GOE 648 AIRFOIL (goe648-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 648 AIRFOIL (goe648-il) Reynolds number: 100,000 Max Cl/Cd: 43.21 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe648-il-100000.txt Download as CSV file: xf-goe648-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3364 0.09897 0.09439 -0.0272 1.0000 0.1685
-8.500 -0.4115 0.09866 0.09430 -0.0271 1.0000 0.1720
-8.250 -0.4711 0.09749 0.09329 -0.0256 1.0000 0.1723
-8.000 -0.3799 0.09303 0.08872 -0.0210 1.0000 0.1777
-7.750 -0.3893 0.09157 0.08732 -0.0183 1.0000 0.1816
-7.500 -0.4221 0.09021 0.08607 -0.0160 1.0000 0.1854
-7.250 -0.6084 0.05180 0.04599 -0.0391 0.9943 0.1000
-7.000 -0.5864 0.04690 0.04044 -0.0421 0.9864 0.1005
-6.750 -0.5521 0.04409 0.03772 -0.0451 0.9805 0.1029
-6.500 -0.5252 0.04121 0.03453 -0.0467 0.9720 0.1044
-6.250 -0.4944 0.03894 0.03190 -0.0486 0.9644 0.1077
-6.000 -0.4641 0.03644 0.02883 -0.0501 0.9562 0.1107
-5.750 -0.4353 0.03436 0.02625 -0.0510 0.9479 0.1138
-5.500 -0.3986 0.03320 0.02515 -0.0532 0.9406 0.1189
-5.250 -0.3684 0.03198 0.02360 -0.0538 0.9318 0.1237
-5.000 -0.3312 0.03066 0.02213 -0.0557 0.9246 0.1298
-4.750 -0.3001 0.02990 0.02126 -0.0564 0.9153 0.1370
-4.500 -0.2583 0.02875 0.02005 -0.0588 0.9076 0.1457
-4.250 -0.2256 0.02807 0.01919 -0.0594 0.8964 0.1555
-4.000 -0.1751 0.02688 0.01808 -0.0630 0.8893 0.1694
-3.750 -0.1442 0.02606 0.01735 -0.0632 0.8768 0.1814
-3.500 -0.0885 0.02485 0.01619 -0.0673 0.8711 0.2027
-3.250 -0.0615 0.02418 0.01562 -0.0667 0.8581 0.2209
-3.000 -0.0101 0.02296 0.01460 -0.0701 0.8537 0.2602
-2.750 0.0107 0.02226 0.01425 -0.0686 0.8415 0.3049
-2.500 0.0550 0.02093 0.01350 -0.0708 0.8367 0.4063
-2.250 0.0767 0.02047 0.01341 -0.0689 0.8249 0.4877
-2.000 0.1188 0.01969 0.01293 -0.0701 0.8190 0.5812
-1.750 0.1421 0.01939 0.01284 -0.0681 0.8072 0.6436
-1.500 0.1837 0.01876 0.01236 -0.0687 0.8006 0.7123
-1.250 0.2077 0.01854 0.01225 -0.0665 0.7879 0.7657
-1.000 0.2544 0.01791 0.01168 -0.0676 0.7809 0.8299
-0.750 0.2931 0.01772 0.01154 -0.0678 0.7671 0.8833
-0.500 0.3639 0.01747 0.01117 -0.0741 0.7540 0.9225
-0.250 0.4401 0.01720 0.01069 -0.0818 0.7382 0.9495
0.000 0.5145 0.01691 0.01019 -0.0898 0.7177 0.9704
0.250 0.5846 0.01657 0.00961 -0.0975 0.6944 0.9912
0.500 0.6246 0.01628 0.00907 -0.1001 0.6715 1.0000
0.750 0.6317 0.01620 0.00885 -0.0968 0.6488 1.0000
1.000 0.6420 0.01621 0.00867 -0.0937 0.6257 1.0000
1.250 0.6561 0.01631 0.00852 -0.0911 0.6030 1.0000
1.500 0.6723 0.01653 0.00848 -0.0889 0.5808 1.0000
1.750 0.6872 0.01682 0.00858 -0.0865 0.5587 1.0000
2.000 0.7048 0.01714 0.00870 -0.0845 0.5389 1.0000
2.250 0.7239 0.01749 0.00885 -0.0827 0.5217 1.0000
2.500 0.7447 0.01786 0.00901 -0.0813 0.5069 1.0000
2.750 0.7657 0.01823 0.00922 -0.0800 0.4933 1.0000
3.000 0.7850 0.01864 0.00954 -0.0783 0.4805 1.0000
3.250 0.8071 0.01906 0.00981 -0.0772 0.4697 1.0000
3.500 0.8292 0.01946 0.01010 -0.0761 0.4593 1.0000
3.750 0.8503 0.01992 0.01049 -0.0748 0.4497 1.0000
4.000 0.8742 0.02034 0.01079 -0.0740 0.4408 1.0000
4.250 0.8950 0.02084 0.01126 -0.0728 0.4323 1.0000
4.500 0.9187 0.02129 0.01161 -0.0720 0.4242 1.0000
4.750 0.9412 0.02184 0.01212 -0.0711 0.4167 1.0000
5.000 0.9628 0.02234 0.01260 -0.0700 0.4091 1.0000
5.250 0.9899 0.02291 0.01301 -0.0699 0.4025 1.0000
5.500 1.0073 0.02348 0.01370 -0.0681 0.3951 1.0000
5.750 1.0330 0.02402 0.01413 -0.0677 0.3885 1.0000
6.000 1.0546 0.02472 0.01484 -0.0668 0.3822 1.0000
6.250 1.0739 0.02535 0.01553 -0.0654 0.3755 1.0000
6.500 1.1030 0.02598 0.01600 -0.0657 0.3694 1.0000
6.750 1.1187 0.02676 0.01693 -0.0638 0.3632 1.0000
7.000 1.1386 0.02747 0.01769 -0.0626 0.3571 1.0000
7.250 1.1688 0.02822 0.01828 -0.0631 0.3515 1.0000
7.500 1.1813 0.02913 0.01939 -0.0608 0.3457 1.0000
7.750 1.1992 0.02991 0.02024 -0.0593 0.3397 1.0000
8.000 1.2286 0.03068 0.02089 -0.0598 0.3343 1.0000
8.250 1.2403 0.03178 0.02218 -0.0575 0.3292 1.0000
8.500 1.2538 0.03278 0.02332 -0.0555 0.3238 1.0000
8.750 1.2773 0.03357 0.02410 -0.0550 0.3187 1.0000
9.000 1.2990 0.03473 0.02526 -0.0544 0.3139 1.0000
9.250 1.3019 0.03597 0.02677 -0.0509 0.3088 1.0000
9.500 1.3174 0.03699 0.02787 -0.0494 0.3040 1.0000
9.750 1.3442 0.03790 0.02874 -0.0495 0.2998 1.0000
10.000 1.3540 0.03949 0.03047 -0.0474 0.2960 1.0000
10.250 1.3462 0.04122 0.03250 -0.0428 0.2919 1.0000
10.500 1.3534 0.04254 0.03394 -0.0404 0.2876 1.0000
10.750 1.3787 0.04335 0.03474 -0.0403 0.2835 1.0000
11.000 1.3987 0.04475 0.03614 -0.0398 0.2797 1.0000
11.250 1.3659 0.04733 0.03907 -0.0326 0.2769 1.0000
11.500 1.3286 0.05021 0.04221 -0.0255 0.2742 1.0000
11.750 1.2874 0.05402 0.04624 -0.0198 0.2716 1.0000
12.000 1.2458 0.05869 0.05109 -0.0158 0.2690 1.0000
12.250 1.1790 0.06679 0.05936 -0.0134 0.2664 1.0000
12.500 1.1317 0.07525 0.06792 -0.0136 0.2633 1.0000
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