GOE 335 (D.F.W.) AIRFOIL (goe335-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: GOE 335 (D.F.W.) AIRFOIL (goe335-il) Reynolds number: 500,000 Max Cl/Cd: 102.1 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe335-il-500000.txt Download as CSV file: xf-goe335-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3265 0.08784 0.08576 -0.0217 1.0000 0.0160
-7.250 -0.3313 0.08601 0.08397 -0.0203 1.0000 0.0163
-7.000 -0.3365 0.08405 0.08207 -0.0191 1.0000 0.0167
-6.750 -0.3374 0.08167 0.07973 -0.0191 1.0000 0.0172
-6.500 -0.3111 0.07730 0.07535 -0.0278 0.9970 0.0189
-6.250 -0.2659 0.07171 0.06969 -0.0423 0.9914 0.0194
-6.000 -0.2298 0.06641 0.06432 -0.0511 0.9862 0.0195
-5.750 -0.1930 0.06091 0.05875 -0.0595 0.9814 0.0196
-5.500 -0.1676 0.05349 0.05127 -0.0665 0.9738 0.0201
-5.250 -0.1371 0.05032 0.04806 -0.0705 0.9695 0.0209
-5.000 -0.1067 0.04711 0.04479 -0.0746 0.9593 0.0221
-4.750 -0.0679 0.04307 0.04061 -0.0804 0.9482 0.0248
-4.500 -0.0181 0.03911 0.03638 -0.0865 0.9348 0.0268
-4.250 0.0190 0.03428 0.03127 -0.0906 0.9158 0.0269
-4.000 0.0440 0.02752 0.02417 -0.0941 0.8902 0.0286
-3.750 0.0707 0.02622 0.02269 -0.0948 0.8649 0.0302
-3.500 0.0970 0.02442 0.02060 -0.0950 0.8455 0.0337
-3.250 0.1285 0.02390 0.01963 -0.0942 0.8311 0.0374
-3.000 0.1482 0.01908 0.01447 -0.0945 0.8193 0.0405
-2.750 0.1733 0.01811 0.01332 -0.0942 0.8081 0.0434
-2.500 0.1997 0.01669 0.01159 -0.0936 0.7978 0.0467
-2.250 0.2266 0.01312 0.00726 -0.0924 0.7884 0.0395
-2.000 0.2530 0.01212 0.00604 -0.0919 0.7780 0.0393
-1.750 0.2793 0.01139 0.00519 -0.0914 0.7682 0.0411
-1.250 0.3322 0.01028 0.00386 -0.0904 0.7478 0.0430
-1.000 0.3585 0.00986 0.00336 -0.0899 0.7369 0.0437
-0.750 0.3847 0.00951 0.00294 -0.0894 0.7253 0.0444
-0.500 0.4108 0.00926 0.00262 -0.0889 0.7124 0.0460
-0.250 0.4368 0.00901 0.00231 -0.0883 0.6980 0.0472
0.000 0.4628 0.00882 0.00205 -0.0877 0.6820 0.0485
0.250 0.4888 0.00870 0.00186 -0.0872 0.6643 0.0499
0.750 0.5399 0.00854 0.00152 -0.0859 0.6198 0.0598
1.000 0.5647 0.00845 0.00149 -0.0852 0.5896 0.1178
1.250 0.6005 0.00671 0.00165 -0.0876 0.5459 1.0000
1.500 0.6234 0.00703 0.00169 -0.0865 0.4983 1.0000
1.750 0.6466 0.00736 0.00178 -0.0856 0.4624 1.0000
2.000 0.6710 0.00763 0.00188 -0.0849 0.4405 1.0000
2.250 0.6959 0.00786 0.00199 -0.0843 0.4248 1.0000
2.500 0.7211 0.00807 0.00211 -0.0837 0.4136 1.0000
2.750 0.7463 0.00828 0.00224 -0.0832 0.4040 1.0000
3.000 0.7721 0.00844 0.00236 -0.0828 0.3956 1.0000
3.250 0.7974 0.00865 0.00250 -0.0822 0.3871 1.0000
3.500 0.8233 0.00881 0.00265 -0.0819 0.3792 1.0000
3.750 0.8487 0.00901 0.00281 -0.0814 0.3724 1.0000
4.000 0.8747 0.00915 0.00295 -0.0810 0.3655 1.0000
4.250 0.8999 0.00938 0.00313 -0.0805 0.3593 1.0000
4.500 0.9262 0.00950 0.00330 -0.0802 0.3533 1.0000
4.750 0.9513 0.00971 0.00347 -0.0797 0.3447 1.0000
5.000 0.9772 0.00983 0.00362 -0.0794 0.3350 1.0000
5.250 1.0027 0.01000 0.00379 -0.0790 0.3254 1.0000
5.500 1.0278 0.01021 0.00399 -0.0785 0.3162 1.0000
5.750 1.0530 0.01038 0.00416 -0.0780 0.3032 1.0000
6.000 1.0782 0.01056 0.00434 -0.0776 0.2871 1.0000
6.250 1.1028 0.01081 0.00454 -0.0771 0.2635 1.0000
6.500 1.1223 0.01157 0.00491 -0.0759 0.1911 1.0000
6.750 1.1309 0.01361 0.00619 -0.0732 0.0666 1.0000
7.000 1.1472 0.01482 0.00714 -0.0715 0.0218 1.0000
7.250 1.1685 0.01545 0.00784 -0.0704 0.0189 1.0000
7.500 1.1883 0.01623 0.00873 -0.0690 0.0168 1.0000
7.750 1.2061 0.01717 0.00982 -0.0673 0.0157 1.0000
8.000 1.2249 0.01793 0.01069 -0.0659 0.0150 1.0000
8.250 1.2425 0.01875 0.01161 -0.0643 0.0141 1.0000
8.500 1.2583 0.01968 0.01262 -0.0625 0.0133 1.0000
8.750 1.2719 0.02073 0.01377 -0.0604 0.0127 1.0000
9.000 1.2834 0.02188 0.01501 -0.0580 0.0122 1.0000
9.250 1.2915 0.02322 0.01643 -0.0552 0.0118 1.0000
9.500 1.2955 0.02464 0.01793 -0.0517 0.0115 1.0000
9.750 1.2967 0.02637 0.01977 -0.0480 0.0112 1.0000
10.000 1.2996 0.02852 0.02200 -0.0448 0.0110 1.0000
10.250 1.3095 0.03063 0.02420 -0.0427 0.0109 1.0000
10.500 1.3272 0.03353 0.02721 -0.0418 0.0108 1.0000
10.750 1.3361 0.03552 0.02938 -0.0398 0.0105 1.0000
11.000 1.3367 0.03586 0.02988 -0.0367 0.0102 1.0000
11.250 1.3440 0.03778 0.03195 -0.0348 0.0100 1.0000
11.500 1.3496 0.03990 0.03425 -0.0329 0.0098 1.0000
11.750 1.3541 0.04276 0.03731 -0.0312 0.0100 1.0000
12.000 1.3544 0.04559 0.04034 -0.0295 0.0099 1.0000
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Polar data table (+)
Polar graphs
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