GOE 770 AIRFOIL (goe770-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 770 AIRFOIL (goe770-il) Reynolds number: 100,000 Max Cl/Cd: 19.17 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe770-il-100000.txt Download as CSV file: xf-goe770-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 770 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-12.750 -0.5988 0.07697 0.07169 -0.0681 1.0000 0.1048
-12.500 -0.6100 0.07166 0.06635 -0.0700 1.0000 0.1042
-12.250 -0.6342 0.06633 0.06097 -0.0718 1.0000 0.1033
-12.000 -0.6646 0.06210 0.05669 -0.0722 1.0000 0.1025
-11.750 -0.6838 0.05734 0.05164 -0.0753 0.9663 0.1018
-11.500 -0.6868 0.05256 0.04639 -0.0774 0.9333 0.1016
-11.250 -0.6870 0.04922 0.04259 -0.0769 0.9058 0.1019
-11.000 -0.6877 0.04670 0.03962 -0.0748 0.8832 0.1028
-10.750 -0.6871 0.04460 0.03704 -0.0723 0.8651 0.1038
-10.500 -0.6842 0.04285 0.03475 -0.0695 0.8503 0.1049
-10.250 -0.6657 0.04053 0.03235 -0.0689 0.8360 0.1066
-10.000 -0.6444 0.03895 0.03069 -0.0682 0.8241 0.1084
-9.750 -0.6256 0.03753 0.02908 -0.0671 0.8132 0.1106
-9.500 -0.6084 0.03626 0.02751 -0.0659 0.8037 0.1133
-9.250 -0.5931 0.03522 0.02605 -0.0642 0.7942 0.1158
-9.000 -0.5661 0.03350 0.02439 -0.0642 0.7864 0.1191
-8.750 -0.5417 0.03242 0.02326 -0.0639 0.7771 0.1226
-8.500 -0.5201 0.03152 0.02210 -0.0628 0.7697 0.1268
-8.250 -0.4927 0.03026 0.02094 -0.0629 0.7630 0.1316
-8.000 -0.4679 0.02943 0.02008 -0.0626 0.7554 0.1371
-7.750 -0.4428 0.02844 0.01907 -0.0621 0.7490 0.1432
-7.500 -0.4187 0.02770 0.01837 -0.0615 0.7431 0.1507
-7.250 -0.3951 0.02691 0.01771 -0.0611 0.7359 0.1589
-7.000 -0.3729 0.02629 0.01710 -0.0602 0.7300 0.1694
-6.750 -0.3522 0.02565 0.01654 -0.0590 0.7250 0.1821
-6.500 -0.3329 0.02515 0.01622 -0.0579 0.7191 0.1989
-6.250 -0.3156 0.02463 0.01600 -0.0566 0.7127 0.2225
-6.000 -0.2992 0.02404 0.01563 -0.0548 0.7074 0.2690
-5.750 -0.2876 0.02317 0.01517 -0.0522 0.7032 0.3388
-5.500 -0.2737 0.02300 0.01548 -0.0499 0.6975 0.4056
-5.250 -0.2545 0.02332 0.01596 -0.0483 0.6912 0.4563
-5.000 -0.2323 0.02365 0.01627 -0.0467 0.6859 0.4920
-4.750 -0.2092 0.02396 0.01643 -0.0453 0.6816 0.5222
-4.500 -0.1877 0.02449 0.01700 -0.0441 0.6754 0.5455
-4.250 -0.1650 0.02490 0.01742 -0.0429 0.6690 0.5674
-4.000 -0.1405 0.02520 0.01770 -0.0415 0.6639 0.5894
-3.750 -0.1150 0.02549 0.01792 -0.0401 0.6596 0.6110
-3.500 -0.0953 0.02610 0.01859 -0.0388 0.6528 0.6306
-3.250 -0.0713 0.02653 0.01909 -0.0375 0.6465 0.6476
-3.000 -0.0453 0.02671 0.01924 -0.0361 0.6417 0.6642
-2.750 -0.0191 0.02690 0.01932 -0.0348 0.6378 0.6814
-2.500 -0.0034 0.02759 0.02008 -0.0333 0.6302 0.6983
-2.250 0.0204 0.02798 0.02052 -0.0318 0.6241 0.7128
-2.000 0.0468 0.02803 0.02049 -0.0306 0.6197 0.7266
-1.750 0.0730 0.02807 0.02037 -0.0298 0.6161 0.7400
-1.500 0.0867 0.02895 0.02141 -0.0284 0.6073 0.7487
-1.250 0.1100 0.02908 0.02148 -0.0276 0.6016 0.7600
-1.000 0.1390 0.02893 0.02123 -0.0270 0.5976 0.7696
-0.750 0.1624 0.02923 0.02148 -0.0261 0.5928 0.7798
-0.500 0.1732 0.03015 0.02250 -0.0247 0.5839 0.7894
-0.250 0.1998 0.03020 0.02250 -0.0241 0.5792 0.7986
0.000 0.2295 0.02998 0.02215 -0.0237 0.5758 0.8102
0.250 0.2395 0.03115 0.02344 -0.0218 0.5675 0.8208
0.500 0.2572 0.03162 0.02392 -0.0207 0.5607 0.8329
0.750 0.2884 0.03142 0.02365 -0.0203 0.5571 0.8440
1.000 0.3218 0.03117 0.02328 -0.0204 0.5543 0.8552
1.250 0.3113 0.03360 0.02596 -0.0175 0.5429 0.8701
1.500 0.3431 0.03368 0.02600 -0.0177 0.5386 0.8818
1.750 0.3826 0.03326 0.02548 -0.0185 0.5359 0.8959
2.000 0.4288 0.03291 0.02501 -0.0204 0.5335 0.9089
2.250 0.4177 0.03642 0.02881 -0.0193 0.5201 0.9292
2.500 0.4756 0.03606 0.02835 -0.0236 0.5174 0.9383
2.750 0.5316 0.03552 0.02768 -0.0276 0.5153 0.9492
3.000 0.5313 0.04099 0.03344 -0.0316 0.5017 0.9688
3.250 0.5951 0.04037 0.03273 -0.0370 0.4991 0.9782
3.500 0.6656 0.03926 0.03150 -0.0430 0.4972 0.9846
3.750 0.7330 0.03824 0.03035 -0.0489 0.4955 0.9927
4.000 0.4995 0.05130 0.04360 -0.0287 0.4774 1.0000
4.250 0.5433 0.05015 0.04236 -0.0290 0.4766 1.0000
4.500 0.5936 0.04864 0.04076 -0.0297 0.4761 1.0000
6.750 0.3499 0.09908 0.09143 -0.0290 0.4876 1.0000
7.000 0.3653 0.10079 0.09312 -0.0291 0.4819 1.0000
7.250 0.3942 0.10283 0.09513 -0.0297 0.4786 1.0000
7.500 0.4340 0.10570 0.09798 -0.0309 0.4766 1.0000
7.750 0.3948 0.10713 0.09943 -0.0292 0.4673 1.0000
8.000 0.4164 0.10892 0.10121 -0.0295 0.4620 1.0000
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Polar data table (+)
Polar graphs
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