AH 93-157 (ah93157-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 93-157 (ah93157-il) Reynolds number: 500,000 Max Cl/Cd: 91.96 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah93157-il-500000-n5.txt Download as CSV file: xf-ah93157-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.6057 0.05348 0.04973 -0.1179 0.8253 0.0112
-14.500 -0.6357 0.04544 0.04143 -0.1236 0.8198 0.0113
-14.250 -0.6564 0.04072 0.03648 -0.1253 0.8149 0.0113
-14.000 -0.6696 0.03750 0.03308 -0.1251 0.8105 0.0114
-13.750 -0.6774 0.03509 0.03050 -0.1241 0.8064 0.0116
-13.500 -0.6851 0.03288 0.02809 -0.1223 0.8025 0.0116
-13.250 -0.6868 0.03121 0.02624 -0.1203 0.7990 0.0118
-13.000 -0.6876 0.02960 0.02446 -0.1181 0.7953 0.0120
-12.750 -0.6864 0.02817 0.02286 -0.1158 0.7918 0.0121
-12.500 -0.6827 0.02692 0.02143 -0.1135 0.7885 0.0122
-12.250 -0.6759 0.02587 0.02021 -0.1113 0.7857 0.0124
-12.000 -0.6703 0.02476 0.01897 -0.1088 0.7830 0.0126
-11.750 -0.6626 0.02382 0.01794 -0.1065 0.7801 0.0128
-11.500 -0.6536 0.02296 0.01699 -0.1041 0.7770 0.0130
-11.250 -0.6417 0.02233 0.01628 -0.1020 0.7741 0.0132
-11.000 -0.6295 0.02174 0.01560 -0.0999 0.7716 0.0135
-10.750 -0.6156 0.02115 0.01491 -0.0980 0.7694 0.0138
-10.500 -0.5991 0.02056 0.01420 -0.0965 0.7673 0.0141
-10.250 -0.5818 0.01991 0.01346 -0.0952 0.7649 0.0145
-10.000 -0.5626 0.01938 0.01283 -0.0940 0.7624 0.0150
-9.750 -0.5431 0.01883 0.01217 -0.0929 0.7598 0.0155
-9.500 -0.5242 0.01822 0.01148 -0.0918 0.7575 0.0159
-9.250 -0.5042 0.01769 0.01090 -0.0908 0.7554 0.0165
-9.000 -0.4831 0.01724 0.01037 -0.0899 0.7534 0.0169
-8.750 -0.4615 0.01680 0.00986 -0.0891 0.7512 0.0174
-8.500 -0.4393 0.01638 0.00939 -0.0884 0.7490 0.0181
-8.250 -0.4170 0.01595 0.00889 -0.0876 0.7466 0.0186
-8.000 -0.3939 0.01558 0.00845 -0.0870 0.7443 0.0193
-7.750 -0.3719 0.01511 0.00795 -0.0862 0.7420 0.0201
-7.500 -0.3485 0.01477 0.00758 -0.0856 0.7397 0.0210
-7.250 -0.3246 0.01447 0.00722 -0.0851 0.7377 0.0221
-7.000 -0.3007 0.01415 0.00683 -0.0846 0.7358 0.0229
-6.750 -0.2769 0.01382 0.00646 -0.0841 0.7336 0.0239
-6.500 -0.2531 0.01348 0.00613 -0.0835 0.7312 0.0252
-6.250 -0.2284 0.01323 0.00585 -0.0831 0.7288 0.0268
-6.000 -0.2035 0.01299 0.00557 -0.0828 0.7265 0.0284
-5.750 -0.1792 0.01269 0.00526 -0.0823 0.7242 0.0304
-5.500 -0.1541 0.01246 0.00500 -0.0819 0.7221 0.0326
-5.250 -0.1286 0.01228 0.00475 -0.0816 0.7200 0.0348
-5.000 -0.1038 0.01202 0.00454 -0.0813 0.7177 0.0382
-4.750 -0.0783 0.01184 0.00434 -0.0810 0.7151 0.0417
-4.500 -0.0532 0.01162 0.00415 -0.0806 0.7125 0.0463
-4.250 -0.0274 0.01145 0.00396 -0.0804 0.7100 0.0512
-4.000 -0.0019 0.01125 0.00378 -0.0801 0.7077 0.0587
-3.750 0.0238 0.01108 0.00361 -0.0799 0.7055 0.0672
-3.500 0.0494 0.01091 0.00347 -0.0796 0.7031 0.0784
-3.250 0.0748 0.01072 0.00335 -0.0793 0.7004 0.0936
-3.000 0.1002 0.01053 0.00324 -0.0791 0.6975 0.1143
-2.750 0.1253 0.01031 0.00311 -0.0788 0.6947 0.1415
-2.500 0.1502 0.01009 0.00299 -0.0784 0.6919 0.1774
-2.250 0.1748 0.00983 0.00287 -0.0780 0.6893 0.2246
-2.000 0.1981 0.00951 0.00279 -0.0775 0.6863 0.2910
-1.750 0.2205 0.00913 0.00271 -0.0768 0.6832 0.3758
-1.500 0.2407 0.00862 0.00259 -0.0757 0.6800 0.4882
-1.250 0.2564 0.00789 0.00246 -0.0736 0.6770 0.6548
-1.000 0.2758 0.00777 0.00278 -0.0714 0.6742 0.7776
-0.750 0.3016 0.00794 0.00300 -0.0707 0.6708 0.8106
-0.500 0.3283 0.00806 0.00310 -0.0705 0.6670 0.8293
-0.250 0.3548 0.00821 0.00322 -0.0701 0.6634 0.8422
0.000 0.3809 0.00842 0.00339 -0.0695 0.6600 0.8511
0.250 0.4065 0.00861 0.00357 -0.0689 0.6561 0.8613
0.500 0.4311 0.00885 0.00381 -0.0680 0.6519 0.8692
0.750 0.4562 0.00899 0.00393 -0.0673 0.6477 0.8764
1.000 0.4812 0.00911 0.00401 -0.0665 0.6437 0.8803
1.250 0.5076 0.00914 0.00404 -0.0664 0.6389 0.8825
1.500 0.5343 0.00915 0.00403 -0.0663 0.6339 0.8843
1.750 0.5612 0.00917 0.00400 -0.0664 0.6294 0.8861
2.000 0.5882 0.00918 0.00400 -0.0664 0.6243 0.8877
2.250 0.6150 0.00920 0.00400 -0.0665 0.6183 0.8893
2.500 0.6408 0.00923 0.00398 -0.0663 0.6129 0.8903
2.750 0.6667 0.00924 0.00401 -0.0661 0.6069 0.8913
3.000 0.6919 0.00928 0.00404 -0.0657 0.6006 0.8924
3.250 0.7172 0.00933 0.00408 -0.0654 0.5943 0.8935
3.500 0.7423 0.00938 0.00412 -0.0651 0.5870 0.8946
3.750 0.7672 0.00944 0.00416 -0.0647 0.5801 0.8957
4.000 0.7917 0.00951 0.00423 -0.0643 0.5722 0.8970
4.250 0.8156 0.00960 0.00429 -0.0638 0.5641 0.8984
4.500 0.8391 0.00969 0.00437 -0.0632 0.5550 0.8997
4.750 0.8627 0.00979 0.00447 -0.0626 0.5461 0.9009
5.000 0.8848 0.00992 0.00457 -0.0618 0.5365 0.9021
5.250 0.9074 0.01005 0.00469 -0.0611 0.5266 0.9034
5.500 0.9280 0.01018 0.00481 -0.0600 0.5169 0.9045
6.000 0.9647 0.01049 0.00510 -0.0568 0.4952 0.9066
6.250 0.9791 0.01066 0.00525 -0.0544 0.4836 0.9079
6.500 0.9920 0.01087 0.00545 -0.0518 0.4721 0.9095
6.750 1.0038 0.01116 0.00571 -0.0491 0.4596 0.9115
7.000 1.0179 0.01145 0.00599 -0.0469 0.4480 0.9130
7.250 1.0310 0.01178 0.00631 -0.0446 0.4364 0.9144
7.500 1.0417 0.01220 0.00671 -0.0420 0.4227 0.9160
7.750 1.0514 0.01269 0.00716 -0.0393 0.4084 0.9174
8.000 1.0602 0.01319 0.00764 -0.0366 0.3951 0.9192
8.250 1.0689 0.01375 0.00818 -0.0339 0.3820 0.9208
8.500 1.0786 0.01434 0.00876 -0.0315 0.3688 0.9223
8.750 1.0853 0.01509 0.00946 -0.0288 0.3524 0.9240
9.000 1.0881 0.01605 0.01034 -0.0257 0.3288 0.9258
9.250 1.0892 0.01717 0.01134 -0.0226 0.3048 0.9277
9.500 1.0938 0.01820 0.01229 -0.0201 0.2831 0.9295
9.750 1.0996 0.01923 0.01324 -0.0178 0.2643 0.9313
10.000 1.1043 0.02035 0.01429 -0.0155 0.2445 0.9328
10.250 1.1113 0.02140 0.01528 -0.0136 0.2263 0.9343
10.500 1.1166 0.02258 0.01639 -0.0116 0.2062 0.9359
10.750 1.1209 0.02389 0.01762 -0.0096 0.1859 0.9376
11.000 1.1259 0.02521 0.01885 -0.0078 0.1649 0.9393
11.250 1.1292 0.02669 0.02025 -0.0060 0.1438 0.9410
11.500 1.1344 0.02819 0.02166 -0.0046 0.1240 0.9426
11.750 1.1374 0.02988 0.02325 -0.0031 0.1033 0.9443
12.000 1.1437 0.03150 0.02480 -0.0021 0.0862 0.9460
12.250 1.1488 0.03337 0.02660 -0.0014 0.0687 0.9481
12.500 1.1560 0.03520 0.02837 -0.0010 0.0547 0.9502
12.750 1.1640 0.03706 0.03020 -0.0007 0.0440 0.9523
13.000 1.1737 0.03884 0.03199 -0.0007 0.0372 0.9543
13.250 1.1835 0.04069 0.03386 -0.0008 0.0316 0.9563
13.500 1.1949 0.04252 0.03572 -0.0012 0.0277 0.9584
13.750 1.2066 0.04446 0.03771 -0.0019 0.0241 0.9612
14.000 1.2176 0.04657 0.03986 -0.0027 0.0215 0.9640
14.250 1.2294 0.04856 0.04192 -0.0034 0.0193 0.9671
14.500 1.2371 0.05070 0.04412 -0.0038 0.0175 0.9773
14.750 1.2403 0.05265 0.04612 -0.0028 0.0163 1.0000
15.000 1.2463 0.05475 0.04828 -0.0026 0.0153 1.0000
15.250 1.2505 0.05707 0.05066 -0.0024 0.0144 1.0000
15.500 1.2537 0.05952 0.05317 -0.0023 0.0135 1.0000
15.750 1.2585 0.06184 0.05556 -0.0023 0.0126 1.0000
16.000 1.2616 0.06442 0.05822 -0.0023 0.0121 1.0000
16.250 1.2647 0.06701 0.06087 -0.0024 0.0114 1.0000
16.500 1.2653 0.06995 0.06388 -0.0026 0.0109 1.0000
16.750 1.2663 0.07289 0.06691 -0.0029 0.0105 1.0000
17.000 1.2680 0.07580 0.06990 -0.0033 0.0101 1.0000
17.250 1.2687 0.07888 0.07307 -0.0038 0.0098 1.0000
17.500 1.2689 0.08209 0.07637 -0.0044 0.0094 1.0000
17.750 1.2684 0.08542 0.07978 -0.0051 0.0091 1.0000
18.000 1.2667 0.08896 0.08341 -0.0059 0.0089 1.0000
18.250 1.2638 0.09270 0.08723 -0.0068 0.0087 1.0000
18.500 1.2589 0.09682 0.09145 -0.0079 0.0084 1.0000
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Polar data table (+)
Polar graphs
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