I.S.A. 571 (isa571-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: I.S.A. 571 (isa571-il) Reynolds number: 500,000 Max Cl/Cd: 89.07 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-isa571-il-500000-n5.txt Download as CSV file: xf-isa571-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: I.S.A. 571
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3972 0.10509 0.10278 -0.0184 1.0000 0.0080
-9.500 -0.3958 0.10184 0.09955 -0.0189 1.0000 0.0075
-8.500 -0.4172 0.08693 0.08480 -0.0192 1.0000 0.0060
-8.250 -0.4285 0.08474 0.08265 -0.0172 1.0000 0.0059
-8.000 -0.4339 0.08164 0.07960 -0.0175 1.0000 0.0059
-7.750 -0.4230 0.07623 0.07419 -0.0236 0.9982 0.0059
-7.500 -0.3989 0.06857 0.06649 -0.0346 0.9953 0.0060
-7.000 -0.3419 0.02167 0.01781 -0.0750 0.9856 0.0065
-6.750 -0.3122 0.01968 0.01557 -0.0763 0.9827 0.0069
-6.500 -0.2791 0.01746 0.01299 -0.0781 0.9803 0.0074
-6.250 -0.2438 0.01551 0.01065 -0.0801 0.9783 0.0079
-6.000 -0.2101 0.01413 0.00898 -0.0816 0.9756 0.0084
-5.750 -0.1790 0.01318 0.00780 -0.0823 0.9715 0.0089
-5.500 -0.1447 0.01209 0.00648 -0.0837 0.9689 0.0098
-5.250 -0.1097 0.01142 0.00570 -0.0853 0.9667 0.0112
-5.000 -0.0814 0.01093 0.00513 -0.0853 0.9612 0.0128
-4.750 -0.0499 0.01038 0.00446 -0.0859 0.9565 0.0145
-4.500 -0.0185 0.00993 0.00399 -0.0866 0.9511 0.0191
-4.250 0.0111 0.00980 0.00390 -0.0868 0.9430 0.0261
-4.000 0.0422 0.00968 0.00373 -0.0873 0.9356 0.0311
-3.750 0.0734 0.00965 0.00369 -0.0879 0.9268 0.0345
-3.500 0.1039 0.00960 0.00357 -0.0882 0.9157 0.0376
-3.250 0.1345 0.00936 0.00327 -0.0887 0.9026 0.0399
-3.000 0.1648 0.00915 0.00302 -0.0891 0.8847 0.0428
-2.750 0.1939 0.00893 0.00268 -0.0892 0.8587 0.0440
-2.500 0.2212 0.00884 0.00240 -0.0888 0.8158 0.0457
-2.000 0.2697 0.00907 0.00199 -0.0868 0.6921 0.0477
-1.750 0.2948 0.00920 0.00188 -0.0861 0.6467 0.0486
-1.500 0.3208 0.00927 0.00178 -0.0857 0.6136 0.0494
-1.250 0.3474 0.00927 0.00164 -0.0854 0.5864 0.0515
-1.000 0.3740 0.00931 0.00156 -0.0852 0.5577 0.0538
-0.750 0.4004 0.00939 0.00150 -0.0849 0.5245 0.0562
-0.500 0.4266 0.00953 0.00147 -0.0845 0.4860 0.0590
-0.250 0.4525 0.00971 0.00148 -0.0842 0.4466 0.0640
0.000 0.4786 0.00987 0.00157 -0.0839 0.4128 0.0916
0.250 0.5051 0.01003 0.00163 -0.0837 0.3879 0.1043
0.500 0.5321 0.01013 0.00167 -0.0836 0.3728 0.1125
0.750 0.5594 0.01019 0.00171 -0.0835 0.3626 0.1208
1.250 0.6137 0.01031 0.00185 -0.0834 0.3431 0.1526
1.500 0.6343 0.00850 0.00205 -0.0822 0.3330 1.0000
1.750 0.6613 0.00866 0.00214 -0.0821 0.3228 1.0000
2.000 0.6883 0.00881 0.00223 -0.0820 0.3136 1.0000
2.250 0.7155 0.00895 0.00232 -0.0819 0.3059 1.0000
2.500 0.7425 0.00910 0.00244 -0.0818 0.2984 1.0000
2.750 0.7696 0.00924 0.00256 -0.0817 0.2914 1.0000
3.000 0.7965 0.00941 0.00269 -0.0816 0.2832 1.0000
3.250 0.8235 0.00955 0.00283 -0.0815 0.2750 1.0000
3.500 0.8502 0.00973 0.00298 -0.0813 0.2655 1.0000
3.750 0.8769 0.00992 0.00314 -0.0812 0.2541 1.0000
4.000 0.9032 0.01014 0.00331 -0.0810 0.2382 1.0000
4.250 0.9287 0.01046 0.00353 -0.0807 0.2123 1.0000
4.500 0.9543 0.01077 0.00377 -0.0804 0.1932 1.0000
4.750 0.9794 0.01114 0.00406 -0.0801 0.1762 1.0000
5.000 1.0044 0.01151 0.00438 -0.0798 0.1612 1.0000
5.250 1.0295 0.01187 0.00470 -0.0795 0.1470 1.0000
5.500 1.0539 0.01232 0.00504 -0.0791 0.1227 1.0000
5.750 1.0763 0.01302 0.00551 -0.0784 0.0864 1.0000
6.000 1.1004 0.01349 0.00596 -0.0779 0.0750 1.0000
6.250 1.1199 0.01457 0.00677 -0.0768 0.0239 1.0000
6.500 1.1430 0.01516 0.00737 -0.0761 0.0144 1.0000
6.750 1.1666 0.01565 0.00793 -0.0755 0.0119 1.0000
7.000 1.1889 0.01631 0.00868 -0.0747 0.0094 1.0000
7.250 1.2119 0.01685 0.00930 -0.0740 0.0086 1.0000
7.500 1.2343 0.01744 0.00998 -0.0732 0.0078 1.0000
7.750 1.2559 0.01809 0.01075 -0.0724 0.0071 1.0000
8.000 1.2758 0.01891 0.01163 -0.0713 0.0064 1.0000
8.250 1.2953 0.01973 0.01256 -0.0702 0.0059 1.0000
8.500 1.3149 0.02049 0.01343 -0.0690 0.0054 1.0000
8.750 1.3330 0.02136 0.01440 -0.0677 0.0051 1.0000
9.000 1.3501 0.02227 0.01541 -0.0662 0.0048 1.0000
9.250 1.3661 0.02323 0.01646 -0.0647 0.0046 1.0000
9.500 1.3803 0.02429 0.01761 -0.0628 0.0043 1.0000
9.750 1.3900 0.02563 0.01907 -0.0604 0.0042 1.0000
10.000 1.3945 0.02723 0.02080 -0.0572 0.0040 1.0000
10.250 1.4001 0.02846 0.02221 -0.0541 0.0039 1.0000
10.500 1.4047 0.02982 0.02370 -0.0511 0.0038 1.0000
10.750 1.4082 0.03130 0.02533 -0.0482 0.0037 1.0000
11.000 1.4109 0.03292 0.02708 -0.0455 0.0035 1.0000
11.250 1.4130 0.03466 0.02896 -0.0432 0.0034 1.0000
11.500 1.4139 0.03664 0.03108 -0.0411 0.0032 1.0000
11.750 1.4146 0.03875 0.03333 -0.0395 0.0031 1.0000
12.000 1.4131 0.04129 0.03600 -0.0382 0.0030 1.0000
12.250 1.4099 0.04425 0.03911 -0.0375 0.0030 1.0000
12.500 1.4058 0.04762 0.04263 -0.0374 0.0029 1.0000
12.750 1.4010 0.05140 0.04655 -0.0380 0.0029 1.0000
13.000 1.3945 0.05572 0.05103 -0.0391 0.0028 1.0000
13.250 1.3870 0.06041 0.05586 -0.0407 0.0028 1.0000
13.500 1.3781 0.06552 0.06112 -0.0426 0.0028 1.0000
13.750 1.3677 0.07100 0.06676 -0.0448 0.0028 1.0000
14.000 1.3560 0.07680 0.07269 -0.0472 0.0027 1.0000
14.250 1.3441 0.08277 0.07880 -0.0497 0.0027 1.0000
14.500 1.3311 0.08898 0.08515 -0.0523 0.0027 1.0000
14.750 1.3175 0.09535 0.09165 -0.0550 0.0027 1.0000
15.000 1.3039 0.10187 0.09830 -0.0579 0.0027 1.0000
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Polar data table (+)
Polar graphs
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