GOE 369 AIRFOIL (goe369-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 369 AIRFOIL (goe369-il) Reynolds number: 500,000 Max Cl/Cd: 105.86 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe369-il-500000.txt Download as CSV file: xf-goe369-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 369 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.2731 0.08321 0.08115 -0.0146 1.0000 0.0098
-8.000 -0.2692 0.07995 0.07792 -0.0149 1.0000 0.0100
-7.750 -0.2658 0.07687 0.07487 -0.0155 1.0000 0.0101
-7.500 -0.3475 0.08902 0.08691 -0.0132 1.0000 0.0096
-7.250 -0.3420 0.08577 0.08368 -0.0129 1.0000 0.0098
-7.000 -0.3355 0.08289 0.08082 -0.0140 1.0000 0.0100
-6.750 -0.3277 0.08004 0.07800 -0.0157 1.0000 0.0101
-6.500 -0.3186 0.07715 0.07513 -0.0174 1.0000 0.0105
-6.250 -0.3082 0.07422 0.07222 -0.0194 1.0000 0.0107
-6.000 -0.2967 0.07123 0.06925 -0.0214 1.0000 0.0110
-5.750 -0.2818 0.06804 0.06607 -0.0240 0.9996 0.0117
-5.500 -0.2268 0.06315 0.06106 -0.0369 0.9854 0.0127
-5.250 -0.1756 0.05826 0.05603 -0.0472 0.9651 0.0128
-5.000 -0.1362 0.05229 0.05000 -0.0546 0.9304 0.0130
-4.750 -0.1014 0.04849 0.04594 -0.0595 0.8656 0.0134
-4.500 -0.0802 0.04597 0.04314 -0.0606 0.8227 0.0137
-4.250 -0.0575 0.04344 0.04041 -0.0618 0.7977 0.0141
-4.000 -0.0331 0.04084 0.03762 -0.0630 0.7796 0.0147
-3.750 -0.0070 0.03826 0.03486 -0.0641 0.7647 0.0154
-3.250 0.0581 0.03369 0.02974 -0.0653 0.7407 0.0168
-3.000 0.0829 0.03012 0.02593 -0.0656 0.7299 0.0171
-2.750 0.1031 0.02773 0.02345 -0.0660 0.7189 0.0177
-2.500 0.1276 0.02599 0.02155 -0.0659 0.7084 0.0187
-2.250 0.1552 0.02423 0.01958 -0.0656 0.6981 0.0207
-2.000 0.1885 0.02384 0.01877 -0.0642 0.6897 0.0223
-1.750 0.2115 0.02029 0.01504 -0.0643 0.6821 0.0233
-1.500 0.2369 0.01891 0.01353 -0.0641 0.6751 0.0242
-1.250 0.2636 0.01770 0.01215 -0.0637 0.6677 0.0256
-1.000 0.2916 0.01675 0.01096 -0.0630 0.6612 0.0283
-0.750 0.3208 0.01674 0.01066 -0.0621 0.6535 0.0298
0.500 0.4551 0.01059 0.00365 -0.0591 0.6163 0.0309
0.750 0.4814 0.01004 0.00313 -0.0586 0.6088 0.0340
1.000 0.5077 0.00966 0.00270 -0.0580 0.6013 0.0357
1.250 0.5341 0.00937 0.00238 -0.0575 0.5928 0.0377
1.500 0.5605 0.00913 0.00211 -0.0570 0.5840 0.0412
1.750 0.5869 0.00897 0.00190 -0.0565 0.5735 0.0447
2.000 0.6135 0.00890 0.00178 -0.0561 0.5613 0.0499
2.250 0.6403 0.00884 0.00175 -0.0557 0.5490 0.0654
2.500 0.6843 0.00699 0.00185 -0.0598 0.5334 1.0000
2.750 0.7103 0.00709 0.00186 -0.0592 0.5182 1.0000
3.000 0.7362 0.00721 0.00189 -0.0587 0.5029 1.0000
3.250 0.7621 0.00733 0.00195 -0.0582 0.4853 1.0000
3.500 0.7878 0.00748 0.00202 -0.0577 0.4642 1.0000
3.750 0.8130 0.00768 0.00211 -0.0572 0.4395 1.0000
4.000 0.8379 0.00793 0.00223 -0.0566 0.4104 1.0000
4.250 0.8623 0.00824 0.00241 -0.0559 0.3780 1.0000
4.500 0.8864 0.00860 0.00262 -0.0553 0.3468 1.0000
4.750 0.9107 0.00896 0.00284 -0.0547 0.3193 1.0000
5.000 0.9351 0.00931 0.00309 -0.0541 0.2920 1.0000
5.250 0.9590 0.00972 0.00335 -0.0535 0.2599 1.0000
5.500 0.9823 0.01020 0.00367 -0.0528 0.2216 1.0000
5.750 1.0052 0.01073 0.00403 -0.0521 0.1910 1.0000
6.000 1.0284 0.01121 0.00441 -0.0514 0.1718 1.0000
6.250 1.0520 0.01164 0.00478 -0.0508 0.1571 1.0000
6.500 1.0755 0.01207 0.00518 -0.0502 0.1446 1.0000
6.750 1.0995 0.01244 0.00553 -0.0496 0.1342 1.0000
7.000 1.1235 0.01280 0.00590 -0.0490 0.1253 1.0000
7.250 1.1466 0.01326 0.00633 -0.0483 0.1172 1.0000
7.500 1.1705 0.01360 0.00673 -0.0478 0.1111 1.0000
7.750 1.1927 0.01414 0.00724 -0.0470 0.1048 1.0000
8.000 1.2165 0.01447 0.00765 -0.0464 0.1007 1.0000
8.250 1.2390 0.01494 0.00813 -0.0457 0.0958 1.0000
8.500 1.2604 0.01551 0.00876 -0.0448 0.0910 1.0000
8.750 1.2837 0.01586 0.00917 -0.0442 0.0862 1.0000
9.000 1.3032 0.01659 0.00987 -0.0432 0.0794 1.0000
9.250 1.3273 0.01681 0.01021 -0.0427 0.0756 1.0000
9.500 1.3491 0.01727 0.01069 -0.0420 0.0703 1.0000
9.750 1.3698 0.01781 0.01129 -0.0412 0.0657 1.0000
10.000 1.3922 0.01816 0.01171 -0.0405 0.0614 1.0000
10.250 1.4114 0.01880 0.01236 -0.0395 0.0560 1.0000
10.500 1.4336 0.01913 0.01279 -0.0389 0.0517 1.0000
10.750 1.4527 0.01973 0.01338 -0.0379 0.0450 1.0000
11.000 1.4703 0.02044 0.01408 -0.0368 0.0356 1.0000
11.250 1.4811 0.02175 0.01528 -0.0348 0.0203 1.0000
11.500 1.4888 0.02324 0.01678 -0.0324 0.0145 1.0000
11.750 1.4967 0.02449 0.01814 -0.0300 0.0128 1.0000
12.000 1.4962 0.02604 0.01980 -0.0264 0.0114 1.0000
12.250 1.4946 0.02770 0.02161 -0.0233 0.0106 1.0000
12.500 1.4967 0.02922 0.02329 -0.0210 0.0102 1.0000
12.750 1.4972 0.03105 0.02526 -0.0192 0.0096 1.0000
13.000 1.4956 0.03327 0.02762 -0.0179 0.0091 1.0000
13.250 1.4932 0.03584 0.03033 -0.0172 0.0087 1.0000
13.500 1.4876 0.03896 0.03360 -0.0169 0.0084 1.0000
13.750 1.4807 0.04247 0.03724 -0.0170 0.0083 1.0000
14.000 1.4686 0.04681 0.04173 -0.0177 0.0080 1.0000
14.250 1.4545 0.05163 0.04670 -0.0188 0.0078 1.0000
14.500 1.4421 0.05645 0.05167 -0.0200 0.0077 1.0000
14.750 1.4261 0.06195 0.05732 -0.0218 0.0076 1.0000
15.000 1.4120 0.06744 0.06296 -0.0238 0.0076 1.0000
15.250 1.3947 0.07366 0.06934 -0.0262 0.0075 1.0000
15.500 1.3814 0.07969 0.07550 -0.0289 0.0074 1.0000
15.750 1.3681 0.08592 0.08187 -0.0317 0.0074 1.0000
16.000 1.3569 0.09212 0.08821 -0.0347 0.0074 1.0000
16.250 1.3441 0.09877 0.09500 -0.0380 0.0073 1.0000
16.500 1.3316 0.10553 0.10189 -0.0414 0.0073 1.0000
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Polar data table (+)
Polar graphs
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