GEMINI (smoothed) (geminism-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GEMINI (smoothed) (geminism-il) Reynolds number: 50,000 Max Cl/Cd: 8.88 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-geminism-il-50000.txt Download as CSV file: xf-geminism-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GEMINI (smoothed)
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3722 0.10996 0.10277 -0.0246 1.0000 0.3372
-9.500 -0.5331 0.08085 0.07410 -0.0526 1.0000 0.1606
-9.250 -0.5480 0.07670 0.07002 -0.0514 1.0000 0.1578
-9.000 -0.5923 0.07206 0.06545 -0.0485 1.0000 0.1525
-8.750 -0.6641 0.06728 0.06045 -0.0430 1.0000 0.1460
-8.500 -0.6760 0.06401 0.05712 -0.0397 1.0000 0.1446
-8.250 -0.6913 0.06082 0.05380 -0.0359 1.0000 0.1433
-8.000 -0.7060 0.05767 0.05045 -0.0320 1.0000 0.1425
-7.750 -0.7173 0.05462 0.04712 -0.0282 1.0000 0.1423
-7.500 -0.7246 0.05170 0.04386 -0.0246 1.0000 0.1430
-7.250 -0.7275 0.04889 0.04065 -0.0213 1.0000 0.1441
-7.000 -0.7261 0.04617 0.03749 -0.0183 1.0000 0.1453
-6.750 -0.7207 0.04359 0.03441 -0.0155 1.0000 0.1465
-6.500 -0.7086 0.04122 0.03187 -0.0137 1.0000 0.1495
-6.250 -0.6941 0.03965 0.03022 -0.0121 1.0000 0.1553
-6.000 -0.6806 0.03785 0.02793 -0.0102 1.0000 0.1609
-5.750 -0.6623 0.03612 0.02615 -0.0090 1.0000 0.1669
-5.500 -0.6449 0.03479 0.02453 -0.0075 1.0000 0.1761
-5.250 -0.6265 0.03357 0.02336 -0.0064 1.0000 0.1876
-5.000 -0.6071 0.03234 0.02210 -0.0052 1.0000 0.2013
-4.750 -0.5887 0.03127 0.02101 -0.0039 1.0000 0.2223
-4.500 -0.5704 0.03012 0.02007 -0.0026 1.0000 0.2529
-4.250 -0.5538 0.02872 0.01920 -0.0010 1.0000 0.3113
-4.000 -0.5418 0.02730 0.01872 0.0019 1.0000 0.4300
-3.750 -0.5329 0.02697 0.01894 0.0058 1.0000 0.5298
-3.500 -0.5225 0.02707 0.01936 0.0098 1.0000 0.6043
-3.250 -0.5114 0.02730 0.01978 0.0138 1.0000 0.6691
-3.000 -0.5004 0.02763 0.02025 0.0182 1.0000 0.7298
-2.750 -0.4900 0.02816 0.02090 0.0233 1.0000 0.7928
-2.500 -0.4689 0.02912 0.02189 0.0273 1.0000 0.8596
-2.250 -0.3578 0.03194 0.02421 0.0140 0.9939 0.9264
-2.000 -0.1910 0.03446 0.02601 -0.0126 0.9847 0.9677
-1.750 -0.0518 0.03535 0.02639 -0.0361 0.9766 1.0000
-1.500 -0.0206 0.03514 0.02600 -0.0405 0.9620 1.0000
-1.250 0.0077 0.03504 0.02575 -0.0439 0.9479 1.0000
-1.000 0.0326 0.03503 0.02559 -0.0463 0.9340 1.0000
-0.750 0.0536 0.03512 0.02554 -0.0478 0.9202 1.0000
-0.500 0.0728 0.03527 0.02557 -0.0485 0.9066 1.0000
-0.250 0.0927 0.03552 0.02569 -0.0491 0.8936 1.0000
0.000 0.1216 0.03584 0.02588 -0.0509 0.8813 1.0000
0.250 0.1380 0.03622 0.02614 -0.0504 0.8682 1.0000
0.500 0.1481 0.03671 0.02653 -0.0488 0.8549 1.0000
0.750 0.1634 0.03729 0.02699 -0.0479 0.8422 1.0000
1.000 0.1885 0.03790 0.02749 -0.0484 0.8306 1.0000
1.250 0.2225 0.03844 0.02794 -0.0502 0.8194 1.0000
1.500 0.2275 0.03928 0.02869 -0.0476 0.8065 1.0000
1.750 0.2419 0.04012 0.02944 -0.0463 0.7946 1.0000
2.000 0.2750 0.04076 0.03002 -0.0477 0.7841 1.0000
2.250 0.2909 0.04164 0.03084 -0.0466 0.7726 1.0000
2.500 0.2983 0.04273 0.03187 -0.0445 0.7607 1.0000
2.750 0.3229 0.04359 0.03269 -0.0446 0.7504 1.0000
3.000 0.3477 0.04442 0.03349 -0.0447 0.7399 1.0000
3.250 0.3505 0.04579 0.03482 -0.0422 0.7284 1.0000
3.500 0.3743 0.04677 0.03578 -0.0422 0.7186 1.0000
3.750 0.3954 0.04777 0.03678 -0.0419 0.7082 1.0000
4.000 0.3972 0.04941 0.03839 -0.0396 0.6974 1.0000
4.250 0.4295 0.05021 0.03922 -0.0405 0.6883 1.0000
4.500 0.4343 0.05183 0.04083 -0.0386 0.6775 1.0000
4.750 0.4411 0.05354 0.04254 -0.0371 0.6677 1.0000
5.000 0.4802 0.05410 0.04316 -0.0384 0.6586 1.0000
5.250 0.4679 0.05659 0.04562 -0.0355 0.6481 1.0000
5.500 0.4891 0.05792 0.04700 -0.0354 0.6390 1.0000
5.750 0.5009 0.05960 0.04871 -0.0345 0.6292 1.0000
6.000 0.5034 0.06179 0.05092 -0.0332 0.6201 1.0000
6.250 0.5405 0.06250 0.05173 -0.0340 0.6108 1.0000
6.500 0.5228 0.06569 0.05491 -0.0317 0.6018 1.0000
6.750 0.5523 0.06684 0.05614 -0.0320 0.5927 1.0000
7.000 0.5424 0.06984 0.05916 -0.0305 0.5845 1.0000
7.250 0.5617 0.07157 0.06096 -0.0304 0.5756 1.0000
7.500 0.5587 0.07443 0.06386 -0.0295 0.5682 1.0000
7.750 0.5751 0.07641 0.06592 -0.0293 0.5595 1.0000
8.000 0.5684 0.07969 0.06925 -0.0286 0.5541 1.0000
8.250 0.5925 0.08141 0.07106 -0.0287 0.5448 1.0000
8.500 0.5802 0.08519 0.07487 -0.0282 0.5417 1.0000
8.750 0.5763 0.08884 0.07858 -0.0283 0.5411 1.0000
9.000 0.5756 0.09260 0.08240 -0.0287 0.5428 1.0000
9.250 0.5910 0.09650 0.08642 -0.0302 0.5471 1.0000
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Polar data table (+)
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