AH 93-K-131/15 (ah93k131-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 93-K-131/15 (ah93k131-il) Reynolds number: 100,000 Max Cl/Cd: 40.28 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah93k131-il-100000-n5.txt Download as CSV file: xf-ah93k131-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 93-K-131/15
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3585 0.08376 0.07890 -0.0650 0.8373 0.0325
-8.750 -0.3576 0.07921 0.07432 -0.0681 0.8349 0.0323
-8.500 -0.3601 0.07534 0.07040 -0.0697 0.8321 0.0320
-8.250 -0.3625 0.07158 0.06657 -0.0707 0.8296 0.0317
-8.000 -0.3642 0.06767 0.06254 -0.0713 0.8274 0.0314
-7.750 -0.3659 0.06378 0.05849 -0.0712 0.8254 0.0311
-7.500 -0.3648 0.05973 0.05422 -0.0712 0.8228 0.0309
-7.250 -0.3617 0.05567 0.04989 -0.0708 0.8196 0.0307
-7.000 -0.3579 0.05186 0.04575 -0.0696 0.8169 0.0307
-6.750 -0.3523 0.04838 0.04189 -0.0677 0.8145 0.0308
-6.500 -0.3456 0.04511 0.03813 -0.0652 0.8123 0.0315
-6.250 -0.3361 0.04222 0.03462 -0.0630 0.8092 0.0329
-6.000 -0.3210 0.04040 0.03265 -0.0622 0.8061 0.0342
-5.750 -0.3046 0.03868 0.03067 -0.0608 0.8033 0.0351
-5.500 -0.2874 0.03685 0.02849 -0.0592 0.8009 0.0359
-5.250 -0.2683 0.03514 0.02641 -0.0576 0.7989 0.0371
-5.000 -0.2476 0.03385 0.02478 -0.0566 0.7961 0.0393
-4.750 -0.2260 0.03280 0.02331 -0.0558 0.7924 0.0419
-4.500 -0.2028 0.03136 0.02163 -0.0551 0.7895 0.0434
-4.250 -0.1787 0.03025 0.02043 -0.0546 0.7872 0.0453
-4.000 -0.1544 0.02954 0.01961 -0.0540 0.7853 0.0488
-3.750 -0.1296 0.02889 0.01878 -0.0534 0.7831 0.0527
-3.500 -0.1076 0.02831 0.01810 -0.0529 0.7785 0.0550
-3.250 -0.0857 0.02763 0.01746 -0.0522 0.7754 0.0587
-3.000 -0.0627 0.02722 0.01699 -0.0514 0.7728 0.0649
-2.750 -0.0399 0.02668 0.01638 -0.0503 0.7708 0.0704
-2.500 -0.0201 0.02646 0.01614 -0.0493 0.7669 0.0774
-2.250 -0.0005 0.02628 0.01596 -0.0483 0.7625 0.0892
-2.000 0.0223 0.02592 0.01564 -0.0475 0.7595 0.1097
-1.750 0.1484 0.02312 0.01583 -0.0664 0.7622 0.8678
-1.500 0.1930 0.02382 0.01633 -0.0687 0.7603 0.9533
-1.250 0.3082 0.02375 0.01592 -0.0861 0.7613 1.0000
-1.000 0.3295 0.02380 0.01583 -0.0851 0.7584 1.0000
-0.500 0.3708 0.02425 0.01606 -0.0838 0.7502 1.0000
-0.250 0.3915 0.02442 0.01614 -0.0830 0.7462 1.0000
0.000 0.4133 0.02444 0.01606 -0.0820 0.7435 1.0000
0.250 0.4358 0.02439 0.01592 -0.0808 0.7414 1.0000
0.500 0.4518 0.02507 0.01657 -0.0802 0.7336 1.0000
0.750 0.4735 0.02512 0.01655 -0.0792 0.7303 1.0000
1.000 0.4966 0.02505 0.01643 -0.0781 0.7280 1.0000
1.250 0.5108 0.02572 0.01708 -0.0770 0.7202 1.0000
1.500 0.5324 0.02579 0.01711 -0.0759 0.7166 1.0000
1.750 0.5560 0.02569 0.01698 -0.0749 0.7141 1.0000
2.000 0.5686 0.02639 0.01769 -0.0734 0.7060 1.0000
2.250 0.5905 0.02642 0.01770 -0.0723 0.7022 1.0000
2.500 0.6152 0.02626 0.01753 -0.0714 0.6999 1.0000
2.750 0.6252 0.02703 0.01832 -0.0694 0.6908 1.0000
3.000 0.6488 0.02694 0.01825 -0.0685 0.6874 1.0000
3.250 0.6689 0.02704 0.01837 -0.0672 0.6826 1.0000
3.500 0.6831 0.02746 0.01881 -0.0654 0.6749 1.0000
3.750 0.7095 0.02714 0.01852 -0.0646 0.6722 1.0000
4.250 0.7436 0.02756 0.01904 -0.0614 0.6590 1.0000
4.500 0.7708 0.02714 0.01866 -0.0607 0.6563 1.0000
4.750 0.7784 0.02784 0.01942 -0.0581 0.6457 1.0000
5.000 0.8074 0.02725 0.01891 -0.0575 0.6432 1.0000
5.250 0.8133 0.02800 0.01972 -0.0547 0.6321 1.0000
5.500 0.8428 0.02735 0.01916 -0.0541 0.6292 1.0000
5.750 0.8489 0.02801 0.01987 -0.0512 0.6181 1.0000
6.000 0.8802 0.02724 0.01923 -0.0508 0.6148 1.0000
6.250 0.8855 0.02781 0.01985 -0.0475 0.6033 1.0000
6.750 0.9258 0.02724 0.01946 -0.0441 0.5870 1.0000
7.000 0.9352 0.02745 0.01975 -0.0411 0.5751 1.0000
7.250 0.9517 0.02734 0.01975 -0.0389 0.5634 1.0000
7.500 0.9716 0.02701 0.01949 -0.0371 0.5497 1.0000
7.750 0.9917 0.02667 0.01922 -0.0353 0.5329 1.0000
8.000 1.0160 0.02615 0.01873 -0.0339 0.5141 1.0000
8.250 1.0311 0.02622 0.01885 -0.0316 0.4926 1.0000
8.500 1.0498 0.02611 0.01871 -0.0297 0.4671 1.0000
8.750 1.0625 0.02638 0.01891 -0.0272 0.4373 1.0000
9.000 1.0716 0.02692 0.01934 -0.0245 0.4044 1.0000
9.250 1.0776 0.02770 0.01997 -0.0216 0.3692 1.0000
9.500 1.0805 0.02874 0.02082 -0.0185 0.3336 1.0000
9.750 1.0813 0.03002 0.02196 -0.0155 0.2977 1.0000
10.000 1.0804 0.03151 0.02325 -0.0126 0.2623 1.0000
10.250 1.0795 0.03312 0.02470 -0.0099 0.2272 1.0000
10.500 1.0779 0.03490 0.02629 -0.0074 0.1938 1.0000
10.750 1.0766 0.03676 0.02797 -0.0050 0.1636 1.0000
11.000 1.0764 0.03864 0.02971 -0.0030 0.1371 1.0000
11.250 1.0770 0.04054 0.03149 -0.0011 0.1149 1.0000
11.500 1.0778 0.04250 0.03336 0.0007 0.0973 1.0000
11.750 1.0792 0.04451 0.03532 0.0023 0.0831 1.0000
12.000 1.0815 0.04652 0.03736 0.0037 0.0717 1.0000
12.250 1.0838 0.04859 0.03946 0.0050 0.0623 1.0000
12.500 1.0845 0.05088 0.04174 0.0063 0.0553 1.0000
12.750 1.0866 0.05308 0.04402 0.0074 0.0488 1.0000
13.000 1.0869 0.05553 0.04650 0.0085 0.0442 1.0000
13.250 1.0893 0.05783 0.04892 0.0095 0.0399 1.0000
13.500 1.0881 0.06055 0.05165 0.0103 0.0367 1.0000
13.750 1.0912 0.06288 0.05413 0.0111 0.0336 1.0000
14.000 1.0936 0.06533 0.05671 0.0119 0.0312 1.0000
14.250 1.0945 0.06799 0.05947 0.0124 0.0293 1.0000
14.500 1.0943 0.07078 0.06228 0.0130 0.0276 1.0000
14.750 1.0984 0.07323 0.06495 0.0135 0.0258 1.0000
15.000 1.1006 0.07593 0.06781 0.0138 0.0242 1.0000
15.250 1.1021 0.07876 0.07076 0.0141 0.0231 1.0000
15.500 1.1029 0.08168 0.07380 0.0142 0.0222 1.0000
15.750 1.1035 0.08467 0.07687 0.0143 0.0215 1.0000
16.000 1.1045 0.08767 0.07995 0.0147 0.0209 1.0000
16.250 1.1035 0.09121 0.08374 0.0146 0.0204 1.0000
16.500 1.0997 0.09522 0.08800 0.0141 0.0200 1.0000
16.750 1.0933 0.09972 0.09275 0.0132 0.0195 1.0000
17.000 1.0848 0.10470 0.09798 0.0118 0.0191 1.0000
17.250 1.0745 0.11015 0.10366 0.0098 0.0188 1.0000
17.500 1.0624 0.11612 0.10985 0.0074 0.0185 1.0000
17.750 1.0484 0.12272 0.11667 0.0044 0.0184 1.0000
18.000 1.0322 0.13012 0.12428 0.0006 0.0183 1.0000
18.250 1.0128 0.13875 0.13313 -0.0042 0.0184 1.0000
18.500 0.9888 0.14926 0.14385 -0.0103 0.0188 1.0000
18.750 0.9601 0.16218 0.15693 -0.0179 0.0194 1.0000
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Polar data table (+)
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