AH 93-K-132/15 (ah93k132-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 93-K-132/15 (ah93k132-il) Reynolds number: 100,000 Max Cl/Cd: 39.97 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah93k132-il-100000-n5.txt Download as CSV file: xf-ah93k132-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.3759 0.14959 0.14463 -0.0305 0.8704 0.0433
-12.500 -0.3755 0.14656 0.14162 -0.0347 0.8698 0.0440
-12.250 -0.3731 0.14315 0.13823 -0.0382 0.8689 0.0443
-12.000 -0.3697 0.13952 0.13461 -0.0414 0.8680 0.0444
-11.750 -0.3660 0.13573 0.13084 -0.0443 0.8670 0.0445
-11.500 -0.3623 0.13183 0.12695 -0.0471 0.8660 0.0446
-11.250 -0.3515 0.12643 0.12157 -0.0462 0.8653 0.0453
-11.000 -0.3412 0.12268 0.11780 -0.0463 0.8646 0.0461
-10.750 -0.3334 0.11915 0.11426 -0.0474 0.8638 0.0467
-10.500 -0.3274 0.11562 0.11073 -0.0490 0.8630 0.0473
-10.250 -0.2124 0.09775 0.09300 -0.0647 0.8579 0.0324
-10.000 -0.2082 0.09404 0.08930 -0.0656 0.8568 0.0308
-9.750 -0.2083 0.08976 0.08504 -0.0673 0.8556 0.0294
-9.500 -0.2120 0.08484 0.08014 -0.0695 0.8543 0.0279
-9.000 -0.3230 0.08246 0.07762 -0.0749 0.8555 0.0248
-8.750 -0.3222 0.07844 0.07357 -0.0778 0.8536 0.0244
-8.500 -0.3253 0.07439 0.06948 -0.0800 0.8515 0.0240
-8.250 -0.3325 0.07094 0.06595 -0.0805 0.8497 0.0237
-8.000 -0.3364 0.06716 0.06205 -0.0812 0.8480 0.0233
-7.750 -0.3371 0.06318 0.05792 -0.0820 0.8453 0.0229
-7.500 -0.3374 0.05940 0.05394 -0.0818 0.8427 0.0226
-7.250 -0.3367 0.05579 0.05007 -0.0807 0.8404 0.0222
-7.000 -0.3347 0.05237 0.04635 -0.0788 0.8381 0.0219
-6.750 -0.3306 0.04925 0.04286 -0.0765 0.8361 0.0218
-6.500 -0.3229 0.04645 0.03968 -0.0749 0.8328 0.0223
-6.250 -0.3139 0.04397 0.03678 -0.0728 0.8298 0.0231
-6.000 -0.3029 0.04165 0.03397 -0.0703 0.8270 0.0241
-5.750 -0.2887 0.03960 0.03140 -0.0680 0.8248 0.0247
-5.500 -0.2715 0.03768 0.02902 -0.0660 0.8231 0.0250
-5.250 -0.2561 0.03592 0.02695 -0.0645 0.8193 0.0253
-5.000 -0.2376 0.03430 0.02511 -0.0633 0.8161 0.0260
-4.750 -0.2162 0.03307 0.02369 -0.0623 0.8136 0.0270
-4.500 -0.1929 0.03207 0.02249 -0.0615 0.8115 0.0288
-4.250 -0.1682 0.03130 0.02151 -0.0608 0.8097 0.0320
-4.000 -0.1487 0.03053 0.02061 -0.0596 0.8060 0.0341
-3.750 -0.1305 0.02969 0.01977 -0.0583 0.8022 0.0365
-3.500 -0.1094 0.02909 0.01912 -0.0572 0.7992 0.0403
-3.250 -0.0871 0.02851 0.01843 -0.0561 0.7969 0.0469
-3.000 -0.0635 0.02800 0.01783 -0.0551 0.7951 0.0555
-2.750 -0.0507 0.02776 0.01760 -0.0532 0.7892 0.0687
-2.500 -0.0307 0.02717 0.01722 -0.0520 0.7858 0.1059
-2.250 -0.0094 0.02608 0.01697 -0.0513 0.7833 0.2889
-2.000 0.1196 0.02552 0.01839 -0.0680 0.7869 0.9361
-1.750 0.1881 0.02595 0.01850 -0.0757 0.7862 0.9701
-1.500 0.2433 0.02598 0.01829 -0.0815 0.7848 0.9847
-1.250 0.3165 0.02572 0.01779 -0.0910 0.7841 1.0000
-1.000 0.3373 0.02577 0.01770 -0.0899 0.7816 1.0000
-0.750 0.3525 0.02614 0.01799 -0.0888 0.7754 1.0000
-0.500 0.3709 0.02630 0.01806 -0.0876 0.7711 1.0000
-0.250 0.3923 0.02633 0.01799 -0.0865 0.7683 1.0000
0.000 0.4067 0.02668 0.01828 -0.0850 0.7624 1.0000
0.250 0.4242 0.02686 0.01840 -0.0836 0.7574 1.0000
0.500 0.4463 0.02686 0.01832 -0.0825 0.7545 1.0000
0.750 0.4580 0.02726 0.01870 -0.0805 0.7476 1.0000
1.000 0.4770 0.02737 0.01875 -0.0792 0.7431 1.0000
1.250 0.5009 0.02729 0.01863 -0.0783 0.7404 1.0000
1.500 0.5082 0.02780 0.01914 -0.0757 0.7319 1.0000
1.750 0.5308 0.02776 0.01906 -0.0747 0.7284 1.0000
2.250 0.5610 0.02817 0.01945 -0.0710 0.7162 1.0000
2.500 0.5869 0.02799 0.01928 -0.0703 0.7135 1.0000
2.750 0.5915 0.02852 0.01981 -0.0671 0.7038 1.0000
3.000 0.6174 0.02832 0.01962 -0.0665 0.7007 1.0000
3.250 0.6229 0.02879 0.02010 -0.0633 0.6913 1.0000
3.500 0.6488 0.02856 0.01989 -0.0627 0.6877 1.0000
3.750 0.6560 0.02894 0.02032 -0.0596 0.6784 1.0000
4.000 0.6815 0.02868 0.02009 -0.0589 0.6743 1.0000
4.500 0.7148 0.02868 0.02017 -0.0550 0.6608 1.0000
4.750 0.7460 0.02813 0.01972 -0.0550 0.6581 1.0000
5.000 0.7468 0.02858 0.02020 -0.0508 0.6469 1.0000
5.250 0.7767 0.02803 0.01973 -0.0505 0.6437 1.0000
5.500 0.7807 0.02837 0.02011 -0.0467 0.6328 1.0000
6.000 0.8189 0.02798 0.01990 -0.0433 0.6182 1.0000
6.250 0.8324 0.02806 0.02006 -0.0409 0.6084 1.0000
6.500 0.8625 0.02734 0.01945 -0.0404 0.6025 1.0000
6.750 0.8760 0.02741 0.01960 -0.0380 0.5907 1.0000
7.000 0.8952 0.02722 0.01952 -0.0363 0.5793 1.0000
7.250 0.9189 0.02680 0.01920 -0.0351 0.5674 1.0000
7.500 0.9413 0.02642 0.01890 -0.0336 0.5520 1.0000
7.750 0.9660 0.02592 0.01845 -0.0324 0.5331 1.0000
8.000 0.9895 0.02556 0.01814 -0.0310 0.5114 1.0000
8.250 1.0094 0.02545 0.01802 -0.0293 0.4864 1.0000
8.500 1.0248 0.02564 0.01817 -0.0272 0.4579 1.0000
8.750 1.0382 0.02598 0.01842 -0.0249 0.4259 1.0000
9.000 1.0466 0.02665 0.01899 -0.0223 0.3913 1.0000
9.250 1.0527 0.02751 0.01972 -0.0196 0.3546 1.0000
9.500 1.0563 0.02862 0.02066 -0.0168 0.3170 1.0000
9.750 1.0578 0.02994 0.02179 -0.0139 0.2791 1.0000
10.000 1.0587 0.03142 0.02309 -0.0113 0.2413 1.0000
10.250 1.0587 0.03306 0.02454 -0.0088 0.2046 1.0000
10.500 1.0590 0.03480 0.02609 -0.0065 0.1709 1.0000
10.750 1.0596 0.03661 0.02774 -0.0044 0.1412 1.0000
11.000 1.0612 0.03842 0.02943 -0.0025 0.1167 1.0000
11.250 1.0626 0.04033 0.03125 -0.0007 0.0978 1.0000
11.500 1.0655 0.04219 0.03309 0.0009 0.0824 1.0000
11.750 1.0680 0.04418 0.03505 0.0024 0.0707 1.0000
12.000 1.0700 0.04627 0.03716 0.0038 0.0613 1.0000
12.250 1.0737 0.04827 0.03925 0.0051 0.0538 1.0000
12.500 1.0742 0.05063 0.04160 0.0063 0.0482 1.0000
12.750 1.0780 0.05274 0.04385 0.0074 0.0430 1.0000
13.000 1.0782 0.05524 0.04639 0.0084 0.0397 1.0000
13.250 1.0808 0.05756 0.04884 0.0095 0.0367 1.0000
13.500 1.0846 0.05983 0.05125 0.0103 0.0336 1.0000
13.750 1.0865 0.06234 0.05383 0.0109 0.0312 1.0000
14.000 1.0872 0.06498 0.05653 0.0117 0.0294 1.0000
14.250 1.0932 0.06717 0.05894 0.0126 0.0279 1.0000
14.500 1.0981 0.06953 0.06148 0.0134 0.0263 1.0000
14.750 1.1011 0.07217 0.06426 0.0138 0.0248 1.0000
15.000 1.1021 0.07503 0.06724 0.0139 0.0235 1.0000
15.250 1.1021 0.07802 0.07029 0.0140 0.0224 1.0000
15.500 1.1028 0.08116 0.07360 0.0143 0.0215 1.0000
15.750 1.1025 0.08458 0.07728 0.0143 0.0208 1.0000
16.000 1.0998 0.08841 0.08137 0.0141 0.0203 1.0000
16.250 1.0945 0.09267 0.08588 0.0136 0.0199 1.0000
16.500 1.0866 0.09745 0.09091 0.0125 0.0195 1.0000
16.750 1.0765 0.10273 0.09643 0.0109 0.0192 1.0000
17.000 1.0644 0.10853 0.10246 0.0088 0.0190 1.0000
17.250 1.0504 0.11490 0.10907 0.0060 0.0188 1.0000
17.500 1.0344 0.12201 0.11640 0.0026 0.0187 1.0000
17.750 1.0158 0.13013 0.12473 -0.0018 0.0188 1.0000
18.000 0.9929 0.13993 0.13476 -0.0075 0.0190 1.0000
18.250 0.9650 0.15205 0.14706 -0.0149 0.0196 1.0000
18.500 0.9327 0.16713 0.16224 -0.0238 0.0202 1.0000
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Polar data table (+)
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