I.S.A. 571 (isa571-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: I.S.A. 571 (isa571-il) Reynolds number: 500,000 Max Cl/Cd: 93.61 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-isa571-il-500000.txt Download as CSV file: xf-isa571-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4119 0.09075 0.08856 -0.0195 1.0000 0.0192
-8.250 -0.4242 0.08858 0.08645 -0.0190 1.0000 0.0194
-8.000 -0.4257 0.08539 0.08330 -0.0208 1.0000 0.0195
-7.750 -0.4246 0.08198 0.07990 -0.0226 1.0000 0.0196
-7.500 -0.4217 0.07828 0.07622 -0.0247 1.0000 0.0196
-7.250 -0.4167 0.07436 0.07228 -0.0268 1.0000 0.0197
-7.000 -0.4214 0.06875 0.06668 -0.0278 1.0000 0.0202
-6.750 -0.4147 0.06649 0.06441 -0.0271 1.0000 0.0206
-6.500 -0.4059 0.06439 0.06231 -0.0267 1.0000 0.0213
-6.250 -0.3942 0.06147 0.05936 -0.0279 1.0000 0.0223
-6.000 -0.3547 0.05571 0.05347 -0.0364 0.9974 0.0242
-5.750 -0.3006 0.04873 0.04617 -0.0465 0.9949 0.0261
-5.500 -0.2713 0.03479 0.03175 -0.0544 0.9922 0.0206
-5.250 -0.2323 0.03596 0.03289 -0.0561 0.9893 0.0260
-5.000 -0.2013 0.01525 0.01003 -0.0607 0.9897 0.0205
-4.750 -0.1626 0.01488 0.00963 -0.0631 0.9870 0.0222
-4.500 -0.1226 0.01397 0.00852 -0.0655 0.9849 0.0246
-4.250 -0.0830 0.01279 0.00711 -0.0679 0.9835 0.0276
-4.000 -0.0507 0.01290 0.00727 -0.0688 0.9785 0.0308
-3.750 -0.0136 0.01286 0.00714 -0.0705 0.9752 0.0346
-3.500 0.0237 0.01182 0.00605 -0.0726 0.9731 0.0399
-3.250 0.0633 0.01171 0.00590 -0.0750 0.9712 0.0449
-3.000 0.0941 0.01075 0.00488 -0.0756 0.9663 0.0489
-2.750 0.1300 0.01031 0.00444 -0.0773 0.9622 0.0533
-2.500 0.1688 0.00987 0.00398 -0.0795 0.9590 0.0566
-2.250 0.2012 0.00947 0.00355 -0.0802 0.9515 0.0581
-2.000 0.2359 0.00879 0.00285 -0.0814 0.9439 0.0619
-1.750 0.2657 0.00845 0.00250 -0.0816 0.9314 0.0649
-1.500 0.2972 0.00816 0.00219 -0.0820 0.9165 0.0675
-1.250 0.3278 0.00793 0.00191 -0.0823 0.8937 0.0704
-1.000 0.3580 0.00776 0.00169 -0.0824 0.8591 0.0784
-0.750 0.3849 0.00780 0.00156 -0.0817 0.8027 0.0973
-0.500 0.4089 0.00798 0.00148 -0.0806 0.7350 0.1188
-0.250 0.4332 0.00818 0.00146 -0.0797 0.6813 0.1380
0.000 0.4580 0.00822 0.00150 -0.0792 0.6366 0.2127
0.250 0.4701 0.00655 0.00169 -0.0760 0.5982 0.9308
0.500 0.5033 0.00678 0.00168 -0.0771 0.5479 1.0000
0.750 0.5283 0.00709 0.00173 -0.0765 0.4992 1.0000
1.000 0.5538 0.00738 0.00179 -0.0761 0.4600 1.0000
1.250 0.5798 0.00764 0.00188 -0.0757 0.4323 1.0000
1.500 0.6061 0.00789 0.00197 -0.0754 0.4112 1.0000
1.750 0.6327 0.00809 0.00208 -0.0752 0.3949 1.0000
2.250 0.6865 0.00845 0.00230 -0.0749 0.3721 1.0000
2.500 0.7134 0.00861 0.00242 -0.0747 0.3628 1.0000
3.000 0.7673 0.00895 0.00270 -0.0744 0.3450 1.0000
3.250 0.7941 0.00913 0.00284 -0.0743 0.3363 1.0000
3.500 0.8209 0.00930 0.00299 -0.0741 0.3276 1.0000
3.750 0.8478 0.00946 0.00317 -0.0740 0.3194 1.0000
4.000 0.8744 0.00967 0.00334 -0.0738 0.3105 1.0000
4.250 0.9013 0.00981 0.00351 -0.0737 0.3013 1.0000
4.500 0.9279 0.01000 0.00368 -0.0735 0.2884 1.0000
4.750 0.9541 0.01022 0.00387 -0.0733 0.2696 1.0000
5.000 0.9801 0.01047 0.00406 -0.0731 0.2470 1.0000
5.250 1.0052 0.01083 0.00429 -0.0728 0.2166 1.0000
5.500 1.0296 0.01128 0.00460 -0.0724 0.1900 1.0000
5.750 1.0538 0.01176 0.00499 -0.0719 0.1703 1.0000
6.000 1.0784 0.01217 0.00536 -0.0715 0.1539 1.0000
6.250 1.1026 0.01265 0.00575 -0.0711 0.1296 1.0000
6.500 1.1231 0.01362 0.00637 -0.0702 0.0793 1.0000
6.750 1.1409 0.01499 0.00742 -0.0687 0.0251 1.0000
7.000 1.1628 0.01578 0.00829 -0.0678 0.0201 1.0000
7.250 1.1850 0.01650 0.00913 -0.0669 0.0181 1.0000
7.500 1.2069 0.01721 0.00995 -0.0659 0.0168 1.0000
7.750 1.2276 0.01804 0.01087 -0.0649 0.0156 1.0000
8.000 1.2465 0.01902 0.01196 -0.0635 0.0147 1.0000
8.250 1.2602 0.02052 0.01360 -0.0614 0.0136 1.0000
8.500 1.2737 0.02195 0.01516 -0.0593 0.0128 1.0000
8.750 1.2915 0.02285 0.01618 -0.0579 0.0123 1.0000
9.000 1.3066 0.02401 0.01744 -0.0560 0.0119 1.0000
9.250 1.3201 0.02528 0.01882 -0.0540 0.0115 1.0000
9.500 1.3324 0.02663 0.02028 -0.0519 0.0111 1.0000
9.750 1.3435 0.02805 0.02180 -0.0496 0.0108 1.0000
10.000 1.3528 0.02955 0.02342 -0.0472 0.0105 1.0000
10.250 1.3590 0.03109 0.02507 -0.0443 0.0103 1.0000
10.500 1.3641 0.03279 0.02689 -0.0414 0.0100 1.0000
10.750 1.3682 0.03467 0.02888 -0.0387 0.0098 1.0000
11.000 1.3712 0.03677 0.03109 -0.0361 0.0096 1.0000
11.250 1.3727 0.03941 0.03384 -0.0336 0.0094 1.0000
11.500 1.3712 0.04314 0.03775 -0.0312 0.0091 1.0000
12.000 1.3549 0.04947 0.04454 -0.0267 0.0088 1.0000
12.250 1.3476 0.05252 0.04779 -0.0254 0.0088 1.0000
12.500 1.3383 0.05625 0.05171 -0.0248 0.0088 1.0000
12.750 1.3274 0.06046 0.05612 -0.0250 0.0088 1.0000
13.000 1.3155 0.06504 0.06089 -0.0261 0.0088 1.0000
13.250 1.3011 0.07051 0.06655 -0.0277 0.0088 1.0000
13.500 1.2842 0.07668 0.07290 -0.0298 0.0089 1.0000
13.750 1.2773 0.08157 0.07790 -0.0307 0.0091 1.0000
14.000 1.2629 0.08756 0.08405 -0.0339 0.0091 1.0000
14.250 1.2497 0.09365 0.09029 -0.0375 0.0091 1.0000
14.500 1.2371 0.10003 0.09681 -0.0415 0.0091 1.0000
14.750 1.2226 0.10704 0.10396 -0.0459 0.0092 1.0000
15.000 1.2100 0.11404 0.11110 -0.0504 0.0092 1.0000
15.250 1.1954 0.12179 0.11898 -0.0554 0.0093 1.0000
15.500 1.1817 0.12987 0.12721 -0.0608 0.0094 1.0000
15.750 0.9280 0.12960 0.12730 -0.0438 0.0106 1.0000
16.000 0.8881 0.14008 0.13796 -0.0498 0.0113 1.0000
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Polar data table (+)
Polar graphs
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