AH 93-157 (ah93157-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 93-157 (ah93157-il) Reynolds number: 1,000,000 Max Cl/Cd: 112.24 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah93157-il-1000000-n5.txt Download as CSV file: xf-ah93157-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 93-157
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.000 -0.7928 0.05737 0.05399 -0.1140 0.8232 0.0080
-16.750 -0.8416 0.04515 0.04143 -0.1232 0.8175 0.0079
-16.500 -0.8570 0.04034 0.03646 -0.1258 0.8125 0.0079
-16.250 -0.8706 0.03664 0.03260 -0.1266 0.8075 0.0079
-16.000 -0.8757 0.03419 0.03003 -0.1263 0.8026 0.0080
-15.750 -0.8803 0.03204 0.02775 -0.1254 0.7984 0.0081
-15.500 -0.8795 0.03041 0.02602 -0.1242 0.7945 0.0081
-15.250 -0.8793 0.02886 0.02435 -0.1227 0.7905 0.0082
-15.000 -0.8742 0.02768 0.02308 -0.1211 0.7869 0.0084
-14.750 -0.8709 0.02647 0.02175 -0.1192 0.7836 0.0084
-14.500 -0.8619 0.02556 0.02078 -0.1177 0.7811 0.0086
-14.250 -0.8547 0.02458 0.01971 -0.1158 0.7781 0.0087
-14.000 -0.8470 0.02366 0.01869 -0.1138 0.7749 0.0088
-13.750 -0.8373 0.02287 0.01781 -0.1119 0.7718 0.0090
-13.500 -0.8290 0.02202 0.01685 -0.1098 0.7689 0.0091
-13.250 -0.8168 0.02137 0.01612 -0.1080 0.7666 0.0092
-13.000 -0.8044 0.02070 0.01537 -0.1061 0.7643 0.0094
-12.750 -0.7918 0.02007 0.01467 -0.1042 0.7617 0.0095
-12.500 -0.7780 0.01953 0.01404 -0.1024 0.7590 0.0097
-12.250 -0.7647 0.01897 0.01341 -0.1004 0.7564 0.0098
-12.000 -0.7541 0.01830 0.01266 -0.0979 0.7540 0.0101
-11.500 -0.7242 0.01735 0.01159 -0.0942 0.7500 0.0105
-11.250 -0.7052 0.01691 0.01111 -0.0930 0.7480 0.0108
-11.000 -0.6855 0.01650 0.01064 -0.0919 0.7458 0.0110
-10.750 -0.6655 0.01607 0.01016 -0.0908 0.7434 0.0112
-10.500 -0.6448 0.01568 0.00971 -0.0899 0.7411 0.0115
-10.250 -0.6239 0.01529 0.00925 -0.0889 0.7391 0.0118
-10.000 -0.6022 0.01493 0.00882 -0.0881 0.7371 0.0121
-9.750 -0.5800 0.01459 0.00842 -0.0873 0.7351 0.0123
-9.500 -0.5574 0.01423 0.00802 -0.0867 0.7332 0.0126
-9.250 -0.5352 0.01380 0.00756 -0.0859 0.7311 0.0132
-9.000 -0.5119 0.01347 0.00721 -0.0853 0.7290 0.0136
-8.750 -0.4881 0.01320 0.00690 -0.0848 0.7268 0.0141
-8.500 -0.4641 0.01292 0.00658 -0.0843 0.7246 0.0146
-8.250 -0.4401 0.01266 0.00627 -0.0838 0.7224 0.0151
-8.000 -0.4157 0.01241 0.00597 -0.0833 0.7204 0.0155
-7.750 -0.3915 0.01210 0.00563 -0.0829 0.7187 0.0161
-7.500 -0.3668 0.01181 0.00534 -0.0825 0.7167 0.0168
-7.250 -0.3417 0.01157 0.00509 -0.0821 0.7145 0.0176
-7.000 -0.3164 0.01136 0.00485 -0.0818 0.7122 0.0184
-6.750 -0.2909 0.01116 0.00461 -0.0816 0.7100 0.0192
-6.500 -0.2659 0.01092 0.00435 -0.0812 0.7078 0.0202
-6.250 -0.2405 0.01072 0.00414 -0.0809 0.7056 0.0214
-6.000 -0.2147 0.01054 0.00394 -0.0806 0.7035 0.0226
-5.750 -0.1885 0.01036 0.00375 -0.0805 0.7015 0.0238
-5.500 -0.1626 0.01015 0.00356 -0.0803 0.6991 0.0256
-5.250 -0.1365 0.00999 0.00339 -0.0801 0.6966 0.0279
-5.000 -0.1103 0.00983 0.00322 -0.0799 0.6942 0.0301
-4.750 -0.0843 0.00967 0.00306 -0.0797 0.6918 0.0328
-4.500 -0.0580 0.00955 0.00291 -0.0795 0.6894 0.0355
-4.250 -0.0315 0.00938 0.00278 -0.0794 0.6873 0.0400
-4.000 -0.0048 0.00924 0.00266 -0.0794 0.6848 0.0444
-3.750 0.0217 0.00910 0.00254 -0.0793 0.6820 0.0498
-3.500 0.0482 0.00896 0.00242 -0.0791 0.6791 0.0570
-3.250 0.0745 0.00884 0.00231 -0.0790 0.6761 0.0657
-3.000 0.1009 0.00872 0.00221 -0.0789 0.6734 0.0758
-2.750 0.1275 0.00856 0.00212 -0.0788 0.6709 0.0917
-2.500 0.1540 0.00841 0.00204 -0.0787 0.6678 0.1109
-2.250 0.1801 0.00825 0.00196 -0.0786 0.6647 0.1356
-2.000 0.2059 0.00809 0.00189 -0.0784 0.6616 0.1670
-1.750 0.2314 0.00792 0.00182 -0.0782 0.6584 0.2037
-1.500 0.2570 0.00769 0.00176 -0.0780 0.6551 0.2538
-1.250 0.2816 0.00742 0.00170 -0.0776 0.6515 0.3215
-1.000 0.3053 0.00711 0.00164 -0.0771 0.6476 0.4043
-0.750 0.3284 0.00681 0.00157 -0.0765 0.6437 0.4888
-0.500 0.3486 0.00625 0.00148 -0.0753 0.6400 0.6311
-0.250 0.3684 0.00584 0.00152 -0.0738 0.6358 0.7612
0.000 0.3935 0.00589 0.00169 -0.0731 0.6311 0.8115
0.250 0.4209 0.00599 0.00176 -0.0730 0.6266 0.8282
0.500 0.4485 0.00609 0.00188 -0.0730 0.6216 0.8387
0.750 0.4757 0.00622 0.00198 -0.0729 0.6167 0.8473
1.000 0.5025 0.00638 0.00213 -0.0727 0.6118 0.8547
1.250 0.5299 0.00650 0.00222 -0.0727 0.6057 0.8603
1.500 0.5560 0.00664 0.00235 -0.0723 0.5994 0.8637
1.750 0.5831 0.00673 0.00243 -0.0722 0.5937 0.8663
2.000 0.6102 0.00680 0.00247 -0.0723 0.5869 0.8676
2.250 0.6370 0.00687 0.00251 -0.0722 0.5805 0.8689
2.500 0.6639 0.00694 0.00255 -0.0722 0.5729 0.8700
2.750 0.6902 0.00702 0.00259 -0.0721 0.5656 0.8713
3.000 0.7168 0.00710 0.00265 -0.0721 0.5576 0.8724
3.250 0.7426 0.00720 0.00271 -0.0719 0.5494 0.8734
3.500 0.7679 0.00731 0.00278 -0.0717 0.5391 0.8742
3.750 0.7932 0.00741 0.00286 -0.0714 0.5296 0.8751
4.000 0.8172 0.00754 0.00295 -0.0708 0.5199 0.8760
4.250 0.8415 0.00766 0.00305 -0.0704 0.5099 0.8767
4.500 0.8653 0.00779 0.00316 -0.0698 0.4997 0.8775
4.750 0.8879 0.00795 0.00329 -0.0690 0.4891 0.8783
5.000 0.9103 0.00812 0.00343 -0.0682 0.4778 0.8793
5.250 0.9316 0.00830 0.00358 -0.0672 0.4650 0.8803
5.500 0.9518 0.00850 0.00374 -0.0659 0.4522 0.8813
5.750 0.9712 0.00871 0.00391 -0.0646 0.4402 0.8823
6.000 0.9881 0.00892 0.00409 -0.0627 0.4284 0.8834
6.250 1.0043 0.00911 0.00426 -0.0606 0.4170 0.8845
6.500 1.0179 0.00937 0.00448 -0.0581 0.4035 0.8860
6.750 1.0303 0.00971 0.00476 -0.0555 0.3886 0.8873
7.000 1.0422 0.01007 0.00508 -0.0528 0.3740 0.8884
7.250 1.0552 0.01043 0.00541 -0.0504 0.3625 0.8893
7.500 1.0664 0.01083 0.00577 -0.0478 0.3499 0.8904
7.750 1.0749 0.01133 0.00622 -0.0448 0.3332 0.8917
8.000 1.0799 0.01199 0.00680 -0.0414 0.3116 0.8932
8.250 1.0825 0.01282 0.00751 -0.0378 0.2879 0.8946
8.500 1.0851 0.01372 0.00831 -0.0344 0.2625 0.8960
8.750 1.0897 0.01462 0.00910 -0.0314 0.2401 0.8973
9.000 1.0963 0.01548 0.00988 -0.0288 0.2209 0.8985
9.250 1.1030 0.01639 0.01071 -0.0263 0.2029 0.8996
9.500 1.1086 0.01738 0.01161 -0.0238 0.1827 0.9009
9.750 1.1141 0.01842 0.01255 -0.0214 0.1632 0.9021
10.000 1.1183 0.01956 0.01360 -0.0190 0.1435 0.9031
10.250 1.1233 0.02070 0.01464 -0.0167 0.1237 0.9039
10.500 1.1299 0.02178 0.01566 -0.0147 0.1084 0.9049
10.750 1.1342 0.02303 0.01683 -0.0126 0.0920 0.9059
11.000 1.1399 0.02423 0.01797 -0.0107 0.0762 0.9069
11.250 1.1442 0.02558 0.01925 -0.0088 0.0611 0.9079
11.500 1.1498 0.02691 0.02052 -0.0070 0.0493 0.9088
11.750 1.1579 0.02812 0.02171 -0.0057 0.0415 0.9097
12.000 1.1650 0.02943 0.02300 -0.0043 0.0339 0.9105
12.250 1.1754 0.03057 0.02415 -0.0033 0.0303 0.9114
12.500 1.1841 0.03186 0.02544 -0.0022 0.0261 0.9123
12.750 1.1931 0.03315 0.02674 -0.0012 0.0226 0.9133
13.000 1.2026 0.03443 0.02804 -0.0003 0.0199 0.9143
13.250 1.2120 0.03577 0.02940 0.0006 0.0180 0.9152
13.500 1.2209 0.03718 0.03083 0.0013 0.0156 0.9159
13.750 1.2301 0.03861 0.03229 0.0020 0.0145 0.9166
14.000 1.2392 0.04007 0.03379 0.0027 0.0132 0.9173
14.500 1.2561 0.04320 0.03699 0.0038 0.0113 0.9189
14.750 1.2637 0.04489 0.03874 0.0043 0.0104 0.9198
15.000 1.2724 0.04652 0.04042 0.0047 0.0100 0.9207
15.250 1.2796 0.04831 0.04226 0.0050 0.0095 0.9217
15.500 1.2858 0.05024 0.04424 0.0054 0.0088 0.9226
15.750 1.2913 0.05229 0.04634 0.0057 0.0083 0.9236
16.000 1.2983 0.05422 0.04834 0.0058 0.0079 0.9246
16.250 1.3048 0.05624 0.05042 0.0059 0.0075 0.9256
16.500 1.3096 0.05849 0.05274 0.0059 0.0074 0.9266
16.750 1.3139 0.06082 0.05513 0.0059 0.0070 0.9277
17.000 1.3177 0.06327 0.05764 0.0058 0.0068 0.9287
17.250 1.3198 0.06595 0.06037 0.0055 0.0063 0.9298
17.500 1.3241 0.06843 0.06293 0.0053 0.0061 0.9308
18.000 1.3294 0.07395 0.06862 0.0043 0.0058 0.9335
18.250 1.3315 0.07686 0.07161 0.0037 0.0057 0.9350
18.500 1.3326 0.07998 0.07481 0.0029 0.0055 0.9366
18.750 1.3335 0.08320 0.07811 0.0020 0.0054 0.9384
19.000 1.3338 0.08655 0.08155 0.0010 0.0052 0.9403
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