AH 93-K-130/15 (ah93k130-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 93-K-130/15 (ah93k130-il) Reynolds number: 200,000 Max Cl/Cd: 75.64 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah93k130-il-200000.txt Download as CSV file: xf-ah93k130-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2924 0.09278 0.08940 -0.0661 0.8866 0.0489
-9.000 -0.2943 0.08872 0.08535 -0.0704 0.8852 0.0508
-8.750 -0.2996 0.08216 0.07878 -0.0830 0.8837 0.0524
-8.500 -0.3131 0.07808 0.07456 -0.0882 0.8814 0.0529
-8.250 -0.3188 0.07512 0.07140 -0.0898 0.8790 0.0532
-8.000 -0.3250 0.06860 0.06484 -0.0905 0.8773 0.0541
-7.750 -0.3134 0.06556 0.06188 -0.0900 0.8754 0.0553
-7.500 -0.3063 0.06343 0.05973 -0.0888 0.8733 0.0565
-7.250 -0.3022 0.06143 0.05764 -0.0873 0.8713 0.0580
-7.000 -0.2940 0.05865 0.05474 -0.0879 0.8683 0.0604
-6.750 -0.2971 0.05835 0.05378 -0.0852 0.8644 0.0665
-6.500 -0.2994 0.05299 0.04832 -0.0833 0.8615 0.0680
-6.250 -0.2864 0.05053 0.04592 -0.0821 0.8591 0.0697
-6.000 -0.2762 0.04898 0.04432 -0.0805 0.8559 0.0721
-5.750 -0.2730 0.05079 0.04549 -0.0759 0.8505 0.0806
-5.500 -0.2659 0.04544 0.04027 -0.0748 0.8476 0.0836
-5.250 -0.2479 0.04415 0.03895 -0.0735 0.8453 0.0892
-5.000 -0.2512 0.03785 0.03144 -0.0654 0.8385 0.0520
-4.750 -0.2361 0.03493 0.02818 -0.0630 0.8351 0.0493
-4.500 -0.2123 0.03275 0.02557 -0.0614 0.8329 0.0484
-4.250 -0.2033 0.03183 0.02441 -0.0585 0.8261 0.0492
-4.000 -0.1799 0.03113 0.02342 -0.0573 0.8226 0.0519
-3.750 -0.1507 0.03036 0.02236 -0.0568 0.8204 0.0532
-3.500 -0.1342 0.02885 0.02072 -0.0552 0.8144 0.0550
-3.250 -0.1119 0.02821 0.02010 -0.0545 0.8103 0.0590
-3.000 -0.0830 0.02770 0.01949 -0.0544 0.8078 0.0634
-2.750 -0.0522 0.02726 0.01894 -0.0542 0.8060 0.0667
-2.500 -0.0448 0.02676 0.01852 -0.0515 0.7976 0.0711
-2.250 -0.0185 0.02645 0.01819 -0.0510 0.7946 0.0788
-2.000 0.0084 0.02591 0.01768 -0.0504 0.7926 0.0884
-1.500 0.1889 0.02351 0.01834 -0.0739 0.7936 0.9652
-1.250 0.3366 0.02336 0.01791 -0.0978 0.7959 1.0000
-1.000 0.3568 0.02337 0.01782 -0.0963 0.7931 1.0000
-0.750 0.3742 0.02372 0.01811 -0.0954 0.7866 1.0000
-0.500 0.3938 0.02384 0.01815 -0.0943 0.7819 1.0000
-0.250 0.4157 0.02378 0.01801 -0.0929 0.7792 1.0000
0.000 0.4321 0.02415 0.01834 -0.0918 0.7721 1.0000
0.250 0.4529 0.02419 0.01832 -0.0906 0.7676 1.0000
0.500 0.4763 0.02406 0.01813 -0.0893 0.7652 1.0000
0.750 0.5000 0.02390 0.01792 -0.0880 0.7635 1.0000
1.000 0.5138 0.02444 0.01845 -0.0870 0.7536 1.0000
1.250 0.5387 0.02421 0.01819 -0.0859 0.7514 1.0000
1.500 0.5637 0.02395 0.01789 -0.0848 0.7497 1.0000
1.750 0.5771 0.02448 0.01843 -0.0835 0.7397 1.0000
2.000 0.6032 0.02416 0.01809 -0.0826 0.7377 1.0000
2.250 0.6295 0.02379 0.01771 -0.0816 0.7361 1.0000
2.500 0.6428 0.02431 0.01825 -0.0802 0.7259 1.0000
2.750 0.6701 0.02387 0.01780 -0.0794 0.7241 1.0000
3.000 0.6972 0.02341 0.01736 -0.0785 0.7225 1.0000
3.250 0.7105 0.02397 0.01795 -0.0771 0.7123 1.0000
3.500 0.7388 0.02341 0.01742 -0.0764 0.7106 1.0000
3.750 0.7667 0.02284 0.01687 -0.0756 0.7090 1.0000
4.000 0.7812 0.02330 0.01739 -0.0742 0.6989 1.0000
4.250 0.8104 0.02259 0.01672 -0.0735 0.6971 1.0000
4.500 0.8387 0.02189 0.01607 -0.0728 0.6950 1.0000
4.750 0.8563 0.02206 0.01630 -0.0714 0.6855 1.0000
5.000 0.8878 0.02094 0.01525 -0.0708 0.6839 1.0000
5.250 0.9196 0.01971 0.01407 -0.0701 0.6827 1.0000
5.500 0.9387 0.01973 0.01418 -0.0689 0.6726 1.0000
5.750 0.9713 0.01844 0.01297 -0.0683 0.6702 1.0000
6.000 0.9957 0.01787 0.01248 -0.0672 0.6606 1.0000
6.250 1.0298 0.01638 0.01102 -0.0665 0.6548 1.0000
6.500 1.0543 0.01591 0.01061 -0.0654 0.6416 1.0000
6.750 1.0803 0.01537 0.01010 -0.0644 0.6269 1.0000
7.000 1.1024 0.01521 0.00997 -0.0631 0.6062 1.0000
7.250 1.1257 0.01497 0.00966 -0.0617 0.5825 1.0000
7.500 1.1444 0.01513 0.00975 -0.0600 0.5541 1.0000
7.750 1.1589 0.01556 0.01010 -0.0578 0.5217 1.0000
8.000 1.1688 0.01617 0.01060 -0.0551 0.4849 1.0000
8.250 1.1720 0.01703 0.01129 -0.0514 0.4455 1.0000
8.500 1.1663 0.01812 0.01217 -0.0465 0.4093 1.0000
8.750 1.1535 0.01914 0.01302 -0.0402 0.3775 1.0000
9.000 1.1428 0.02032 0.01400 -0.0346 0.3407 1.0000
9.250 1.1329 0.02168 0.01514 -0.0295 0.3007 1.0000
9.500 1.1230 0.02323 0.01642 -0.0248 0.2572 1.0000
9.750 1.1132 0.02496 0.01786 -0.0204 0.2122 1.0000
10.000 1.1041 0.02684 0.01944 -0.0163 0.1672 1.0000
10.250 1.0962 0.02883 0.02113 -0.0126 0.1264 1.0000
10.500 1.0899 0.03087 0.02292 -0.0093 0.0976 1.0000
10.750 1.0873 0.03278 0.02472 -0.0065 0.0791 1.0000
11.000 1.0856 0.03470 0.02661 -0.0039 0.0684 1.0000
11.250 1.0869 0.03650 0.02839 -0.0017 0.0607 1.0000
11.500 1.0898 0.03826 0.03021 0.0003 0.0550 1.0000
11.750 1.0948 0.03992 0.03189 0.0020 0.0502 1.0000
12.000 1.0961 0.04194 0.03388 0.0041 0.0466 1.0000
12.250 1.1053 0.04336 0.03543 0.0056 0.0438 1.0000
12.500 1.1137 0.04487 0.03700 0.0069 0.0409 1.0000
12.750 1.1211 0.04651 0.03862 0.0084 0.0382 1.0000
13.000 1.1342 0.04793 0.04010 0.0100 0.0358 1.0000
13.250 1.1471 0.04933 0.04167 0.0113 0.0342 1.0000
13.500 1.1588 0.05086 0.04333 0.0125 0.0324 1.0000
13.750 1.1675 0.05255 0.04510 0.0135 0.0306 1.0000
14.000 1.1788 0.05429 0.04685 0.0146 0.0287 1.0000
14.250 1.1953 0.05694 0.04973 0.0159 0.0273 1.0000
14.500 1.1982 0.05935 0.05238 0.0172 0.0267 1.0000
14.750 1.1993 0.06210 0.05539 0.0184 0.0261 1.0000
15.000 1.1970 0.06512 0.05866 0.0196 0.0255 1.0000
15.250 1.1923 0.06835 0.06212 0.0205 0.0248 1.0000
15.500 1.1863 0.07173 0.06571 0.0211 0.0241 1.0000
15.750 1.1799 0.07520 0.06936 0.0214 0.0234 1.0000
16.000 1.1736 0.07876 0.07309 0.0215 0.0228 1.0000
16.250 1.1634 0.08298 0.07751 0.0213 0.0225 1.0000
16.500 1.1499 0.08790 0.08264 0.0208 0.0223 1.0000
16.750 1.1337 0.09338 0.08835 0.0197 0.0223 1.0000
17.000 1.1145 0.09962 0.09482 0.0180 0.0223 1.0000
17.250 1.0882 0.10745 0.10292 0.0150 0.0225 1.0000
17.500 1.0530 0.11764 0.11340 0.0101 0.0231 1.0000
17.750 1.0158 0.12938 0.12541 0.0037 0.0238 1.0000
18.000 0.9741 0.14386 0.14011 -0.0050 0.0251 1.0000
18.250 0.9368 0.15904 0.15539 -0.0138 0.0267 1.0000
18.500 0.9161 0.17011 0.16644 -0.0191 0.0276 1.0000
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