AH 81-K-144/17 (ah81k144-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 81-K-144/17 (ah81k144-il) Reynolds number: 100,000 Max Cl/Cd: 30.47 at α=10° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah81k144-il-100000-n5.txt Download as CSV file: xf-ah81k144-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.1790 0.09800 0.09216 -0.1010 0.8166 0.0283
-11.000 -0.1764 0.09425 0.08842 -0.1027 0.8152 0.0281
-10.750 -0.1751 0.09036 0.08455 -0.1044 0.8138 0.0279
-10.500 -0.1735 0.08679 0.08099 -0.1061 0.8124 0.0276
-10.250 -0.1774 0.08212 0.07637 -0.1084 0.8111 0.0275
-10.000 -0.1825 0.07744 0.07173 -0.1107 0.8095 0.0272
-9.750 -0.1933 0.07157 0.06594 -0.1140 0.8074 0.0270
-9.500 -0.2076 0.06475 0.05916 -0.1189 0.8050 0.0264
-9.250 -0.2322 0.05883 0.05318 -0.1218 0.8023 0.0261
-9.000 -0.2545 0.05520 0.04945 -0.1212 0.7999 0.0257
-8.750 -0.2737 0.05224 0.04631 -0.1191 0.7980 0.0254
-8.500 -0.2894 0.04873 0.04252 -0.1169 0.7961 0.0255
-8.250 -0.2965 0.04583 0.03935 -0.1148 0.7935 0.0253
-8.000 -0.3009 0.04276 0.03590 -0.1124 0.7908 0.0257
-7.750 -0.2981 0.04015 0.03289 -0.1103 0.7885 0.0258
-7.500 -0.2908 0.03772 0.03004 -0.1083 0.7866 0.0262
-7.250 -0.2791 0.03559 0.02748 -0.1066 0.7849 0.0267
-7.000 -0.2638 0.03373 0.02516 -0.1051 0.7833 0.0277
-6.750 -0.2463 0.03241 0.02361 -0.1040 0.7818 0.0298
-6.500 -0.2300 0.03163 0.02273 -0.1029 0.7790 0.0315
-6.250 -0.2118 0.03059 0.02149 -0.1017 0.7766 0.0334
-6.000 -0.1920 0.02952 0.02020 -0.1006 0.7746 0.0350
-5.750 -0.1718 0.02856 0.01907 -0.0996 0.7726 0.0377
-5.500 -0.1515 0.02795 0.01842 -0.0988 0.7708 0.0418
-5.250 -0.1294 0.02722 0.01752 -0.0978 0.7691 0.0464
-5.000 -0.1087 0.02647 0.01674 -0.0968 0.7676 0.0516
-4.750 -0.0937 0.02624 0.01648 -0.0952 0.7647 0.0603
-4.500 -0.0777 0.02603 0.01626 -0.0937 0.7617 0.0711
-4.250 -0.0596 0.02573 0.01597 -0.0924 0.7590 0.0867
-4.000 -0.0397 0.02537 0.01570 -0.0913 0.7568 0.1084
-3.750 -0.0183 0.02505 0.01545 -0.0905 0.7551 0.1373
-3.500 0.0041 0.02473 0.01522 -0.0898 0.7536 0.1745
-3.250 0.0187 0.02470 0.01533 -0.0881 0.7505 0.2130
-3.000 0.0295 0.02478 0.01561 -0.0859 0.7462 0.2610
-2.750 0.0450 0.02455 0.01569 -0.0842 0.7434 0.3417
-2.500 0.0604 0.02405 0.01572 -0.0822 0.7412 0.4694
-2.250 0.0784 0.02357 0.01597 -0.0795 0.7395 0.6512
-2.000 0.1031 0.02381 0.01645 -0.0773 0.7383 0.7763
-1.750 0.0993 0.02473 0.01737 -0.0724 0.7317 0.8159
-1.500 0.1143 0.02510 0.01764 -0.0698 0.7284 0.8519
-1.250 0.1376 0.02533 0.01776 -0.0685 0.7263 0.8807
-1.000 0.1670 0.02548 0.01776 -0.0683 0.7248 0.9048
-0.750 0.2096 0.02564 0.01778 -0.0707 0.7238 0.9253
-0.500 0.2376 0.02640 0.01848 -0.0720 0.7187 0.9459
-0.250 0.3204 0.02671 0.01861 -0.0827 0.7185 0.9651
0.000 0.3799 0.02704 0.01881 -0.0895 0.7164 0.9779
0.250 0.4231 0.02726 0.01894 -0.0933 0.7139 0.9860
0.500 0.4635 0.02738 0.01899 -0.0963 0.7120 0.9924
0.750 0.5029 0.02744 0.01896 -0.0990 0.7104 0.9985
1.000 0.5297 0.02744 0.01890 -0.0991 0.7089 1.0000
1.250 0.4983 0.02878 0.02028 -0.0906 0.6986 1.0000
1.500 0.5150 0.02884 0.02029 -0.0888 0.6961 1.0000
1.750 0.5367 0.02880 0.02020 -0.0877 0.6944 1.0000
2.250 0.5206 0.03006 0.02143 -0.0771 0.6811 1.0000
2.500 0.5429 0.03010 0.02142 -0.0762 0.6789 1.0000
2.750 0.5185 0.03128 0.02257 -0.0689 0.6680 1.0000
3.000 0.5470 0.03126 0.02254 -0.0690 0.6662 1.0000
3.500 0.5637 0.03256 0.02380 -0.0643 0.6535 1.0000
3.750 0.5941 0.03247 0.02371 -0.0646 0.6518 1.0000
4.250 0.6185 0.03373 0.02499 -0.0613 0.6390 1.0000
4.500 0.6489 0.03362 0.02490 -0.0615 0.6372 1.0000
4.750 0.6479 0.03494 0.02624 -0.0587 0.6267 1.0000
5.000 0.6766 0.03490 0.02623 -0.0588 0.6243 1.0000
5.500 0.7082 0.03605 0.02748 -0.0566 0.6115 1.0000
5.750 0.7390 0.03581 0.02730 -0.0568 0.6094 1.0000
6.250 0.7729 0.03680 0.02843 -0.0549 0.5961 1.0000
6.750 0.8083 0.03776 0.02955 -0.0531 0.5828 1.0000
7.000 0.8395 0.03737 0.02927 -0.0533 0.5807 1.0000
7.250 0.8455 0.03862 0.03060 -0.0516 0.5696 1.0000
7.500 0.8766 0.03810 0.03022 -0.0516 0.5669 1.0000
8.000 0.9146 0.03877 0.03113 -0.0500 0.5531 1.0000
8.500 0.9553 0.03911 0.03176 -0.0484 0.5389 1.0000
9.000 1.0012 0.03882 0.03178 -0.0470 0.5237 1.0000
9.250 1.0281 0.03746 0.03052 -0.0457 0.5062 1.0000
9.500 1.0450 0.03685 0.02991 -0.0437 0.4726 1.0000
9.750 1.0697 0.03580 0.02870 -0.0421 0.4276 1.0000
10.000 1.0876 0.03569 0.02834 -0.0404 0.3775 1.0000
10.250 1.0944 0.03672 0.02907 -0.0382 0.3254 1.0000
10.500 1.0910 0.03868 0.03067 -0.0358 0.2688 1.0000
10.750 1.0837 0.04123 0.03285 -0.0334 0.2099 1.0000
11.000 1.0727 0.04430 0.03544 -0.0312 0.1460 1.0000
11.250 1.0664 0.04716 0.03793 -0.0294 0.1007 1.0000
11.500 1.0640 0.04977 0.04033 -0.0279 0.0742 1.0000
11.750 1.0650 0.05219 0.04267 -0.0267 0.0622 1.0000
12.000 1.0680 0.05448 0.04500 -0.0257 0.0538 1.0000
12.250 1.0705 0.05686 0.04743 -0.0248 0.0490 1.0000
12.500 1.0747 0.05913 0.04979 -0.0240 0.0445 1.0000
12.750 1.0756 0.06174 0.05243 -0.0232 0.0413 1.0000
13.000 1.0803 0.06398 0.05479 -0.0224 0.0389 1.0000
13.250 1.0863 0.06610 0.05706 -0.0217 0.0368 1.0000
13.500 1.0920 0.06829 0.05932 -0.0211 0.0341 1.0000
13.750 1.0972 0.07047 0.06155 -0.0205 0.0324 1.0000
14.000 1.1054 0.07226 0.06337 -0.0195 0.0307 1.0000
14.250 1.1174 0.07376 0.06502 -0.0185 0.0294 1.0000
14.500 1.1280 0.07549 0.06689 -0.0179 0.0278 1.0000
14.750 1.1379 0.07734 0.06884 -0.0173 0.0264 1.0000
15.000 1.1451 0.07949 0.07103 -0.0170 0.0249 1.0000
15.250 1.1589 0.08095 0.07250 -0.0159 0.0238 1.0000
15.500 1.1684 0.08317 0.07498 -0.0154 0.0232 1.0000
15.750 1.1763 0.08574 0.07782 -0.0147 0.0226 1.0000
16.000 1.1790 0.08889 0.08124 -0.0146 0.0218 1.0000
16.250 1.1797 0.09230 0.08490 -0.0146 0.0213 1.0000
16.500 1.1760 0.09610 0.08890 -0.0152 0.0203 1.0000
16.750 1.1729 0.10018 0.09324 -0.0156 0.0203 1.0000
17.000 1.1671 0.10430 0.09753 -0.0168 0.0195 1.0000
17.250 1.1610 0.10865 0.10204 -0.0181 0.0189 1.0000
17.500 1.1519 0.11383 0.10747 -0.0197 0.0189 1.0000
17.750 1.1440 0.11874 0.11252 -0.0216 0.0185 1.0000
18.000 1.1323 0.12460 0.11860 -0.0241 0.0184 1.0000
18.250 1.1195 0.13087 0.12507 -0.0272 0.0183 1.0000
18.500 1.1033 0.13821 0.13265 -0.0311 0.0183 1.0000
18.750 1.0828 0.14706 0.14175 -0.0363 0.0184 1.0000
19.000 1.0454 0.16149 0.15652 -0.0454 0.0190 1.0000
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