GOE 335 (D.F.W.) AIRFOIL (goe335-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 335 (D.F.W.) AIRFOIL (goe335-il) Reynolds number: 200,000 Max Cl/Cd: 75.36 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe335-il-200000.txt Download as CSV file: xf-goe335-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 335 (D.F.W.) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.3214 0.08843 0.08519 -0.0226 1.0000 0.0302
-7.000 -0.3244 0.08633 0.08316 -0.0217 1.0000 0.0307
-6.750 -0.3239 0.08388 0.08077 -0.0219 1.0000 0.0314
-6.500 -0.3234 0.08149 0.07843 -0.0221 1.0000 0.0320
-6.250 -0.3232 0.07915 0.07615 -0.0223 1.0000 0.0327
-6.000 -0.3254 0.07708 0.07415 -0.0220 1.0000 0.0333
-5.750 -0.3341 0.07566 0.07278 -0.0204 1.0000 0.0339
-5.500 -0.2794 0.07105 0.06801 -0.0369 0.9940 0.0368
-5.250 -0.2259 0.06595 0.06271 -0.0492 0.9868 0.0373
-5.000 -0.2064 0.05855 0.05534 -0.0528 0.9818 0.0390
-4.750 -0.1788 0.05525 0.05203 -0.0555 0.9746 0.0419
-4.500 -0.1336 0.05078 0.04741 -0.0635 0.9700 0.0461
-4.250 -0.0754 0.04521 0.04133 -0.0742 0.9607 0.0508
-4.000 -0.0475 0.04128 0.03748 -0.0770 0.9566 0.0533
-3.750 -0.0142 0.03847 0.03456 -0.0799 0.9476 0.0587
-3.500 0.0303 0.03451 0.03031 -0.0852 0.9430 0.0678
-3.250 0.0701 0.03156 0.02689 -0.0884 0.9332 0.0790
-3.000 0.1083 0.03046 0.02552 -0.0905 0.9258 0.0912
-2.750 0.1350 0.02678 0.02191 -0.0921 0.9165 0.0970
-2.500 0.1668 0.02486 0.01978 -0.0933 0.9062 0.1109
-2.250 0.1997 0.02304 0.01775 -0.0946 0.8964 0.1255
-2.000 0.2413 0.01866 0.01229 -0.0947 0.8874 0.0800
-1.750 0.2729 0.01665 0.00995 -0.0947 0.8757 0.0709
-1.500 0.3043 0.01503 0.00784 -0.0944 0.8641 0.0668
-1.250 0.3340 0.01411 0.00671 -0.0943 0.8521 0.0670
-1.000 0.3624 0.01358 0.00609 -0.0940 0.8395 0.0707
-0.750 0.3901 0.01297 0.00534 -0.0935 0.8265 0.0715
-0.500 0.4169 0.01249 0.00475 -0.0928 0.8131 0.0730
-0.250 0.4430 0.01213 0.00432 -0.0920 0.7993 0.0757
0.000 0.4684 0.01176 0.00392 -0.0912 0.7854 0.0796
0.250 0.4937 0.01153 0.00369 -0.0904 0.7710 0.0875
0.500 0.5188 0.01130 0.00348 -0.0895 0.7555 0.1073
0.750 0.5578 0.00901 0.00326 -0.0918 0.7383 1.0000
1.000 0.5823 0.00909 0.00315 -0.0907 0.7190 1.0000
1.250 0.6066 0.00917 0.00307 -0.0896 0.6971 1.0000
1.500 0.6306 0.00928 0.00300 -0.0885 0.6721 1.0000
1.750 0.6542 0.00942 0.00296 -0.0873 0.6418 1.0000
2.000 0.6775 0.00962 0.00295 -0.0861 0.6066 1.0000
2.250 0.7005 0.00990 0.00298 -0.0850 0.5708 1.0000
2.500 0.7238 0.01021 0.00309 -0.0839 0.5391 1.0000
2.750 0.7475 0.01054 0.00322 -0.0830 0.5148 1.0000
3.000 0.7718 0.01087 0.00339 -0.0823 0.4960 1.0000
3.250 0.7965 0.01121 0.00360 -0.0817 0.4810 1.0000
3.500 0.8214 0.01155 0.00386 -0.0811 0.4681 1.0000
3.750 0.8463 0.01190 0.00412 -0.0806 0.4564 1.0000
4.000 0.8715 0.01227 0.00439 -0.0801 0.4464 1.0000
4.250 0.8968 0.01257 0.00469 -0.0796 0.4365 1.0000
4.500 0.9222 0.01293 0.00504 -0.0792 0.4281 1.0000
4.750 0.9476 0.01326 0.00537 -0.0787 0.4196 1.0000
5.000 0.9727 0.01358 0.00572 -0.0783 0.4107 1.0000
5.250 0.9980 0.01398 0.00607 -0.0778 0.4028 1.0000
5.500 1.0227 0.01423 0.00643 -0.0773 0.3937 1.0000
5.750 1.0467 0.01452 0.00677 -0.0766 0.3825 1.0000
6.000 1.0704 0.01478 0.00706 -0.0759 0.3708 1.0000
6.250 1.0928 0.01492 0.00727 -0.0749 0.3545 1.0000
6.500 1.1158 0.01513 0.00754 -0.0740 0.3412 1.0000
6.750 1.1387 0.01531 0.00784 -0.0731 0.3265 1.0000
7.000 1.1597 0.01542 0.00800 -0.0719 0.3004 1.0000
7.250 1.1802 0.01566 0.00821 -0.0706 0.2536 1.0000
7.500 1.1844 0.01780 0.00935 -0.0675 0.0977 1.0000
7.750 1.1916 0.01995 0.01103 -0.0646 0.0403 1.0000
8.000 1.2065 0.02116 0.01229 -0.0626 0.0323 1.0000
8.250 1.2214 0.02226 0.01359 -0.0606 0.0298 1.0000
8.500 1.2343 0.02344 0.01493 -0.0584 0.0281 1.0000
8.750 1.2443 0.02475 0.01638 -0.0558 0.0269 1.0000
9.000 1.2517 0.02619 0.01792 -0.0529 0.0260 1.0000
9.250 1.2555 0.02771 0.01954 -0.0496 0.0252 1.0000
9.500 1.2582 0.02941 0.02130 -0.0463 0.0245 1.0000
9.750 1.2599 0.03173 0.02368 -0.0432 0.0234 1.0000
10.000 1.2694 0.03387 0.02591 -0.0410 0.0225 1.0000
10.250 1.2837 0.03582 0.02801 -0.0395 0.0223 1.0000
10.500 1.3015 0.03815 0.03051 -0.0383 0.0221 1.0000
10.750 1.3211 0.04099 0.03356 -0.0375 0.0221 1.0000
11.000 1.3406 0.04468 0.03750 -0.0370 0.0224 1.0000
11.250 1.3658 0.04951 0.04259 -0.0375 0.0232 1.0000
11.500 1.3688 0.05064 0.04394 -0.0344 0.0237 1.0000
11.750 1.3621 0.05303 0.04684 -0.0304 0.0256 1.0000
12.000 1.3460 0.05821 0.05254 -0.0271 0.0279 1.0000
12.250 1.3341 0.06263 0.05725 -0.0253 0.0291 1.0000
12.500 1.3197 0.06773 0.06259 -0.0242 0.0301 1.0000
13.750 1.0972 0.09294 0.08912 -0.0282 0.0293 1.0000
14.000 1.0676 0.09959 0.09596 -0.0321 0.0291 1.0000
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Polar data table (+)
Polar graphs
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