AH 93-K-132/15 (ah93k132-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 93-K-132/15 (ah93k132-il) Reynolds number: 200,000 Max Cl/Cd: 71.68 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah93k132-il-200000-n5.txt Download as CSV file: xf-ah93k132-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 93-K-132/15
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.2674 0.10369 0.10015 -0.0440 0.8097 0.0259
-10.250 -0.2679 0.09965 0.09612 -0.0453 0.8093 0.0259
-10.000 -0.2701 0.09496 0.09144 -0.0477 0.8085 0.0257
-9.750 -0.2684 0.08942 0.08588 -0.0486 0.8075 0.0181
-9.500 -0.2666 0.08566 0.08212 -0.0499 0.8062 0.0175
-9.250 -0.2682 0.08124 0.07772 -0.0518 0.8050 0.0170
-9.000 -0.3746 0.08781 0.08416 -0.0463 0.8084 0.0178
-8.750 -0.3728 0.08321 0.07960 -0.0505 0.8067 0.0172
-8.500 -0.3753 0.07734 0.07373 -0.0570 0.8047 0.0166
-8.250 -0.3831 0.07195 0.06829 -0.0608 0.8027 0.0159
-8.000 -0.4066 0.06004 0.05604 -0.0645 0.8007 0.0135
-7.750 -0.4070 0.05619 0.05201 -0.0642 0.7991 0.0133
-7.500 -0.4057 0.05224 0.04784 -0.0632 0.7977 0.0131
-7.250 -0.4027 0.04831 0.04363 -0.0618 0.7964 0.0130
-7.000 -0.3976 0.04446 0.03944 -0.0599 0.7954 0.0128
-6.750 -0.3879 0.04063 0.03523 -0.0587 0.7934 0.0127
-6.500 -0.3751 0.03704 0.03118 -0.0574 0.7906 0.0126
-6.250 -0.3606 0.03392 0.02759 -0.0558 0.7884 0.0127
-6.000 -0.3433 0.03130 0.02448 -0.0542 0.7866 0.0128
-5.750 -0.3234 0.02916 0.02186 -0.0527 0.7850 0.0131
-5.500 -0.3014 0.02746 0.01977 -0.0515 0.7836 0.0135
-5.250 -0.2789 0.02595 0.01801 -0.0506 0.7825 0.0140
-5.000 -0.2556 0.02522 0.01721 -0.0500 0.7815 0.0150
-4.750 -0.2305 0.02464 0.01650 -0.0498 0.7798 0.0166
-4.500 -0.2033 0.02393 0.01564 -0.0503 0.7762 0.0179
-4.250 -0.1784 0.02307 0.01467 -0.0500 0.7739 0.0188
-4.000 -0.1553 0.02224 0.01382 -0.0493 0.7719 0.0201
-3.750 -0.1316 0.02168 0.01321 -0.0486 0.7703 0.0218
-3.500 -0.1072 0.02129 0.01272 -0.0479 0.7689 0.0249
-3.250 -0.0844 0.02068 0.01209 -0.0470 0.7677 0.0285
-3.000 -0.0598 0.02039 0.01172 -0.0467 0.7651 0.0329
-2.750 -0.0354 0.02018 0.01153 -0.0467 0.7607 0.0426
-2.500 -0.0115 0.01978 0.01119 -0.0461 0.7583 0.0612
-2.250 0.0110 0.01922 0.01087 -0.0453 0.7564 0.1203
-1.750 0.0479 0.01750 0.01032 -0.0423 0.7536 0.4291
-1.500 0.1233 0.01653 0.01095 -0.0505 0.7539 0.8791
-1.250 0.1595 0.01717 0.01151 -0.0519 0.7505 0.9251
-1.000 0.2028 0.01763 0.01185 -0.0551 0.7473 0.9445
-0.750 0.2403 0.01779 0.01190 -0.0570 0.7451 0.9565
-0.500 0.2800 0.01784 0.01185 -0.0595 0.7435 0.9666
-0.250 0.3291 0.01778 0.01169 -0.0637 0.7424 0.9771
0.000 0.3739 0.01762 0.01145 -0.0673 0.7413 0.9855
0.250 0.4124 0.01735 0.01111 -0.0696 0.7403 0.9892
0.500 0.4475 0.01764 0.01138 -0.0723 0.7344 0.9924
0.750 0.4800 0.01755 0.01126 -0.0737 0.7313 0.9950
1.000 0.5129 0.01732 0.01101 -0.0749 0.7292 0.9972
1.250 0.5452 0.01705 0.01071 -0.0759 0.7277 0.9995
1.500 0.5706 0.01677 0.01039 -0.0754 0.7264 1.0000
1.750 0.5958 0.01724 0.01091 -0.0763 0.7181 1.0000
2.000 0.6194 0.01702 0.01069 -0.0755 0.7156 1.0000
2.250 0.6431 0.01671 0.01037 -0.0746 0.7138 1.0000
2.500 0.6668 0.01707 0.01076 -0.0748 0.7061 1.0000
2.750 0.6906 0.01684 0.01055 -0.0740 0.7028 1.0000
3.000 0.7148 0.01645 0.01018 -0.0731 0.7005 1.0000
3.250 0.7376 0.01672 0.01050 -0.0730 0.6922 1.0000
3.500 0.7618 0.01640 0.01021 -0.0722 0.6884 1.0000
3.750 0.7866 0.01596 0.00978 -0.0713 0.6858 1.0000
4.250 0.8334 0.01583 0.00976 -0.0700 0.6726 1.0000
4.500 0.8551 0.01603 0.01002 -0.0695 0.6626 1.0000
4.750 0.8810 0.01546 0.00948 -0.0685 0.6582 1.0000
5.250 0.9267 0.01531 0.00944 -0.0668 0.6374 1.0000
5.500 0.9514 0.01492 0.00907 -0.0658 0.6263 1.0000
5.750 0.9754 0.01463 0.00877 -0.0647 0.6122 1.0000
6.000 0.9986 0.01439 0.00849 -0.0634 0.5916 1.0000
6.250 1.0201 0.01433 0.00834 -0.0620 0.5655 1.0000
6.500 1.0393 0.01450 0.00841 -0.0605 0.5379 1.0000
6.750 1.0557 0.01488 0.00867 -0.0587 0.5089 1.0000
7.000 1.0681 0.01545 0.00913 -0.0564 0.4775 1.0000
7.250 1.0763 0.01617 0.00973 -0.0536 0.4459 1.0000
7.500 1.0788 0.01704 0.01045 -0.0501 0.4149 1.0000
7.750 1.0737 0.01787 0.01117 -0.0450 0.3877 1.0000
8.000 1.0662 0.01870 0.01187 -0.0395 0.3613 1.0000
8.250 1.0612 0.01963 0.01265 -0.0347 0.3321 1.0000
8.500 1.0583 0.02061 0.01349 -0.0304 0.3026 1.0000
8.750 1.0566 0.02168 0.01440 -0.0265 0.2717 1.0000
9.000 1.0561 0.02283 0.01541 -0.0231 0.2392 1.0000
9.250 1.0566 0.02407 0.01648 -0.0199 0.2062 1.0000
9.500 1.0581 0.02538 0.01761 -0.0172 0.1725 1.0000
9.750 1.0607 0.02673 0.01880 -0.0147 0.1421 1.0000
10.000 1.0651 0.02806 0.01999 -0.0125 0.1162 1.0000
10.250 1.0706 0.02938 0.02121 -0.0105 0.0960 1.0000
10.500 1.0775 0.03066 0.02244 -0.0088 0.0795 1.0000
10.750 1.0847 0.03195 0.02371 -0.0071 0.0662 1.0000
11.000 1.0920 0.03329 0.02505 -0.0056 0.0553 1.0000
11.250 1.0991 0.03468 0.02644 -0.0041 0.0467 1.0000
11.500 1.1056 0.03620 0.02796 -0.0027 0.0395 1.0000
11.750 1.1138 0.03764 0.02948 -0.0014 0.0340 1.0000
12.000 1.1184 0.03941 0.03125 -0.0001 0.0295 1.0000
12.250 1.1260 0.04099 0.03295 0.0010 0.0265 1.0000
12.500 1.1317 0.04278 0.03482 0.0022 0.0240 1.0000
12.750 1.1333 0.04499 0.03707 0.0034 0.0219 1.0000
13.000 1.1399 0.04678 0.03900 0.0043 0.0202 1.0000
13.250 1.1455 0.04872 0.04108 0.0051 0.0186 1.0000
13.500 1.1496 0.05085 0.04330 0.0059 0.0174 1.0000
13.750 1.1500 0.05342 0.04595 0.0067 0.0164 1.0000
14.000 1.1504 0.05605 0.04868 0.0074 0.0157 1.0000
14.250 1.1537 0.05842 0.05121 0.0080 0.0150 1.0000
14.500 1.1565 0.06091 0.05384 0.0085 0.0143 1.0000
14.750 1.1591 0.06347 0.05652 0.0088 0.0135 1.0000
15.000 1.1613 0.06614 0.05930 0.0089 0.0128 1.0000
15.250 1.1618 0.06906 0.06231 0.0089 0.0122 1.0000
15.500 1.1596 0.07235 0.06569 0.0089 0.0117 1.0000
15.750 1.1580 0.07561 0.06908 0.0089 0.0113 1.0000
16.000 1.1580 0.07877 0.07241 0.0088 0.0110 1.0000
16.250 1.1570 0.08212 0.07596 0.0086 0.0107 1.0000
16.500 1.1550 0.08567 0.07968 0.0082 0.0104 1.0000
16.750 1.1522 0.08944 0.08362 0.0076 0.0101 1.0000
17.000 1.1482 0.09347 0.08783 0.0068 0.0099 1.0000
17.250 1.1431 0.09775 0.09228 0.0057 0.0097 1.0000
17.500 1.1372 0.10229 0.09698 0.0043 0.0095 1.0000
17.750 1.1306 0.10707 0.10192 0.0026 0.0093 1.0000
18.000 1.1234 0.11210 0.10711 0.0006 0.0091 1.0000
18.250 1.1155 0.11740 0.11256 -0.0017 0.0089 1.0000
18.500 1.1071 0.12290 0.11821 -0.0043 0.0088 1.0000
18.750 1.0984 0.12862 0.12407 -0.0072 0.0086 1.0000
19.000 1.0888 0.13471 0.13030 -0.0104 0.0085 1.0000
19.250 1.0785 0.14115 0.13689 -0.0139 0.0084 1.0000
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