GOE 602 MOD. AIRFOIL (goe602m-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: GOE 602 MOD. AIRFOIL (goe602m-il) Reynolds number: 50,000 Max Cl/Cd: 39.22 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe602m-il-50000.txt Download as CSV file: xf-goe602m-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 602 MOD. AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2822 0.11133 0.10491 -0.0303 1.0000 0.2092
-9.250 -0.2703 0.10700 0.10060 -0.0291 1.0000 0.2165
-9.000 -0.2845 0.10602 0.09972 -0.0289 1.0000 0.2236
-8.750 -0.2723 0.10183 0.09556 -0.0274 1.0000 0.2346
-8.500 -0.2757 0.09916 0.09297 -0.0265 1.0000 0.2420
-8.250 -0.2843 0.09758 0.09149 -0.0253 1.0000 0.2518
-8.000 -0.2745 0.09365 0.08759 -0.0237 1.0000 0.2613
-7.750 -0.3010 0.09362 0.08773 -0.0224 1.0000 0.2673
-7.500 -0.2850 0.08906 0.08316 -0.0206 1.0000 0.2792
-7.250 -0.2872 0.08619 0.08037 -0.0188 1.0000 0.2868
-7.000 -0.3628 0.09288 0.08664 -0.0172 1.0000 0.2868
-6.750 -0.3845 0.09261 0.08654 -0.0141 1.0000 0.2955
-6.500 -0.3776 0.08922 0.08319 -0.0118 1.0000 0.3070
-6.000 -0.4069 0.08634 0.08059 -0.0075 1.0000 0.3269
-5.750 -0.4168 0.08479 0.07912 -0.0059 1.0000 0.3405
-5.500 -0.4178 0.08222 0.07662 -0.0035 1.0000 0.3551
-5.250 -0.4181 0.07951 0.07396 -0.0009 1.0000 0.3705
-5.000 -0.4066 0.07612 0.07059 0.0036 1.0000 0.3911
-4.750 -0.4186 0.07480 0.06937 0.0054 1.0000 0.4135
-4.250 -0.3459 0.04981 0.04314 -0.0448 1.0000 0.1785
-4.000 -0.3070 0.04180 0.03402 -0.0525 1.0000 0.1516
-3.750 -0.2808 0.03806 0.02981 -0.0539 1.0000 0.1466
-3.500 -0.2534 0.03507 0.02623 -0.0550 1.0000 0.1472
-3.250 -0.2264 0.03277 0.02330 -0.0555 1.0000 0.1510
-3.000 -0.1998 0.03080 0.02075 -0.0555 1.0000 0.1527
-2.750 -0.1759 0.02916 0.01892 -0.0551 1.0000 0.1568
-2.500 -0.1521 0.02808 0.01755 -0.0546 1.0000 0.1672
-2.250 -0.1298 0.02709 0.01651 -0.0539 1.0000 0.1794
-2.000 -0.1073 0.02622 0.01559 -0.0530 1.0000 0.1934
-1.750 -0.0826 0.02554 0.01497 -0.0526 1.0000 0.2212
-1.500 -0.0556 0.02442 0.01458 -0.0525 1.0000 0.3490
-1.250 -0.0390 0.02324 0.01464 -0.0494 1.0000 0.6190
-1.000 -0.0287 0.02184 0.01434 -0.0453 1.0000 1.0000
-0.750 -0.0020 0.02238 0.01423 -0.0469 1.0000 1.0000
-0.500 0.0197 0.02297 0.01439 -0.0473 1.0000 1.0000
-0.250 0.0397 0.02362 0.01469 -0.0475 1.0000 1.0000
0.000 0.0588 0.02432 0.01509 -0.0475 1.0000 1.0000
0.250 0.0773 0.02508 0.01560 -0.0475 1.0000 1.0000
0.500 0.1204 0.02638 0.01661 -0.0521 0.9884 1.0000
0.750 0.1707 0.02776 0.01771 -0.0578 0.9728 1.0000
1.000 0.2192 0.02901 0.01874 -0.0629 0.9573 1.0000
1.250 0.2611 0.03002 0.01959 -0.0668 0.9409 1.0000
1.500 0.3003 0.03094 0.02039 -0.0700 0.9243 1.0000
1.750 0.3394 0.03184 0.02119 -0.0730 0.9079 1.0000
2.000 0.3779 0.03267 0.02196 -0.0757 0.8918 1.0000
2.250 0.4166 0.03346 0.02270 -0.0784 0.8757 1.0000
2.500 0.4552 0.03417 0.02339 -0.0808 0.8600 1.0000
2.750 0.4940 0.03480 0.02403 -0.0830 0.8445 1.0000
3.000 0.5331 0.03535 0.02461 -0.0852 0.8292 1.0000
3.250 0.5636 0.03598 0.02527 -0.0860 0.8129 1.0000
3.500 0.5922 0.03661 0.02595 -0.0864 0.7960 1.0000
3.750 0.6242 0.03713 0.02657 -0.0872 0.7798 1.0000
4.000 0.6579 0.03756 0.02708 -0.0880 0.7641 1.0000
4.250 0.6931 0.03785 0.02749 -0.0888 0.7486 1.0000
4.500 0.7295 0.03802 0.02779 -0.0895 0.7333 1.0000
4.750 0.7667 0.03806 0.02802 -0.0902 0.7183 1.0000
5.000 0.8062 0.03792 0.02806 -0.0909 0.7034 1.0000
5.250 0.8452 0.03772 0.02806 -0.0914 0.6884 1.0000
5.500 0.8851 0.03734 0.02793 -0.0917 0.6732 1.0000
5.750 0.9274 0.03676 0.02758 -0.0920 0.6577 1.0000
6.000 0.9510 0.03725 0.02826 -0.0906 0.6392 1.0000
6.250 0.9868 0.03668 0.02795 -0.0897 0.6188 1.0000
6.500 1.0347 0.03480 0.02630 -0.0890 0.5943 1.0000
6.750 1.0786 0.03326 0.02493 -0.0881 0.5681 1.0000
7.000 1.1098 0.03233 0.02415 -0.0860 0.5379 1.0000
7.250 1.1408 0.03046 0.02218 -0.0829 0.4977 1.0000
7.500 1.1553 0.03023 0.02202 -0.0793 0.4634 1.0000
7.750 1.1702 0.03003 0.02184 -0.0758 0.4296 1.0000
8.000 1.1782 0.03004 0.02188 -0.0716 0.3937 1.0000
8.250 1.1797 0.03030 0.02217 -0.0667 0.3534 1.0000
8.500 1.1702 0.03105 0.02279 -0.0607 0.3001 1.0000
8.750 1.1558 0.03264 0.02398 -0.0546 0.2351 1.0000
9.000 1.1377 0.03551 0.02615 -0.0491 0.1725 1.0000
9.250 1.1280 0.03872 0.02884 -0.0451 0.1354 1.0000
9.500 1.1294 0.04155 0.03135 -0.0423 0.1171 1.0000
9.750 1.1469 0.04405 0.03378 -0.0405 0.1024 1.0000
10.000 1.1771 0.04661 0.03625 -0.0400 0.0902 1.0000
10.250 1.2156 0.04954 0.03944 -0.0405 0.0826 1.0000
10.500 1.2696 0.05461 0.04469 -0.0435 0.0783 1.0000
10.750 1.2816 0.05830 0.04888 -0.0417 0.0774 1.0000
11.000 1.2842 0.06193 0.05297 -0.0392 0.0767 1.0000
11.250 1.2782 0.06542 0.05686 -0.0362 0.0761 1.0000
11.500 1.2681 0.06901 0.06080 -0.0333 0.0759 1.0000
11.750 1.2538 0.07281 0.06491 -0.0307 0.0759 1.0000
12.000 1.2366 0.07692 0.06931 -0.0287 0.0761 1.0000
12.250 1.2166 0.08136 0.07401 -0.0276 0.0764 1.0000
12.500 1.1967 0.08635 0.07923 -0.0274 0.0770 1.0000
12.750 1.1752 0.09184 0.08491 -0.0281 0.0775 1.0000
13.000 1.1546 0.09787 0.09110 -0.0297 0.0781 1.0000
13.250 1.1359 0.10436 0.09771 -0.0319 0.0786 1.0000
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Polar data table (+)
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