AH 93-K-130/15 (ah93k130-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 93-K-130/15 (ah93k130-il) Reynolds number: 500,000 Max Cl/Cd: 114.77 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah93k130-il-500000.txt Download as CSV file: xf-ah93k130-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: AH 93-K-130/15
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2931 0.08560 0.08325 -0.0463 0.8071 0.0231
-9.250 -0.3134 0.07755 0.07523 -0.0489 0.8066 0.0236
-9.000 -0.3214 0.07243 0.07012 -0.0511 0.8059 0.0238
-8.750 -0.3290 0.06733 0.06503 -0.0545 0.8049 0.0240
-8.500 -0.3475 0.05955 0.05723 -0.0621 0.8028 0.0240
-8.250 -0.3584 0.05487 0.05249 -0.0634 0.8005 0.0241
-8.000 -0.3654 0.05129 0.04885 -0.0628 0.7986 0.0243
-7.750 -0.3663 0.04784 0.04532 -0.0623 0.7969 0.0247
-7.500 -0.3654 0.04434 0.04172 -0.0615 0.7954 0.0250
-7.250 -0.3629 0.04089 0.03816 -0.0604 0.7942 0.0256
-7.000 -0.3592 0.03735 0.03447 -0.0591 0.7931 0.0263
-6.750 -0.3550 0.03356 0.03049 -0.0574 0.7921 0.0272
-6.500 -0.3985 0.03653 0.03236 -0.0501 0.7928 0.0223
-6.250 -0.3930 0.03211 0.02748 -0.0469 0.7918 0.0216
-6.000 -0.3779 0.02792 0.02278 -0.0453 0.7884 0.0213
-5.750 -0.3575 0.02547 0.01994 -0.0441 0.7858 0.0217
-5.500 -0.3350 0.02388 0.01806 -0.0431 0.7838 0.0223
-5.250 -0.3109 0.02293 0.01688 -0.0423 0.7823 0.0229
-5.000 -0.2888 0.02079 0.01447 -0.0413 0.7811 0.0243
-4.750 -0.2643 0.02020 0.01386 -0.0407 0.7800 0.0258
-4.500 -0.2395 0.01957 0.01314 -0.0400 0.7791 0.0271
-4.250 -0.2145 0.01893 0.01241 -0.0393 0.7782 0.0286
-4.000 -0.1863 0.01855 0.01196 -0.0397 0.7749 0.0301
-3.750 -0.1593 0.01790 0.01125 -0.0399 0.7716 0.0317
-3.500 -0.1349 0.01717 0.01051 -0.0394 0.7696 0.0347
-3.250 -0.1093 0.01679 0.01010 -0.0389 0.7681 0.0371
-3.000 -0.0841 0.01638 0.00964 -0.0383 0.7670 0.0395
-2.750 -0.0584 0.01605 0.00926 -0.0377 0.7660 0.0415
-2.500 -0.0354 0.01538 0.00856 -0.0367 0.7651 0.0461
-2.250 -0.0101 0.01505 0.00820 -0.0360 0.7643 0.0502
-2.000 0.0175 0.01504 0.00820 -0.0367 0.7592 0.0555
-1.750 0.0436 0.01476 0.00794 -0.0364 0.7565 0.0655
-1.500 0.0684 0.01430 0.00761 -0.0358 0.7549 0.0973
-1.250 0.0889 0.01340 0.00730 -0.0346 0.7536 0.2612
-1.000 0.1001 0.01200 0.00697 -0.0315 0.7523 0.5637
-0.750 0.1811 0.01136 0.00753 -0.0419 0.7525 0.9338
-0.500 0.2163 0.01154 0.00763 -0.0429 0.7517 0.9536
-0.250 0.2611 0.01165 0.00766 -0.0461 0.7511 0.9648
0.000 0.3259 0.01181 0.00774 -0.0535 0.7507 0.9799
0.250 0.4104 0.01162 0.00748 -0.0653 0.7505 0.9964
0.500 0.4545 0.01149 0.00734 -0.0691 0.7475 1.0000
0.750 0.4813 0.01143 0.00727 -0.0694 0.7434 1.0000
1.000 0.5060 0.01120 0.00701 -0.0689 0.7412 1.0000
1.250 0.5303 0.01093 0.00670 -0.0682 0.7395 1.0000
1.500 0.5546 0.01064 0.00637 -0.0674 0.7381 1.0000
1.750 0.5788 0.01035 0.00604 -0.0667 0.7368 1.0000
2.000 0.6069 0.01036 0.00610 -0.0672 0.7314 1.0000
2.250 0.6327 0.01017 0.00590 -0.0669 0.7282 1.0000
2.500 0.6581 0.00993 0.00565 -0.0665 0.7259 1.0000
2.750 0.6831 0.00966 0.00535 -0.0659 0.7240 1.0000
3.000 0.7100 0.00957 0.00529 -0.0659 0.7198 1.0000
3.250 0.7368 0.00946 0.00520 -0.0659 0.7148 1.0000
3.500 0.7625 0.00921 0.00495 -0.0655 0.7115 1.0000
3.750 0.7889 0.00907 0.00483 -0.0653 0.7067 1.0000
4.000 0.8157 0.00893 0.00472 -0.0653 0.6997 1.0000
4.250 0.8419 0.00875 0.00454 -0.0650 0.6932 1.0000
4.500 0.8687 0.00866 0.00448 -0.0650 0.6848 1.0000
4.750 0.8956 0.00860 0.00445 -0.0650 0.6751 1.0000
5.000 0.9219 0.00853 0.00436 -0.0648 0.6634 1.0000
5.250 0.9483 0.00852 0.00431 -0.0647 0.6475 1.0000
5.500 0.9747 0.00858 0.00433 -0.0646 0.6303 1.0000
5.750 1.0008 0.00872 0.00442 -0.0646 0.6119 1.0000
6.000 1.0269 0.00895 0.00460 -0.0647 0.5887 1.0000
6.250 1.0522 0.00929 0.00484 -0.0647 0.5602 1.0000
6.500 1.0765 0.00973 0.00517 -0.0647 0.5286 1.0000
6.750 1.0990 0.01032 0.00562 -0.0645 0.4917 1.0000
7.000 1.1186 0.01107 0.00620 -0.0640 0.4494 1.0000
7.250 1.1343 0.01199 0.00692 -0.0629 0.4055 1.0000
7.500 1.1449 0.01309 0.00781 -0.0612 0.3599 1.0000
7.750 1.1486 0.01437 0.00887 -0.0584 0.3157 1.0000
8.000 1.1414 0.01554 0.00986 -0.0533 0.2802 1.0000
8.250 1.1282 0.01650 0.01068 -0.0467 0.2517 1.0000
8.500 1.1204 0.01756 0.01156 -0.0413 0.2196 1.0000
8.750 1.1169 0.01861 0.01243 -0.0369 0.1869 1.0000
9.000 1.1148 0.01970 0.01335 -0.0328 0.1551 1.0000
9.250 1.1144 0.02081 0.01428 -0.0290 0.1251 1.0000
9.500 1.1151 0.02193 0.01525 -0.0256 0.0989 1.0000
9.750 1.1179 0.02303 0.01622 -0.0226 0.0770 1.0000
10.000 1.1205 0.02420 0.01727 -0.0196 0.0593 1.0000
10.250 1.1245 0.02535 0.01835 -0.0169 0.0471 1.0000
10.500 1.1316 0.02637 0.01938 -0.0147 0.0402 1.0000
10.750 1.1371 0.02752 0.02055 -0.0123 0.0352 1.0000
11.000 1.1456 0.02853 0.02159 -0.0104 0.0318 1.0000
11.250 1.1479 0.03001 0.02308 -0.0079 0.0284 1.0000
11.500 1.1551 0.03121 0.02437 -0.0061 0.0268 1.0000
11.750 1.1641 0.03236 0.02559 -0.0045 0.0253 1.0000
12.000 1.1726 0.03360 0.02688 -0.0031 0.0237 1.0000
12.250 1.1782 0.03511 0.02842 -0.0015 0.0221 1.0000
12.500 1.1743 0.03748 0.03087 0.0008 0.0205 1.0000
12.750 1.1833 0.03883 0.03232 0.0020 0.0198 1.0000
13.000 1.1917 0.04028 0.03385 0.0031 0.0190 1.0000
13.250 1.1989 0.04187 0.03553 0.0042 0.0181 1.0000
13.500 1.2062 0.04350 0.03721 0.0052 0.0172 1.0000
13.750 1.2124 0.04526 0.03902 0.0061 0.0163 1.0000
14.000 1.2125 0.04761 0.04143 0.0073 0.0154 1.0000
14.250 1.2090 0.05032 0.04424 0.0090 0.0146 1.0000
14.500 1.2171 0.05207 0.04609 0.0095 0.0142 1.0000
14.750 1.2230 0.05404 0.04816 0.0102 0.0137 1.0000
15.000 1.2278 0.05615 0.05039 0.0108 0.0132 1.0000
15.250 1.2320 0.05839 0.05272 0.0113 0.0126 1.0000
15.500 1.2359 0.06070 0.05512 0.0116 0.0122 1.0000
15.750 1.2390 0.06316 0.05765 0.0118 0.0117 1.0000
16.000 1.2398 0.06591 0.06045 0.0120 0.0112 1.0000
16.250 1.2343 0.06920 0.06385 0.0129 0.0107 1.0000
16.500 1.2317 0.07240 0.06720 0.0133 0.0104 1.0000
16.750 1.2331 0.07539 0.07033 0.0129 0.0101 1.0000
17.000 1.2326 0.07863 0.07371 0.0125 0.0098 1.0000
17.250 1.2305 0.08210 0.07731 0.0121 0.0096 1.0000
17.500 1.2273 0.08580 0.08114 0.0115 0.0093 1.0000
17.750 1.2231 0.08972 0.08520 0.0108 0.0091 1.0000
18.000 1.2179 0.09391 0.08952 0.0097 0.0089 1.0000
18.250 1.2119 0.09830 0.09405 0.0085 0.0087 1.0000
18.500 1.2051 0.10291 0.09878 0.0070 0.0085 1.0000
18.750 1.1975 0.10774 0.10376 0.0053 0.0084 1.0000
19.000 1.1894 0.11280 0.10894 0.0033 0.0083 1.0000
19.250 1.1807 0.11807 0.11433 0.0011 0.0082 1.0000
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