 0.00842 0.00331 -0.0824 0.6741 0.8373
0.750 0.4783 0.00845 0.00335 -0.0820 0.6721 0.8475
1.000 0.5037 0.00849 0.00338 -0.0815 0.6702 0.8586
1.250 0.5298 0.00851 0.00342 -0.0811 0.6684 0.8695
1.500 0.5561 0.00852 0.00343 -0.0808 0.6668 0.8773
1.750 0.5837 0.00853 0.00342 -0.0808 0.6652 0.8823
2.000 0.6083 0.00858 0.00350 -0.0803 0.6627 0.8875
2.250 0.6343 0.00859 0.00356 -0.0800 0.6600 0.8916
2.500 0.6609 0.00860 0.00359 -0.0799 0.6573 0.8953
2.750 0.6875 0.00859 0.00359 -0.0798 0.6550 0.8988
3.000 0.7144 0.00858 0.00357 -0.0798 0.6526 0.9018
3.250 0.7417 0.00859 0.00358 -0.0798 0.6505 0.9044
3.500 0.7676 0.00863 0.00369 -0.0797 0.6472 0.9067
3.750 0.7939 0.00865 0.00376 -0.0796 0.6438 0.9092
4.000 0.8205 0.00865 0.00380 -0.0795 0.6406 0.9116
4.250 0.8478 0.00864 0.00379 -0.0796 0.6375 0.9139
4.500 0.8728 0.00869 0.00389 -0.0793 0.6332 0.9167
4.750 0.8985 0.00872 0.00398 -0.0791 0.6285 0.9192
5.000 0.9261 0.00872 0.00401 -0.0792 0.6241 0.9213
5.250 0.9524 0.00876 0.00412 -0.0792 0.6190 0.9240
5.500 0.9783 0.00880 0.00422 -0.0791 0.6130 0.9272
5.750 1.0039 0.00884 0.00429 -0.0789 0.6064 0.9305
6.000 1.0287 0.00888 0.00436 -0.0785 0.5952 0.9337
6.250 1.0532 0.00898 0.00444 -0.0782 0.5749 0.9374
6.500 1.0722 0.00929 0.00460 -0.0768 0.5383 0.9432
6.750 1.0857 0.01018 0.00520 -0.0752 0.4775 0.9528
7.000 1.1018 0.01164 0.00632 -0.0751 0.4074 0.9673
7.250 1.1120 0.01332 0.00773 -0.0745 0.3505 1.0000
7.500 1.1105 0.01515 0.00936 -0.0720 0.3075 1.0000
7.750 1.1116 0.01707 0.01106 -0.0701 0.2654 1.0000
8.000 1.1102 0.01908 0.01281 -0.0678 0.2173 1.0000
8.250 1.1107 0.02094 0.01445 -0.0656 0.1732 1.0000
8.500 1.1084 0.02297 0.01620 -0.0631 0.1247 1.0000
8.750 1.1116 0.02466 0.01769 -0.0612 0.0902 1.0000
9.000 1.1154 0.02633 0.01919 -0.0594 0.0602 1.0000
9.250 1.1251 0.02761 0.02041 -0.0582 0.0456 1.0000
9.500 1.1352 0.02888 0.02163 -0.0570 0.0350 1.0000
9.750 1.1472 0.03003 0.02277 -0.0560 0.0291 1.0000
10.000 1.1583 0.03124 0.02399 -0.0550 0.0249 1.0000
10.250 1.1709 0.03236 0.02514 -0.0541 0.0223 1.0000
10.500 1.1825 0.03356 0.02636 -0.0532 0.0199 1.0000
10.750 1.1943 0.03481 0.02765 -0.0523 0.0191 1.0000
11.000 1.2048 0.03616 0.02905 -0.0514 0.0175 1.0000
11.250 1.2173 0.03740 0.03034 -0.0506 0.0164 1.0000
11.500 1.2284 0.03877 0.03176 -0.0498 0.0153 1.0000
11.750 1.2391 0.04020 0.03324 -0.0490 0.0144 1.0000
12.000 1.2466 0.04189 0.03498 -0.0481 0.0135 1.0000
12.250 1.2564 0.04343 0.03659 -0.0473 0.0129 1.0000
12.500 1.2666 0.04497 0.03819 -0.0466 0.0124 1.0000
12.750 1.2767 0.04653 0.03981 -0.0460 0.0115 1.0000
13.000 1.2857 0.04822 0.04157 -0.0453 0.0111 1.0000
13.250 1.2949 0.04988 0.04328 -0.0447 0.0107 1.0000
13.500 1.3017 0.05182 0.04529 -0.0440 0.0101 1.0000
13.750 1.3053 0.05410 0.04762 -0.0432 0.0096 1.0000
14.000 1.3123 0.05609 0.04970 -0.0427 0.0093 1.0000
14.250 1.3212 0.05792 0.05161 -0.0422 0.0088 1.0000
14.500 1.3280 0.05996 0.05372 -0.0418 0.0085 1.0000
14.750 1.3337 0.06214 0.05599 -0.0414 0.0082 1.0000
15.000 1.3406 0.06424 0.05815 -0.0411 0.0078 1.0000
15.250 1.3447 0.06668 0.06067 -0.0407 0.0076 1.0000
15.500 1.3484 0.06920 0.06326 -0.0404 0.0074 1.0000
15.750 1.3520 0.07177 0.06592 -0.0403 0.0071 1.0000
16.000 1.3523 0.07474 0.06897 -0.0400 0.0067 1.0000
16.250 1.3528 0.07776 0.07209 -0.0399 0.0067 1.0000
16.500 1.3548 0.08062 0.07507 -0.0398 0.0065 1.0000
16.750 1.3566 0.08357 0.07811 -0.0400 0.0065 1.0000
17.000 1.3582 0.08658 0.08123 -0.0401 0.0062 1.0000
17.250 1.3587 0.08976 0.08453 -0.0404 0.0060 1.0000
17.500 1.3582 0.09310 0.08797 -0.0407 0.0059 1.0000
17.750 1.3586 0.09640 0.09137 -0.0412 0.0057 1.0000
18.000 1.3554 0.10019 0.09528 -0.0417 0.0057 1.0000
18.250 1.3544 0.10377 0.09895 -0.0425 0.0055 1.0000
18.500 1.3541 0.10731 0.10260 -0.0434 0.0053 1.0000
18.750 1.3515 0.11123 0.10663 -0.0443 0.0053 1.0000
19.000 1.3475 0.11534 0.11087 -0.0454 0.0053 1.0000
19.250 1.3435 0.11958 0.11520 -0.0468 0.0051 1.0000
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