GOE 648 AIRFOIL (goe648-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 648 AIRFOIL (goe648-il) Reynolds number: 500,000 Max Cl/Cd: 79.75 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe648-il-500000.txt Download as CSV file: xf-goe648-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 648 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
------ -------- --------- --------- -------- -------- --------
-16.000 -0.7683 0.07572 0.07230 -0.0744 1.0000 0.0262
-15.750 -0.8126 0.06522 0.06157 -0.0817 1.0000 0.0261
-15.500 -0.8365 0.05862 0.05483 -0.0859 1.0000 0.0262
-15.250 -0.8547 0.05321 0.04929 -0.0891 1.0000 0.0263
-15.000 -0.8652 0.04919 0.04521 -0.0910 1.0000 0.0265
-14.750 -0.8753 0.04551 0.04145 -0.0926 1.0000 0.0267
-14.500 -0.8865 0.04205 0.03789 -0.0937 1.0000 0.0268
-14.250 -0.8941 0.03944 0.03522 -0.0939 1.0000 0.0271
-14.000 -0.9051 0.03702 0.03270 -0.0932 1.0000 0.0273
-13.750 -0.9178 0.03508 0.03069 -0.0912 1.0000 0.0275
-13.500 -0.9351 0.03354 0.02906 -0.0877 1.0000 0.0276
-13.250 -0.9577 0.03259 0.02804 -0.0818 1.0000 0.0278
-13.000 -0.9789 0.03180 0.02717 -0.0754 1.0000 0.0279
-12.750 -0.9649 0.03053 0.02577 -0.0751 0.9980 0.0285
-12.500 -0.9382 0.02917 0.02422 -0.0770 0.9947 0.0292
-12.250 -0.9124 0.02768 0.02252 -0.0786 0.9915 0.0299
-12.000 -0.8866 0.02641 0.02126 -0.0796 0.9876 0.0307
-11.750 -0.8556 0.02553 0.02035 -0.0812 0.9845 0.0314
-11.500 -0.8221 0.02457 0.01930 -0.0833 0.9822 0.0323
-11.250 -0.7933 0.02362 0.01820 -0.0843 0.9782 0.0332
-11.000 -0.7642 0.02282 0.01723 -0.0851 0.9737 0.0339
-10.750 -0.7342 0.02154 0.01598 -0.0865 0.9709 0.0350
-10.500 -0.6996 0.02091 0.01533 -0.0882 0.9691 0.0361
-10.250 -0.6701 0.02027 0.01461 -0.0889 0.9655 0.0373
-10.000 -0.6427 0.01963 0.01385 -0.0890 0.9603 0.0383
-9.750 -0.6118 0.01859 0.01279 -0.0902 0.9576 0.0394
-9.500 -0.5770 0.01799 0.01220 -0.0918 0.9558 0.0407
-9.250 -0.5409 0.01742 0.01158 -0.0936 0.9544 0.0422
-9.000 -0.5136 0.01695 0.01102 -0.0934 0.9493 0.0434
-8.750 -0.4843 0.01613 0.01020 -0.0940 0.9449 0.0448
-8.500 -0.4493 0.01562 0.00970 -0.0955 0.9423 0.0464
-8.250 -0.4131 0.01515 0.00918 -0.0971 0.9398 0.0483
-8.000 -0.3849 0.01460 0.00858 -0.0971 0.9338 0.0499
-7.750 -0.3551 0.01412 0.00812 -0.0975 0.9273 0.0517
-7.500 -0.3186 0.01371 0.00766 -0.0990 0.9226 0.0542
-7.250 -0.2945 0.01330 0.00722 -0.0981 0.9131 0.0563
-7.000 -0.2623 0.01292 0.00684 -0.0989 0.9067 0.0590
-6.750 -0.2362 0.01267 0.00654 -0.0983 0.8969 0.0617
-6.500 -0.2063 0.01225 0.00610 -0.0985 0.8889 0.0650
-6.250 -0.1812 0.01206 0.00588 -0.0977 0.8783 0.0684
-6.000 -0.1526 0.01172 0.00549 -0.0977 0.8697 0.0724
-5.750 -0.1283 0.01151 0.00527 -0.0967 0.8587 0.0762
-5.500 -0.1017 0.01129 0.00498 -0.0962 0.8487 0.0804
-5.250 -0.0767 0.01102 0.00471 -0.0954 0.8384 0.0851
-5.000 -0.0509 0.01090 0.00451 -0.0947 0.8276 0.0891
-4.750 -0.0261 0.01060 0.00419 -0.0939 0.8159 0.0942
-4.500 -0.0017 0.01045 0.00400 -0.0929 0.8032 0.0989
-4.250 0.0227 0.01024 0.00378 -0.0920 0.7912 0.1045
-4.000 0.0482 0.01010 0.00359 -0.0913 0.7799 0.1106
-3.750 0.0723 0.00992 0.00341 -0.0902 0.7675 0.1183
-3.500 0.0969 0.00976 0.00325 -0.0893 0.7550 0.1291
-3.250 0.1208 0.00956 0.00310 -0.0883 0.7414 0.1485
-3.000 0.1439 0.00934 0.00295 -0.0872 0.7265 0.1826
-2.750 0.1668 0.00912 0.00285 -0.0860 0.7107 0.2265
-2.500 0.1900 0.00895 0.00276 -0.0849 0.6949 0.2672
-2.250 0.2136 0.00883 0.00269 -0.0839 0.6790 0.3016
-2.000 0.2368 0.00872 0.00262 -0.0827 0.6633 0.3377
-1.750 0.2595 0.00860 0.00258 -0.0815 0.6479 0.3809
-1.500 0.2818 0.00849 0.00256 -0.0802 0.6324 0.4323
-1.250 0.3042 0.00843 0.00257 -0.0789 0.6168 0.4839
-1.000 0.3266 0.00840 0.00259 -0.0776 0.6007 0.5277
-0.750 0.3498 0.00838 0.00261 -0.0764 0.5854 0.5637
-0.500 0.3729 0.00839 0.00264 -0.0752 0.5700 0.5948
-0.250 0.3955 0.00839 0.00267 -0.0738 0.5539 0.6251
0.000 0.4173 0.00840 0.00271 -0.0724 0.5366 0.6596
0.250 0.4381 0.00842 0.00278 -0.0706 0.5169 0.6977
0.500 0.4581 0.00849 0.00286 -0.0687 0.4944 0.7365
0.750 0.4779 0.00860 0.00293 -0.0668 0.4689 0.7715
1.000 0.4966 0.00873 0.00302 -0.0647 0.4402 0.8061
1.250 0.5156 0.00885 0.00313 -0.0627 0.4117 0.8448
1.750 0.6117 0.00943 0.00360 -0.0711 0.3653 0.9454
2.250 0.7051 0.01004 0.00400 -0.0791 0.3425 0.9889
2.500 0.7459 0.01037 0.00421 -0.0820 0.3342 1.0000
2.750 0.7651 0.01050 0.00430 -0.0802 0.3295 1.0000
3.000 0.7845 0.01065 0.00441 -0.0785 0.3245 1.0000
3.250 0.8034 0.01086 0.00455 -0.0767 0.3197 1.0000
3.500 0.8223 0.01110 0.00472 -0.0749 0.3150 1.0000
3.750 0.8439 0.01122 0.00484 -0.0735 0.3116 1.0000
4.000 0.8649 0.01138 0.00499 -0.0721 0.3075 1.0000
4.250 0.8851 0.01158 0.00514 -0.0705 0.3034 1.0000
4.500 0.9042 0.01186 0.00536 -0.0688 0.2991 1.0000
4.750 0.9254 0.01204 0.00553 -0.0674 0.2960 1.0000
5.000 0.9469 0.01219 0.00569 -0.0661 0.2928 1.0000
5.250 0.9678 0.01236 0.00586 -0.0647 0.2892 1.0000
5.500 0.9870 0.01258 0.00604 -0.0630 0.2854 1.0000
5.750 1.0048 0.01290 0.00630 -0.0611 0.2813 1.0000
6.000 1.0247 0.01306 0.00648 -0.0595 0.2786 1.0000
6.250 1.0448 0.01321 0.00666 -0.0580 0.2755 1.0000
6.500 1.0645 0.01340 0.00686 -0.0564 0.2721 1.0000
6.750 1.0833 0.01363 0.00706 -0.0547 0.2684 1.0000
7.000 1.1014 0.01398 0.00736 -0.0530 0.2643 1.0000
7.250 1.1219 0.01416 0.00759 -0.0517 0.2613 1.0000
7.500 1.1422 0.01434 0.00780 -0.0503 0.2579 1.0000
7.750 1.1619 0.01457 0.00804 -0.0489 0.2542 1.0000
8.000 1.1801 0.01487 0.00831 -0.0473 0.2501 1.0000
8.250 1.1987 0.01520 0.00863 -0.0459 0.2461 1.0000
8.500 1.2191 0.01540 0.00889 -0.0447 0.2424 1.0000
8.750 1.2384 0.01566 0.00916 -0.0433 0.2381 1.0000
9.000 1.2556 0.01602 0.00949 -0.0417 0.2336 1.0000
9.250 1.2741 0.01636 0.00985 -0.0404 0.2293 1.0000
9.500 1.2937 0.01665 0.01018 -0.0392 0.2253 1.0000
9.750 1.3116 0.01702 0.01056 -0.0378 0.2211 1.0000
10.000 1.3269 0.01753 0.01103 -0.0362 0.2167 1.0000
10.250 1.3459 0.01788 0.01144 -0.0351 0.2130 1.0000
10.500 1.3641 0.01828 0.01188 -0.0339 0.2087 1.0000
10.750 1.3799 0.01879 0.01239 -0.0324 0.2046 1.0000
11.000 1.3942 0.01942 0.01300 -0.0309 0.2005 1.0000
11.250 1.4126 0.01986 0.01352 -0.0299 0.1972 1.0000
11.500 1.4289 0.02041 0.01410 -0.0287 0.1934 1.0000
11.750 1.4427 0.02110 0.01479 -0.0272 0.1894 1.0000
12.000 1.4562 0.02185 0.01555 -0.0259 0.1856 1.0000
12.250 1.4729 0.02243 0.01621 -0.0249 0.1822 1.0000
12.500 1.4869 0.02318 0.01698 -0.0237 0.1781 1.0000
12.750 1.4984 0.02411 0.01790 -0.0223 0.1745 1.0000
13.000 1.5109 0.02500 0.01884 -0.0212 0.1712 1.0000
13.250 1.5256 0.02578 0.01969 -0.0202 0.1682 1.0000
13.500 1.5381 0.02672 0.02068 -0.0192 0.1650 1.0000
13.750 1.5478 0.02787 0.02184 -0.0180 0.1618 1.0000
14.000 1.5558 0.02918 0.02317 -0.0168 0.1586 1.0000
14.250 1.5696 0.03010 0.02420 -0.0161 0.1558 1.0000
14.500 1.5803 0.03127 0.02543 -0.0153 0.1527 1.0000
14.750 1.5872 0.03277 0.02695 -0.0143 0.1487 1.0000
15.000 1.5922 0.03447 0.02867 -0.0134 0.1452 1.0000
15.250 1.6037 0.03569 0.03000 -0.0129 0.1414 1.0000
15.500 1.6099 0.03739 0.03175 -0.0123 0.1376 1.0000
15.750 1.6099 0.03972 0.03408 -0.0116 0.1332 1.0000
16.000 1.6188 0.04130 0.03576 -0.0113 0.1293 1.0000
16.250 1.6210 0.04355 0.03807 -0.0109 0.1247 1.0000
16.500 1.6189 0.04631 0.04086 -0.0107 0.1203 1.0000
16.750 1.6214 0.04868 0.04331 -0.0106 0.1149 1.0000
17.000 1.6135 0.05226 0.04691 -0.0107 0.1097 1.0000
17.250 1.6116 0.05522 0.04995 -0.0108 0.1043 1.0000
17.500 1.5975 0.05971 0.05448 -0.0113 0.0985 1.0000
17.750 1.5877 0.06380 0.05863 -0.0119 0.0926 1.0000
18.000 1.5698 0.06899 0.06388 -0.0129 0.0883 1.0000
18.250 1.5535 0.07411 0.06907 -0.0140 0.0834 1.0000
18.750 1.5118 0.08595 0.08107 -0.0171 0.0770 1.0000
19.000 1.4921 0.09189 0.08710 -0.0189 0.0747 1.0000
19.250 1.4691 0.09842 0.09370 -0.0210 0.0727 1.0000
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