AH 83-159 (ah83159-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 83-159 (ah83159-il) Reynolds number: 1,000,000 Max Cl/Cd: 136.8 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah83159-il-1000000.txt Download as CSV file: xf-ah83159-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: AH 83-159
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.1438 0.08027 0.07767 -0.0892 0.7448 0.0119
-11.000 -0.1464 0.07554 0.07294 -0.0911 0.7430 0.0119
-10.750 -0.1473 0.07145 0.06884 -0.0928 0.7410 0.0121
-10.500 -0.1556 0.06537 0.06278 -0.0955 0.7397 0.0121
-10.250 -0.1651 0.05917 0.05660 -0.0985 0.7382 0.0122
-10.000 -0.2383 0.03917 0.03643 -0.1109 0.7378 0.0118
-9.750 -0.2640 0.03497 0.03214 -0.1110 0.7356 0.0119
-9.500 -0.2839 0.03198 0.02905 -0.1096 0.7332 0.0120
-9.250 -0.3059 0.02903 0.02595 -0.1068 0.7308 0.0119
-9.000 -0.3241 0.02705 0.02385 -0.1028 0.7282 0.0120
-8.750 -0.3293 0.02508 0.02177 -0.1002 0.7259 0.0121
-8.500 -0.3296 0.02298 0.01956 -0.0981 0.7238 0.0122
-8.250 -0.3988 0.02169 0.01671 -0.0921 0.7252 0.0088
-8.000 -0.3821 0.01976 0.01452 -0.0908 0.7232 0.0088
-7.750 -0.3597 0.01934 0.01404 -0.0904 0.7209 0.0092
-7.500 -0.3387 0.01800 0.01252 -0.0897 0.7187 0.0092
-7.250 -0.3163 0.01682 0.01117 -0.0890 0.7167 0.0093
-7.000 -0.2930 0.01589 0.01011 -0.0885 0.7147 0.0094
-6.750 -0.2689 0.01515 0.00925 -0.0882 0.7125 0.0096
-6.500 -0.2449 0.01433 0.00835 -0.0877 0.7109 0.0096
-6.250 -0.2209 0.01362 0.00757 -0.0873 0.7090 0.0098
-6.000 -0.1958 0.01316 0.00707 -0.0871 0.7069 0.0102
-5.750 -0.1712 0.01266 0.00651 -0.0867 0.7049 0.0104
-5.500 -0.1466 0.01216 0.00595 -0.0864 0.7030 0.0107
-5.250 -0.1221 0.01168 0.00540 -0.0860 0.7011 0.0110
-5.000 -0.0969 0.01133 0.00497 -0.0858 0.6991 0.0112
-4.750 -0.0726 0.01082 0.00440 -0.0854 0.6972 0.0118
-4.500 -0.0472 0.01041 0.00398 -0.0852 0.6954 0.0132
-4.250 -0.0204 0.01018 0.00374 -0.0853 0.6935 0.0149
-4.000 0.0059 0.00987 0.00340 -0.0852 0.6916 0.0176
-3.750 0.0328 0.00963 0.00317 -0.0853 0.6897 0.0231
-3.500 0.0597 0.00940 0.00296 -0.0853 0.6879 0.0330
-3.250 0.0867 0.00920 0.00281 -0.0855 0.6859 0.0493
-3.000 0.1129 0.00890 0.00267 -0.0856 0.6838 0.0956
-2.750 0.1381 0.00841 0.00250 -0.0857 0.6823 0.1858
-2.500 0.1613 0.00762 0.00231 -0.0857 0.6804 0.3553
-2.250 0.1836 0.00661 0.00207 -0.0856 0.6784 0.5790
-2.000 0.2079 0.00614 0.00209 -0.0852 0.6765 0.7256
-1.750 0.2362 0.00620 0.00220 -0.0853 0.6747 0.7614
-1.500 0.2650 0.00632 0.00229 -0.0855 0.6728 0.7773
-1.250 0.2941 0.00650 0.00241 -0.0858 0.6708 0.7901
-1.000 0.3226 0.00675 0.00265 -0.0859 0.6689 0.7978
-0.750 0.3513 0.00692 0.00281 -0.0861 0.6672 0.8055
-0.500 0.3792 0.00713 0.00304 -0.0860 0.6652 0.8101
-0.250 0.4078 0.00729 0.00318 -0.0862 0.6632 0.8149
0.000 0.4368 0.00740 0.00326 -0.0866 0.6612 0.8192
0.250 0.4644 0.00752 0.00338 -0.0865 0.6592 0.8217
0.500 0.4924 0.00765 0.00350 -0.0866 0.6571 0.8242
0.750 0.5209 0.00780 0.00361 -0.0869 0.6548 0.8268
1.000 0.5495 0.00783 0.00365 -0.0872 0.6529 0.8294
1.250 0.5788 0.00786 0.00367 -0.0878 0.6505 0.8317
1.500 0.6079 0.00786 0.00366 -0.0884 0.6479 0.8333
1.750 0.6359 0.00784 0.00364 -0.0886 0.6454 0.8344
2.000 0.6641 0.00787 0.00365 -0.0889 0.6428 0.8355
2.250 0.6923 0.00792 0.00369 -0.0892 0.6399 0.8366
2.500 0.7202 0.00791 0.00371 -0.0895 0.6367 0.8377
2.750 0.7485 0.00791 0.00372 -0.0898 0.6333 0.8389
3.000 0.7767 0.00793 0.00374 -0.0902 0.6303 0.8402
3.250 0.8052 0.00798 0.00377 -0.0906 0.6272 0.8414
3.500 0.8336 0.00800 0.00382 -0.0911 0.6243 0.8427
3.750 0.8620 0.00801 0.00386 -0.0915 0.6209 0.8440
4.000 0.8905 0.00803 0.00389 -0.0920 0.6174 0.8454
4.250 0.9190 0.00809 0.00394 -0.0925 0.6139 0.8465
4.500 0.9471 0.00811 0.00398 -0.0929 0.6103 0.8474
4.750 0.9744 0.00808 0.00400 -0.0931 0.6063 0.8482
5.000 1.0014 0.00810 0.00403 -0.0933 0.6015 0.8491
5.250 1.0281 0.00815 0.00410 -0.0934 0.5964 0.8500
5.500 1.0550 0.00816 0.00417 -0.0935 0.5902 0.8510
5.750 1.0809 0.00824 0.00423 -0.0935 0.5832 0.8519
6.000 1.1073 0.00828 0.00432 -0.0935 0.5744 0.8528
6.250 1.1328 0.00836 0.00442 -0.0934 0.5650 0.8538
6.500 1.1573 0.00848 0.00453 -0.0932 0.5537 0.8548
6.750 1.1806 0.00863 0.00467 -0.0927 0.5381 0.8560
7.250 1.2161 0.00932 0.00518 -0.0897 0.4850 0.8586
7.500 1.2294 0.00980 0.00554 -0.0875 0.4558 0.8598
7.750 1.2359 0.01041 0.00600 -0.0840 0.4215 0.8608
8.000 1.2319 0.01096 0.00642 -0.0784 0.3918 0.8627
8.250 1.2212 0.01193 0.00725 -0.0722 0.3571 0.8646
8.500 1.2206 0.01282 0.00805 -0.0681 0.3345 0.8661
8.750 1.2113 0.01419 0.00925 -0.0631 0.2987 0.8678
9.000 1.2100 0.01540 0.01034 -0.0595 0.2717 0.8693
9.250 1.2052 0.01686 0.01164 -0.0556 0.2399 0.8710
9.500 1.2005 0.01842 0.01303 -0.0521 0.2071 0.8723
9.750 1.1978 0.01998 0.01443 -0.0489 0.1767 0.8733
10.000 1.1964 0.02155 0.01585 -0.0461 0.1487 0.8741
10.250 1.1969 0.02305 0.01723 -0.0436 0.1252 0.8749
10.500 1.1974 0.02457 0.01863 -0.0412 0.1021 0.8760
10.750 1.2003 0.02601 0.01998 -0.0391 0.0827 0.8771
11.000 1.2035 0.02751 0.02140 -0.0372 0.0658 0.8780
11.250 1.2083 0.02899 0.02283 -0.0356 0.0517 0.8788
11.500 1.2149 0.03040 0.02418 -0.0342 0.0408 0.8795
11.750 1.2210 0.03190 0.02565 -0.0329 0.0314 0.8802
12.000 1.2289 0.03331 0.02704 -0.0317 0.0250 0.8808
12.250 1.2380 0.03467 0.02841 -0.0308 0.0209 0.8815
12.500 1.2451 0.03622 0.02995 -0.0298 0.0153 0.8822
12.750 1.2505 0.03796 0.03167 -0.0287 0.0107 0.8829
13.000 1.2568 0.03967 0.03341 -0.0277 0.0080 0.8837
13.250 1.2615 0.04156 0.03534 -0.0268 0.0065 0.8844
13.500 1.2701 0.04318 0.03702 -0.0261 0.0060 0.8850
13.750 1.2796 0.04475 0.03864 -0.0256 0.0056 0.8856
14.000 1.2863 0.04661 0.04055 -0.0250 0.0050 0.8861
14.250 1.2898 0.04883 0.04284 -0.0243 0.0046 0.8866
14.500 1.2932 0.05112 0.04521 -0.0238 0.0044 0.8870
14.750 1.2970 0.05344 0.04762 -0.0233 0.0043 0.8874
15.000 1.3038 0.05549 0.04973 -0.0231 0.0043 0.8878
15.250 1.3094 0.05770 0.05203 -0.0229 0.0041 0.8881
15.500 1.3155 0.05989 0.05429 -0.0228 0.0041 0.8885
15.750 1.3169 0.06270 0.05720 -0.0227 0.0040 0.8891
16.000 1.3216 0.06517 0.05975 -0.0228 0.0039 0.8897
16.250 1.3241 0.06794 0.06262 -0.0229 0.0038 0.8902
16.500 1.3270 0.07072 0.06548 -0.0231 0.0037 0.8909
16.750 1.3272 0.07389 0.06875 -0.0234 0.0037 0.8915
17.000 1.3286 0.07699 0.07194 -0.0238 0.0036 0.8921
17.250 1.3297 0.08020 0.07524 -0.0244 0.0036 0.8927
17.500 1.3294 0.08368 0.07882 -0.0251 0.0035 0.8931
17.750 1.3259 0.08768 0.08293 -0.0259 0.0034 0.8935
18.000 1.3272 0.09104 0.08637 -0.0269 0.0034 0.8940
18.250 1.3262 0.09482 0.09024 -0.0280 0.0033 0.8944
18.500 1.3248 0.09871 0.09422 -0.0292 0.0032 0.8948
18.750 1.3218 0.10292 0.09854 -0.0306 0.0032 0.8952
19.000 1.3169 0.10747 0.10319 -0.0323 0.0031 0.8956
19.250 1.3132 0.11192 0.10775 -0.0340 0.0031 0.8959
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Polar data table (+)
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