GOE 369 AIRFOIL (goe369-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 369 AIRFOIL (goe369-il) Reynolds number: 100,000 Max Cl/Cd: 59.23 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe369-il-100000.txt Download as CSV file: xf-goe369-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3522 0.09983 0.09503 -0.0114 1.0000 0.0378
-7.750 -0.3495 0.09795 0.09323 -0.0130 1.0000 0.0383
-7.500 -0.3466 0.09651 0.09186 -0.0162 1.0000 0.0387
-7.250 -0.3376 0.09501 0.09040 -0.0215 1.0000 0.0391
-7.000 -0.3244 0.09320 0.08860 -0.0269 1.0000 0.0393
-6.750 -0.3158 0.08853 0.08398 -0.0274 1.0000 0.0397
-6.500 -0.3127 0.08283 0.07837 -0.0224 1.0000 0.0409
-6.250 -0.3043 0.07940 0.07499 -0.0221 1.0000 0.0421
-6.000 -0.2941 0.07638 0.07202 -0.0231 1.0000 0.0434
-5.750 -0.2826 0.07347 0.06914 -0.0246 1.0000 0.0450
-5.500 -0.2695 0.07063 0.06633 -0.0265 1.0000 0.0467
-5.250 -0.2529 0.06802 0.06372 -0.0294 1.0000 0.0489
-5.000 -0.2207 0.06743 0.06294 -0.0365 1.0000 0.0509
-4.750 -0.2117 0.06429 0.05984 -0.0368 1.0000 0.0516
-4.500 -0.2225 0.06164 0.05737 -0.0327 1.0000 0.0522
-4.250 -0.2289 0.05970 0.05550 -0.0301 0.9987 0.0530
-4.000 -0.1896 0.05536 0.05111 -0.0359 0.9892 0.0581
-3.750 -0.1298 0.05172 0.04713 -0.0462 0.9786 0.0654
-3.500 -0.0908 0.04768 0.04305 -0.0512 0.9699 0.0746
-3.250 -0.0464 0.04390 0.03906 -0.0571 0.9592 0.0811
-3.000 0.0012 0.04110 0.03594 -0.0627 0.9489 0.0926
-2.750 0.0462 0.03757 0.03225 -0.0677 0.9422 0.1068
-2.500 0.0816 0.03474 0.02930 -0.0706 0.9309 0.1231
-2.250 0.1390 0.01343 0.00825 -0.0750 0.8950 0.1801
-1.500 0.1967 0.02534 0.01992 -0.0750 0.8885 0.3584
-1.250 0.2249 0.02339 0.01791 -0.0747 0.8770 0.4043
-1.000 0.2684 0.02226 0.01629 -0.0769 0.8651 0.3800
-0.750 0.3366 0.02202 0.01439 -0.0790 0.8547 0.1478
-0.500 0.3681 0.02096 0.01294 -0.0777 0.8420 0.1152
-0.250 0.3973 0.02000 0.01168 -0.0766 0.8301 0.0993
0.000 0.4263 0.01952 0.01084 -0.0754 0.8190 0.0904
0.250 0.4540 0.01885 0.01000 -0.0744 0.8088 0.0908
0.500 0.4801 0.01799 0.00918 -0.0736 0.7978 0.0947
0.750 0.5054 0.01750 0.00871 -0.0725 0.7865 0.0974
1.000 0.5310 0.01717 0.00833 -0.0715 0.7758 0.1069
1.250 0.5576 0.01694 0.00798 -0.0706 0.7658 0.1189
1.500 0.5831 0.01669 0.00781 -0.0697 0.7541 0.1576
1.750 0.6248 0.01504 0.00758 -0.0719 0.7411 1.0000
2.000 0.6488 0.01527 0.00762 -0.0706 0.7274 1.0000
2.250 0.6727 0.01547 0.00766 -0.0692 0.7128 1.0000
2.500 0.6966 0.01562 0.00768 -0.0678 0.6974 1.0000
2.750 0.7206 0.01576 0.00770 -0.0664 0.6820 1.0000
3.000 0.7447 0.01589 0.00775 -0.0651 0.6667 1.0000
3.250 0.7691 0.01605 0.00786 -0.0639 0.6518 1.0000
3.500 0.7935 0.01620 0.00795 -0.0628 0.6366 1.0000
3.750 0.8180 0.01630 0.00798 -0.0616 0.6205 1.0000
4.000 0.8419 0.01636 0.00801 -0.0603 0.6020 1.0000
4.250 0.8655 0.01637 0.00799 -0.0589 0.5809 1.0000
4.500 0.8897 0.01633 0.00791 -0.0575 0.5607 1.0000
4.750 0.9129 0.01636 0.00796 -0.0562 0.5367 1.0000
5.000 0.9363 0.01638 0.00796 -0.0549 0.5117 1.0000
5.250 0.9591 0.01643 0.00798 -0.0535 0.4821 1.0000
5.500 0.9812 0.01657 0.00807 -0.0521 0.4473 1.0000
5.750 1.0021 0.01692 0.00826 -0.0506 0.4056 1.0000
6.000 1.0214 0.01760 0.00865 -0.0489 0.3602 1.0000
6.250 1.0401 0.01856 0.00932 -0.0474 0.3176 1.0000
6.500 1.0594 0.01958 0.01011 -0.0461 0.2834 1.0000
6.750 1.0795 0.02059 0.01096 -0.0449 0.2577 1.0000
7.000 1.1005 0.02158 0.01191 -0.0438 0.2361 1.0000
7.250 1.1215 0.02260 0.01285 -0.0429 0.2191 1.0000
7.500 1.1430 0.02369 0.01388 -0.0420 0.2049 1.0000
7.750 1.1650 0.02486 0.01509 -0.0412 0.1930 1.0000
8.000 1.1869 0.02611 0.01637 -0.0404 0.1823 1.0000
8.250 1.2104 0.02757 0.01769 -0.0400 0.1731 1.0000
8.500 1.2315 0.02883 0.01924 -0.0390 0.1647 1.0000
8.750 1.2539 0.03045 0.02092 -0.0385 0.1569 1.0000
9.000 1.2742 0.03179 0.02246 -0.0376 0.1490 1.0000
9.250 1.2957 0.03372 0.02453 -0.0369 0.1430 1.0000
9.500 1.3143 0.03546 0.02662 -0.0358 0.1372 1.0000
9.750 1.3367 0.03756 0.02873 -0.0355 0.1321 1.0000
10.000 1.3492 0.03983 0.03158 -0.0337 0.1276 1.0000
10.250 1.3654 0.04157 0.03358 -0.0325 0.1219 1.0000
10.500 1.3823 0.04413 0.03625 -0.0318 0.1172 1.0000
10.750 1.3869 0.04584 0.03850 -0.0294 0.1109 1.0000
11.000 1.4000 0.04632 0.03897 -0.0283 0.1020 1.0000
11.250 1.4156 0.04650 0.03911 -0.0272 0.0933 1.0000
11.500 1.4116 0.04892 0.04204 -0.0245 0.0876 1.0000
11.750 1.4231 0.04986 0.04283 -0.0233 0.0788 1.0000
12.000 1.4083 0.05234 0.04583 -0.0197 0.0740 1.0000
12.250 1.4105 0.05338 0.04670 -0.0177 0.0663 1.0000
12.500 1.3893 0.05657 0.05031 -0.0145 0.0642 1.0000
12.750 1.3714 0.06001 0.05404 -0.0130 0.0614 1.0000
13.000 1.3766 0.06190 0.05571 -0.0123 0.0556 1.0000
13.250 1.3550 0.06652 0.06067 -0.0124 0.0551 1.0000
13.500 1.3324 0.07193 0.06638 -0.0136 0.0548 1.0000
13.750 1.3089 0.07799 0.07270 -0.0157 0.0547 1.0000
14.000 1.2851 0.08468 0.07961 -0.0186 0.0550 1.0000
14.250 1.2608 0.09206 0.08716 -0.0223 0.0554 1.0000
14.500 1.2365 0.10001 0.09525 -0.0266 0.0558 1.0000
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Polar data table (+)
Polar graphs
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