FX 77-W-270 (fx77w270-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 77-W-270 (fx77w270-il) Reynolds number: 100,000 Max Cl/Cd: 1.26 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx77w270-il-100000.txt Download as CSV file: xf-fx77w270-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: FX 77-W-270
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.000 -0.4301 0.17566 0.16987 0.0034 0.6156 0.1389
-14.750 -0.7642 0.09227 0.08576 -0.0424 0.6517 0.0720
-14.500 -0.7870 0.08669 0.07995 -0.0436 0.6489 0.0716
-14.250 -0.8111 0.08142 0.07440 -0.0443 0.6463 0.0712
-14.000 -0.8344 0.07656 0.06924 -0.0444 0.6437 0.0709
-13.750 -0.8545 0.07214 0.06456 -0.0440 0.6405 0.0707
-13.500 -0.8710 0.06823 0.06037 -0.0432 0.6370 0.0706
-13.250 -0.8837 0.06480 0.05664 -0.0420 0.6334 0.0705
-13.000 -0.8936 0.06189 0.05343 -0.0403 0.6300 0.0706
-12.750 -0.9007 0.05954 0.05078 -0.0381 0.6269 0.0707
-12.500 -0.8993 0.05730 0.04819 -0.0366 0.6237 0.0710
-12.250 -0.8923 0.05511 0.04573 -0.0355 0.6203 0.0714
-12.000 -0.8822 0.05307 0.04339 -0.0346 0.6166 0.0719
-11.750 -0.8636 0.05129 0.04143 -0.0343 0.6128 0.0725
-11.500 -0.8358 0.04999 0.04013 -0.0347 0.6088 0.0735
-11.250 -0.8115 0.04882 0.03889 -0.0347 0.6056 0.0747
-11.000 -0.7900 0.04765 0.03753 -0.0344 0.6028 0.0761
-10.750 -0.7692 0.04634 0.03601 -0.0343 0.6001 0.0776
-10.500 -0.7402 0.04545 0.03527 -0.0349 0.5971 0.0796
-10.250 -0.7158 0.04462 0.03442 -0.0351 0.5943 0.0819
-10.000 -0.6916 0.04369 0.03340 -0.0351 0.5916 0.0844
-9.750 -0.6655 0.04303 0.03281 -0.0353 0.5892 0.0873
-9.500 -0.6417 0.04225 0.03187 -0.0352 0.5870 0.0905
-9.250 -0.6144 0.04161 0.03133 -0.0353 0.5847 0.0940
-9.000 -0.5895 0.04100 0.03064 -0.0351 0.5825 0.0983
-8.750 -0.5636 0.04041 0.03009 -0.0352 0.5802 0.1036
-8.500 -0.5362 0.03979 0.02971 -0.0354 0.5778 0.1093
-8.250 -0.5115 0.03925 0.02936 -0.0353 0.5758 0.1157
-8.000 -0.4890 0.03877 0.02901 -0.0351 0.5740 0.1229
-7.750 -0.4676 0.03831 0.02868 -0.0349 0.5724 0.1318
-7.500 -0.4476 0.03779 0.02830 -0.0346 0.5708 0.1444
-7.250 -0.4296 0.03711 0.02785 -0.0341 0.5694 0.1616
-7.000 -0.4127 0.03628 0.02737 -0.0339 0.5681 0.1929
-6.750 -0.3990 0.03482 0.02658 -0.0341 0.5667 0.2635
-6.500 -0.3850 0.03355 0.02654 -0.0337 0.5650 0.4205
-6.250 -0.3613 0.03646 0.03002 -0.0278 0.5629 0.5101
-6.000 -0.3311 0.03838 0.03185 -0.0271 0.5607 0.5506
-5.750 -0.2990 0.03959 0.03299 -0.0293 0.5584 0.5819
-5.500 -0.2684 0.04163 0.03499 -0.0295 0.5560 0.6011
-5.250 -0.2392 0.04355 0.03685 -0.0298 0.5540 0.6197
-5.000 -0.2115 0.04623 0.03956 -0.0273 0.5524 0.6264
-4.750 -0.1852 0.04794 0.04122 -0.0273 0.5509 0.6418
-4.500 -0.1582 0.05034 0.04364 -0.0252 0.5495 0.6496
-4.250 -0.1346 0.05175 0.04501 -0.0252 0.5482 0.6630
-4.000 -0.1090 0.05376 0.04701 -0.0236 0.5470 0.6708
-3.750 -0.0887 0.05518 0.04840 -0.0235 0.5461 0.6844
-3.500 -0.0638 0.05694 0.05013 -0.0215 0.5446 0.6947
-3.250 -0.0404 0.05776 0.05083 -0.0194 0.5429 0.7078
-3.000 -0.2835 0.07674 0.07104 -0.0267 0.6328 0.6896
-2.750 -0.2576 0.07808 0.07225 -0.0266 0.6284 0.7040
-2.500 -0.2346 0.07998 0.07411 -0.0225 0.6258 0.7130
-2.250 -0.2463 0.08088 0.07493 -0.0214 0.6131 0.7246
-2.000 -0.2375 0.08205 0.07609 -0.0155 0.6084 0.7326
-1.750 -0.2082 0.08346 0.07737 -0.0159 0.6057 0.7477
-1.500 -0.1849 0.08505 0.07891 -0.0121 0.6040 0.7575
-1.250 -0.2114 0.08543 0.07928 -0.0089 0.5898 0.7644
-1.000 -0.1934 0.08627 0.08005 -0.0058 0.5862 0.7757
-0.750 -0.1627 0.08782 0.08149 -0.0061 0.5840 0.7916
-0.500 -0.1889 0.08849 0.08219 -0.0005 0.5752 0.7968
-0.250 -0.1779 0.08927 0.08292 0.0015 0.5688 0.8086
0.000 -0.1591 0.08991 0.08348 0.0035 0.5656 0.8188
0.250 -0.1304 0.09116 0.08464 0.0037 0.5635 0.8288
0.500 -0.0913 0.09300 0.08636 0.0014 0.5621 0.8361
0.750 -0.0552 0.09504 0.08830 0.0010 0.5613 0.8410
1.000 -0.1119 0.09362 0.08696 0.0065 0.5454 0.8439
1.250 -0.0791 0.09505 0.08829 0.0046 0.5434 0.8470
1.500 -0.0401 0.09703 0.09017 0.0017 0.5420 0.8490
1.750 0.0031 0.09968 0.09270 -0.0017 0.5411 0.8509
2.000 -0.0477 0.09900 0.09211 0.0017 0.5262 0.8523
2.250 -0.0140 0.10074 0.09376 -0.0011 0.5237 0.8544
2.500 0.0230 0.10281 0.09574 -0.0038 0.5221 0.8565
2.750 0.0570 0.10490 0.09776 -0.0049 0.5211 0.8590
3.000 0.0963 0.10789 0.10068 -0.0070 0.5204 0.8612
3.250 0.0348 0.10634 0.09923 -0.0032 0.5051 0.8618
3.500 0.0664 0.10812 0.10095 -0.0050 0.5028 0.8635
3.750 0.1025 0.11045 0.10321 -0.0072 0.5014 0.8655
4.000 0.1425 0.11344 0.10614 -0.0100 0.5004 0.8668
4.250 0.0901 0.11333 0.10613 -0.0077 0.4886 0.8670
4.500 0.1145 0.11508 0.10783 -0.0096 0.4853 0.8678
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Polar data table (+)
Polar graphs
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