GOE 758 AIRFOIL (goe758-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 758 AIRFOIL (goe758-il) Reynolds number: 500,000 Max Cl/Cd: 102.78 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe758-il-500000-n5.txt Download as CSV file: xf-goe758-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 758 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3974 0.04018 0.03697 -0.1176 0.8707 0.0209
-10.250 -0.4166 0.03752 0.03407 -0.1157 0.8518 0.0210
-10.000 -0.4187 0.03547 0.03182 -0.1144 0.8374 0.0211
-9.750 -0.4142 0.03373 0.02989 -0.1133 0.8243 0.0213
-9.500 -0.4064 0.03210 0.02806 -0.1121 0.8116 0.0214
-9.250 -0.3969 0.03045 0.02620 -0.1110 0.7987 0.0216
-9.000 -0.3854 0.02882 0.02433 -0.1098 0.7849 0.0219
-8.750 -0.3723 0.02723 0.02249 -0.1087 0.7695 0.0222
-8.500 -0.3571 0.02587 0.02088 -0.1076 0.7512 0.0226
-8.250 -0.3412 0.02450 0.01920 -0.1064 0.7301 0.0230
-8.000 -0.3242 0.02323 0.01760 -0.1051 0.7069 0.0234
-7.250 -0.2646 0.02021 0.01371 -0.1021 0.6590 0.0243
-7.000 -0.2419 0.01954 0.01281 -0.1014 0.6497 0.0245
-6.750 -0.2184 0.01899 0.01205 -0.1007 0.6417 0.0246
-6.500 -0.1960 0.01773 0.01069 -0.1002 0.6355 0.0251
-6.250 -0.1718 0.01707 0.00995 -0.0997 0.6293 0.0255
-5.750 -0.1221 0.01597 0.00867 -0.0988 0.6192 0.0260
-5.500 -0.0967 0.01546 0.00808 -0.0984 0.6145 0.0262
-5.250 -0.0714 0.01501 0.00755 -0.0980 0.6100 0.0265
-5.000 -0.0459 0.01460 0.00705 -0.0976 0.6059 0.0268
-4.750 -0.0200 0.01417 0.00658 -0.0972 0.6021 0.0270
-4.500 0.0060 0.01379 0.00615 -0.0969 0.5981 0.0273
-4.250 0.0318 0.01344 0.00575 -0.0965 0.5941 0.0276
-4.000 0.0575 0.01313 0.00537 -0.0960 0.5904 0.0279
-3.750 0.0839 0.01284 0.00506 -0.0957 0.5869 0.0283
-3.500 0.1103 0.01258 0.00476 -0.0954 0.5830 0.0287
-3.250 0.1367 0.01235 0.00449 -0.0951 0.5791 0.0291
-3.000 0.1628 0.01213 0.00422 -0.0948 0.5751 0.0293
-2.750 0.1892 0.01192 0.00398 -0.0944 0.5712 0.0295
-2.500 0.2152 0.01160 0.00365 -0.0941 0.5669 0.0299
-2.250 0.2414 0.01136 0.00339 -0.0938 0.5624 0.0304
-2.000 0.2677 0.01119 0.00318 -0.0934 0.5583 0.0309
-1.750 0.2946 0.01103 0.00301 -0.0932 0.5546 0.0315
-1.500 0.3217 0.01090 0.00287 -0.0930 0.5505 0.0321
-1.250 0.3487 0.01080 0.00274 -0.0928 0.5462 0.0328
-1.000 0.3755 0.01073 0.00263 -0.0926 0.5422 0.0336
-0.750 0.4027 0.01066 0.00254 -0.0924 0.5385 0.0347
-0.500 0.4300 0.01058 0.00246 -0.0922 0.5342 0.0360
-0.250 0.4570 0.01052 0.00238 -0.0920 0.5296 0.0379
0.000 0.4837 0.01049 0.00232 -0.0917 0.5253 0.0404
0.250 0.5103 0.01029 0.00228 -0.0915 0.5210 0.0870
0.500 0.5348 0.00983 0.00226 -0.0911 0.5163 0.2362
0.750 0.5599 0.00959 0.00227 -0.0907 0.5113 0.3298
1.000 0.5847 0.00934 0.00231 -0.0903 0.5065 0.4348
1.250 0.6090 0.00909 0.00241 -0.0897 0.5013 0.5504
1.500 0.6340 0.00901 0.00247 -0.0891 0.4960 0.6096
1.750 0.6590 0.00894 0.00252 -0.0885 0.4906 0.6575
2.000 0.6823 0.00878 0.00259 -0.0875 0.4845 0.7282
2.500 0.7867 0.00854 0.00282 -0.0980 0.4702 1.0000
2.750 0.8106 0.00867 0.00288 -0.0972 0.4633 1.0000
3.000 0.8354 0.00877 0.00296 -0.0966 0.4565 1.0000
3.250 0.8596 0.00890 0.00305 -0.0959 0.4496 1.0000
3.500 0.8839 0.00903 0.00314 -0.0952 0.4431 1.0000
3.750 0.9081 0.00917 0.00325 -0.0945 0.4354 1.0000
4.000 0.9321 0.00933 0.00336 -0.0938 0.4279 1.0000
4.250 0.9562 0.00948 0.00348 -0.0931 0.4202 1.0000
4.500 0.9800 0.00965 0.00363 -0.0924 0.4126 1.0000
4.750 1.0032 0.00985 0.00378 -0.0915 0.4026 1.0000
5.000 1.0265 0.01004 0.00393 -0.0907 0.3925 1.0000
5.250 1.0492 0.01026 0.00412 -0.0899 0.3840 1.0000
5.500 1.0730 0.01044 0.00429 -0.0892 0.3769 1.0000
5.750 1.0953 0.01068 0.00449 -0.0883 0.3693 1.0000
6.000 1.1184 0.01089 0.00469 -0.0875 0.3608 1.0000
6.250 1.1402 0.01114 0.00492 -0.0865 0.3528 1.0000
6.500 1.1629 0.01136 0.00513 -0.0856 0.3454 1.0000
6.750 1.1844 0.01162 0.00538 -0.0846 0.3394 1.0000
7.000 1.2068 0.01184 0.00562 -0.0837 0.3330 1.0000
7.250 1.2269 0.01215 0.00590 -0.0825 0.3245 1.0000
7.500 1.2473 0.01243 0.00617 -0.0813 0.3149 1.0000
7.750 1.2658 0.01277 0.00649 -0.0798 0.3054 1.0000
8.000 1.2847 0.01309 0.00680 -0.0784 0.2962 1.0000
8.250 1.3017 0.01340 0.00712 -0.0766 0.2887 1.0000
8.500 1.3168 0.01377 0.00747 -0.0745 0.2789 1.0000
8.750 1.3322 0.01415 0.00783 -0.0725 0.2687 1.0000
9.000 1.3461 0.01459 0.00827 -0.0703 0.2580 1.0000
9.250 1.3587 0.01511 0.00875 -0.0680 0.2456 1.0000
9.500 1.3704 0.01570 0.00930 -0.0657 0.2321 1.0000
9.750 1.3796 0.01642 0.00996 -0.0632 0.2142 1.0000
10.000 1.3827 0.01749 0.01090 -0.0600 0.1900 1.0000
10.250 1.3870 0.01857 0.01190 -0.0572 0.1686 1.0000
10.500 1.3743 0.02072 0.01380 -0.0529 0.1253 1.0000
10.750 1.3620 0.02311 0.01598 -0.0492 0.0920 1.0000
11.000 1.3635 0.02477 0.01762 -0.0471 0.0805 1.0000
11.250 1.3673 0.02637 0.01923 -0.0454 0.0723 1.0000
11.500 1.3694 0.02818 0.02104 -0.0438 0.0617 1.0000
11.750 1.3583 0.03120 0.02393 -0.0418 0.0370 1.0000
12.000 1.3514 0.03408 0.02678 -0.0403 0.0249 1.0000
12.250 1.3515 0.03648 0.02921 -0.0394 0.0209 1.0000
12.500 1.3541 0.03871 0.03150 -0.0388 0.0191 1.0000
12.750 1.3558 0.04109 0.03394 -0.0382 0.0177 1.0000
13.000 1.3585 0.04344 0.03636 -0.0377 0.0168 1.0000
13.250 1.3606 0.04587 0.03887 -0.0373 0.0160 1.0000
13.500 1.3619 0.04843 0.04152 -0.0370 0.0154 1.0000
13.750 1.3620 0.05117 0.04433 -0.0367 0.0147 1.0000
14.000 1.3595 0.05426 0.04749 -0.0365 0.0140 1.0000
14.250 1.3584 0.05723 0.05054 -0.0364 0.0136 1.0000
14.500 1.3586 0.06011 0.05350 -0.0363 0.0131 1.0000
14.750 1.3583 0.06310 0.05659 -0.0364 0.0128 1.0000
15.000 1.3566 0.06633 0.05990 -0.0365 0.0125 1.0000
15.250 1.3544 0.06967 0.06334 -0.0368 0.0122 1.0000
15.500 1.3516 0.07318 0.06693 -0.0371 0.0119 1.0000
15.750 1.3487 0.07676 0.07059 -0.0376 0.0116 1.0000
16.000 1.3444 0.08056 0.07447 -0.0381 0.0113 1.0000
16.250 1.3391 0.08459 0.07858 -0.0388 0.0111 1.0000
16.500 1.3324 0.08889 0.08298 -0.0397 0.0109 1.0000
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