GOE 477 AIRFOIL (goe477-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
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Airfoil: GOE 477 AIRFOIL (goe477-il) Reynolds number: 1,000,000 Max Cl/Cd: 121.69 at α=1.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe477-il-1000000.txt Download as CSV file: xf-goe477-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 477 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.2306 0.10760 0.10560 -0.0726 0.9093 0.0156
-11.500 -0.6604 0.02915 0.02619 -0.1109 0.8481 0.0115
-11.250 -0.6523 0.02631 0.02310 -0.1106 0.8451 0.0117
-11.000 -0.6394 0.02425 0.02081 -0.1100 0.8423 0.0119
-10.750 -0.6219 0.02284 0.01921 -0.1095 0.8396 0.0122
-10.500 -0.6023 0.02171 0.01789 -0.1090 0.8371 0.0124
-10.250 -0.5912 0.01922 0.01505 -0.1078 0.8345 0.0128
-10.000 -0.5710 0.01808 0.01379 -0.1072 0.8329 0.0133
-9.750 -0.5484 0.01728 0.01289 -0.1067 0.8312 0.0136
-9.500 -0.5248 0.01661 0.01212 -0.1063 0.8293 0.0141
-9.250 -0.5009 0.01593 0.01132 -0.1059 0.8275 0.0145
-9.000 -0.4766 0.01530 0.01057 -0.1054 0.8257 0.0150
-8.750 -0.4517 0.01477 0.00991 -0.1051 0.8239 0.0154
-8.500 -0.4282 0.01396 0.00895 -0.1045 0.8219 0.0160
-8.250 -0.4043 0.01325 0.00813 -0.1040 0.8196 0.0168
-8.000 -0.3784 0.01284 0.00767 -0.1037 0.8180 0.0176
-7.750 -0.3521 0.01249 0.00726 -0.1035 0.8164 0.0184
-7.500 -0.3255 0.01217 0.00687 -0.1032 0.8147 0.0192
-7.250 -0.3004 0.01155 0.00616 -0.1028 0.8129 0.0204
-7.000 -0.2740 0.01118 0.00576 -0.1025 0.8112 0.0216
-6.750 -0.2470 0.01093 0.00545 -0.1023 0.8096 0.0229
-6.500 -0.2199 0.01070 0.00516 -0.1021 0.8081 0.0239
-6.250 -0.1936 0.01031 0.00475 -0.1018 0.8064 0.0263
-6.000 -0.1660 0.01021 0.00461 -0.1017 0.8045 0.0282
-5.750 -0.1389 0.00995 0.00433 -0.1015 0.8030 0.0304
-5.500 -0.1112 0.00982 0.00423 -0.1014 0.8010 0.0330
-5.250 -0.0834 0.00974 0.00414 -0.1013 0.7984 0.0351
-5.000 -0.0562 0.00953 0.00391 -0.1011 0.7956 0.0378
-4.750 -0.0280 0.00952 0.00391 -0.1010 0.7931 0.0402
-4.500 0.0002 0.00952 0.00389 -0.1009 0.7907 0.0423
-4.250 0.0287 0.00960 0.00394 -0.1010 0.7885 0.0434
-4.000 0.0549 0.00917 0.00351 -0.1006 0.7862 0.0468
-3.750 0.0826 0.00906 0.00341 -0.1005 0.7829 0.0488
-3.500 0.1103 0.00895 0.00327 -0.1003 0.7789 0.0509
-3.250 0.1382 0.00891 0.00318 -0.1001 0.7750 0.0524
-3.000 0.1657 0.00880 0.00306 -0.0999 0.7710 0.0534
-2.750 0.1916 0.00835 0.00259 -0.0995 0.7665 0.0567
-2.500 0.2189 0.00817 0.00241 -0.0993 0.7624 0.0588
-2.250 0.2466 0.00807 0.00227 -0.0991 0.7589 0.0608
-2.000 0.2741 0.00793 0.00214 -0.0989 0.7554 0.0626
-1.750 0.3017 0.00781 0.00202 -0.0988 0.7515 0.0640
-1.500 0.3294 0.00770 0.00189 -0.0986 0.7475 0.0648
-1.250 0.3565 0.00752 0.00166 -0.0983 0.7429 0.0680
-1.000 0.3838 0.00736 0.00154 -0.0981 0.7370 0.0720
-0.750 0.4112 0.00725 0.00143 -0.0979 0.7309 0.0755
-0.500 0.4388 0.00716 0.00134 -0.0977 0.7251 0.0797
-0.250 0.4658 0.00700 0.00126 -0.0975 0.7179 0.0994
0.000 0.4921 0.00676 0.00123 -0.0972 0.7099 0.1725
0.250 0.5183 0.00661 0.00119 -0.0968 0.6993 0.2263
0.500 0.5437 0.00640 0.00117 -0.0963 0.6848 0.3110
0.750 0.5665 0.00604 0.00119 -0.0954 0.6639 0.4771
1.000 0.5769 0.00513 0.00130 -0.0917 0.6419 0.8703
1.250 0.6425 0.00528 0.00141 -0.1000 0.6004 0.9845
1.500 0.6883 0.00566 0.00153 -0.1041 0.5462 0.9994
1.750 0.7074 0.00618 0.00172 -0.1025 0.4760 1.0000
2.000 0.7261 0.00658 0.00189 -0.1007 0.4335 1.0000
2.250 0.7473 0.00685 0.00203 -0.0994 0.4092 1.0000
2.500 0.7693 0.00708 0.00215 -0.0982 0.3895 1.0000
2.750 0.7916 0.00730 0.00228 -0.0971 0.3715 1.0000
3.000 0.8141 0.00752 0.00241 -0.0960 0.3545 1.0000
3.250 0.8367 0.00773 0.00253 -0.0950 0.3385 1.0000
3.500 0.8593 0.00794 0.00267 -0.0939 0.3225 1.0000
3.750 0.8818 0.00816 0.00281 -0.0929 0.3069 1.0000
4.000 0.9041 0.00839 0.00296 -0.0918 0.2923 1.0000
4.500 0.9490 0.00884 0.00329 -0.0898 0.2669 1.0000
4.750 0.9713 0.00907 0.00347 -0.0887 0.2551 1.0000
5.000 0.9938 0.00930 0.00365 -0.0877 0.2463 1.0000
5.250 1.0166 0.00951 0.00383 -0.0868 0.2388 1.0000
5.500 1.0392 0.00974 0.00402 -0.0859 0.2311 1.0000
5.750 1.0621 0.00993 0.00421 -0.0850 0.2252 1.0000
6.000 1.0841 0.01019 0.00443 -0.0840 0.2186 1.0000
6.250 1.1075 0.01036 0.00460 -0.0832 0.2129 1.0000
6.500 1.1289 0.01063 0.00483 -0.0821 0.2053 1.0000
6.750 1.1519 0.01081 0.00502 -0.0812 0.1990 1.0000
7.000 1.1727 0.01111 0.00528 -0.0801 0.1900 1.0000
7.250 1.1943 0.01135 0.00549 -0.0790 0.1796 1.0000
7.500 1.2129 0.01175 0.00579 -0.0775 0.1604 1.0000
7.750 1.2047 0.01353 0.00696 -0.0715 0.0618 1.0000
8.000 1.2124 0.01442 0.00770 -0.0681 0.0341 1.0000
8.250 1.2273 0.01495 0.00822 -0.0659 0.0282 1.0000
8.500 1.2440 0.01539 0.00867 -0.0642 0.0256 1.0000
8.750 1.2583 0.01600 0.00929 -0.0621 0.0227 1.0000
9.000 1.2754 0.01643 0.00977 -0.0605 0.0216 1.0000
9.250 1.2920 0.01691 0.01028 -0.0589 0.0205 1.0000
9.500 1.3074 0.01747 0.01087 -0.0571 0.0190 1.0000
9.750 1.3188 0.01832 0.01177 -0.0549 0.0175 1.0000
10.000 1.3349 0.01885 0.01234 -0.0534 0.0169 1.0000
10.250 1.3501 0.01945 0.01298 -0.0519 0.0162 1.0000
10.500 1.3644 0.02013 0.01370 -0.0503 0.0156 1.0000
10.750 1.3781 0.02085 0.01447 -0.0487 0.0149 1.0000
11.000 1.3882 0.02184 0.01550 -0.0468 0.0141 1.0000
11.250 1.3925 0.02326 0.01701 -0.0443 0.0135 1.0000
11.500 1.4081 0.02391 0.01771 -0.0432 0.0131 1.0000
11.750 1.4201 0.02483 0.01868 -0.0418 0.0126 1.0000
12.000 1.4307 0.02587 0.01978 -0.0403 0.0122 1.0000
12.250 1.4397 0.02705 0.02103 -0.0387 0.0119 1.0000
12.500 1.4493 0.02821 0.02223 -0.0373 0.0114 1.0000
12.750 1.4554 0.02965 0.02373 -0.0357 0.0112 1.0000
13.000 1.4575 0.03145 0.02560 -0.0339 0.0108 1.0000
13.250 1.4479 0.03429 0.02857 -0.0315 0.0104 1.0000
13.500 1.4490 0.03632 0.03069 -0.0301 0.0103 1.0000
13.750 1.4558 0.03792 0.03236 -0.0291 0.0101 1.0000
14.000 1.4613 0.03968 0.03421 -0.0281 0.0099 1.0000
14.250 1.4620 0.04198 0.03660 -0.0271 0.0097 1.0000
14.500 1.4610 0.04458 0.03929 -0.0262 0.0095 1.0000
14.750 1.4595 0.04735 0.04216 -0.0256 0.0094 1.0000
15.000 1.4568 0.05039 0.04530 -0.0253 0.0093 1.0000
15.250 1.4570 0.05326 0.04824 -0.0251 0.0090 1.0000
15.500 1.4610 0.05576 0.05080 -0.0253 0.0087 1.0000
15.750 1.4548 0.05964 0.05478 -0.0256 0.0086 1.0000
16.000 1.4491 0.06360 0.05885 -0.0261 0.0086 1.0000
16.250 1.4443 0.06763 0.06296 -0.0270 0.0084 1.0000
16.500 1.4332 0.07270 0.06813 -0.0282 0.0082 1.0000
16.750 1.4236 0.07765 0.07319 -0.0296 0.0081 1.0000
17.000 1.4132 0.08287 0.07851 -0.0312 0.0081 1.0000
17.250 1.3946 0.08928 0.08504 -0.0331 0.0079 1.0000
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