I.S.A. 571 (isa571-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: I.S.A. 571 (isa571-il) Reynolds number: 1,000,000 Max Cl/Cd: 109.42 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-isa571-il-1000000.txt Download as CSV file: xf-isa571-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4200 0.08998 0.08841 -0.0193 1.0000 0.0106
-8.500 -0.4284 0.08746 0.08593 -0.0179 1.0000 0.0106
-8.250 -0.4519 0.08335 0.08188 -0.0164 1.0000 0.0108
-8.000 -0.4537 0.08075 0.07929 -0.0166 1.0000 0.0110
-7.750 -0.4531 0.07825 0.07681 -0.0170 1.0000 0.0112
-7.500 -0.4346 0.07480 0.07335 -0.0216 0.9989 0.0115
-7.250 -0.4195 0.01965 0.01645 -0.0650 0.9930 0.0091
-7.000 -0.3872 0.01677 0.01314 -0.0669 0.9910 0.0097
-6.750 -0.3530 0.01502 0.01105 -0.0687 0.9891 0.0102
-6.500 -0.3180 0.01399 0.00982 -0.0704 0.9876 0.0105
-6.250 -0.2851 0.01170 0.00710 -0.0719 0.9865 0.0115
-6.000 -0.2494 0.01107 0.00638 -0.0737 0.9853 0.0123
-5.750 -0.2132 0.01052 0.00574 -0.0754 0.9844 0.0132
-5.500 -0.1774 0.01002 0.00514 -0.0771 0.9836 0.0142
-5.250 -0.1486 0.00937 0.00439 -0.0772 0.9801 0.0155
-5.000 -0.1146 0.00900 0.00403 -0.0785 0.9773 0.0177
-4.750 -0.0786 0.00873 0.00372 -0.0801 0.9754 0.0196
-4.500 -0.0438 0.00839 0.00340 -0.0815 0.9738 0.0239
-4.250 -0.0096 0.00821 0.00322 -0.0828 0.9720 0.0277
-4.000 0.0216 0.00827 0.00334 -0.0833 0.9688 0.0313
-3.750 0.0504 0.00834 0.00342 -0.0833 0.9632 0.0340
-3.500 0.0815 0.00800 0.00304 -0.0839 0.9585 0.0364
-3.250 0.1092 0.00776 0.00280 -0.0837 0.9496 0.0391
-3.000 0.1387 0.00761 0.00265 -0.0838 0.9399 0.0416
-2.750 0.1673 0.00743 0.00243 -0.0838 0.9273 0.0435
-2.500 0.1955 0.00736 0.00231 -0.0836 0.9104 0.0451
-2.250 0.2230 0.00731 0.00218 -0.0832 0.8827 0.0458
-2.000 0.2484 0.00699 0.00161 -0.0824 0.8337 0.0488
-1.750 0.2719 0.00714 0.00143 -0.0813 0.7591 0.0513
-1.500 0.2964 0.00731 0.00133 -0.0805 0.6967 0.0528
-1.250 0.3222 0.00744 0.00126 -0.0800 0.6526 0.0542
-1.000 0.3484 0.00755 0.00119 -0.0796 0.6129 0.0557
-0.750 0.3750 0.00767 0.00114 -0.0793 0.5737 0.0573
-0.500 0.4014 0.00781 0.00110 -0.0790 0.5278 0.0605
-0.250 0.4276 0.00795 0.00113 -0.0787 0.4786 0.0755
0.000 0.4541 0.00811 0.00119 -0.0785 0.4408 0.1039
0.250 0.4812 0.00825 0.00123 -0.0783 0.4147 0.1140
0.500 0.5084 0.00835 0.00127 -0.0782 0.3956 0.1222
0.750 0.5357 0.00842 0.00132 -0.0781 0.3796 0.1331
1.000 0.5631 0.00819 0.00140 -0.0783 0.3652 0.2935
1.250 0.5839 0.00663 0.00157 -0.0771 0.3545 0.9966
1.500 0.6118 0.00674 0.00162 -0.0771 0.3453 1.0000
1.750 0.6393 0.00687 0.00169 -0.0770 0.3369 1.0000
2.000 0.6668 0.00698 0.00176 -0.0770 0.3286 1.0000
2.250 0.6943 0.00710 0.00184 -0.0769 0.3210 1.0000
2.500 0.7218 0.00723 0.00192 -0.0769 0.3130 1.0000
2.750 0.7493 0.00735 0.00202 -0.0768 0.3062 1.0000
3.000 0.7766 0.00748 0.00212 -0.0767 0.2983 1.0000
3.250 0.8041 0.00760 0.00222 -0.0767 0.2908 1.0000
3.500 0.8312 0.00775 0.00234 -0.0766 0.2817 1.0000
3.750 0.8585 0.00788 0.00246 -0.0766 0.2718 1.0000
4.000 0.8852 0.00809 0.00259 -0.0764 0.2539 1.0000
4.250 0.9112 0.00838 0.00275 -0.0762 0.2257 1.0000
4.500 0.9357 0.00887 0.00301 -0.0758 0.1839 1.0000
4.750 0.9616 0.00917 0.00326 -0.0756 0.1693 1.0000
5.000 0.9876 0.00945 0.00349 -0.0754 0.1586 1.0000
5.250 1.0136 0.00972 0.00372 -0.0752 0.1465 1.0000
5.500 1.0391 0.01005 0.00397 -0.0749 0.1277 1.0000
5.750 1.0626 0.01067 0.00437 -0.0744 0.0893 1.0000
6.000 1.0874 0.01108 0.00473 -0.0740 0.0763 1.0000
6.250 1.1071 0.01222 0.00553 -0.0728 0.0224 1.0000
6.500 1.1314 0.01271 0.00604 -0.0723 0.0164 1.0000
6.750 1.1550 0.01329 0.00668 -0.0716 0.0135 1.0000
7.000 1.1793 0.01375 0.00720 -0.0711 0.0126 1.0000
7.250 1.2033 0.01421 0.00772 -0.0705 0.0117 1.0000
7.500 1.2269 0.01472 0.00828 -0.0699 0.0108 1.0000
7.750 1.2491 0.01536 0.00898 -0.0692 0.0098 1.0000
8.000 1.2673 0.01652 0.01030 -0.0676 0.0089 1.0000
8.250 1.2901 0.01702 0.01086 -0.0670 0.0086 1.0000
8.500 1.3116 0.01766 0.01156 -0.0661 0.0082 1.0000
8.750 1.3320 0.01838 0.01236 -0.0650 0.0078 1.0000
9.000 1.3516 0.01915 0.01320 -0.0639 0.0075 1.0000
9.250 1.3704 0.01994 0.01407 -0.0627 0.0071 1.0000
9.500 1.3883 0.02079 0.01499 -0.0613 0.0068 1.0000
9.750 1.4037 0.02181 0.01610 -0.0597 0.0065 1.0000
10.000 1.4095 0.02365 0.01806 -0.0566 0.0062 1.0000
10.250 1.4143 0.02547 0.02003 -0.0534 0.0059 1.0000
10.500 1.4308 0.02612 0.02076 -0.0519 0.0057 1.0000
10.750 1.4405 0.02711 0.02184 -0.0494 0.0056 1.0000
11.000 1.4458 0.02833 0.02317 -0.0463 0.0054 1.0000
11.250 1.4491 0.02976 0.02471 -0.0432 0.0053 1.0000
11.500 1.4512 0.03134 0.02641 -0.0403 0.0052 1.0000
11.750 1.4524 0.03309 0.02829 -0.0377 0.0051 1.0000
12.000 1.4524 0.03505 0.03037 -0.0353 0.0050 1.0000
12.250 1.4511 0.03728 0.03273 -0.0333 0.0049 1.0000
12.500 1.4488 0.03980 0.03537 -0.0318 0.0048 1.0000
12.750 1.4454 0.04266 0.03837 -0.0309 0.0047 1.0000
13.000 1.4420 0.04580 0.04164 -0.0306 0.0047 1.0000
13.250 1.4364 0.04954 0.04552 -0.0310 0.0046 1.0000
13.500 1.4298 0.05371 0.04983 -0.0320 0.0046 1.0000
13.750 1.4208 0.05852 0.05479 -0.0335 0.0045 1.0000
14.000 1.4124 0.06344 0.05985 -0.0355 0.0045 1.0000
14.250 1.4017 0.06888 0.06542 -0.0378 0.0045 1.0000
14.500 1.3886 0.07484 0.07153 -0.0404 0.0044 1.0000
14.750 1.3762 0.08088 0.07769 -0.0432 0.0044 1.0000
15.000 1.3606 0.08752 0.08447 -0.0461 0.0044 1.0000
15.250 1.3467 0.09405 0.09112 -0.0492 0.0044 1.0000
15.500 1.3299 0.10113 0.09833 -0.0525 0.0044 1.0000
15.750 1.3130 0.10848 0.10581 -0.0560 0.0044 1.0000
16.000 1.2984 0.11558 0.11303 -0.0596 0.0044 1.0000
16.250 1.2786 0.12385 0.12144 -0.0637 0.0044 1.0000
16.500 1.2617 0.13191 0.12963 -0.0679 0.0044 1.0000
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Polar data table (+)
Polar graphs
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