GOE 7K AIRFOIL (goe07k-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 7K AIRFOIL (goe07k-il) Reynolds number: 200,000 Max Cl/Cd: 69.69 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe07k-il-200000.txt Download as CSV file: xf-goe07k-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 7K 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
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3871 0.09242 0.08914 -0.0613 0.9548 0.0414
-7.250 -0.3838 0.08866 0.08536 -0.0646 0.9515 0.0424
-7.000 -0.3928 0.08577 0.08248 -0.0640 0.9443 0.0429
-6.750 -0.3860 0.08147 0.07813 -0.0675 0.9404 0.0440
-6.500 -0.3853 0.07762 0.07422 -0.0690 0.9353 0.0458
-6.250 -0.3775 0.07298 0.06922 -0.0738 0.9282 0.0487
-5.500 -0.3669 0.06063 0.05662 -0.0711 0.9167 0.0513
-5.250 -0.3511 0.05782 0.05372 -0.0713 0.9145 0.0527
-5.000 -0.3304 0.05468 0.05040 -0.0723 0.9128 0.0553
-4.750 -0.3322 0.05276 0.04833 -0.0682 0.9067 0.0572
-4.500 -0.3139 0.05245 0.04721 -0.0657 0.9025 0.0621
-4.250 -0.3041 0.04613 0.04092 -0.0655 0.9011 0.0644
-4.000 -0.2818 0.04426 0.03904 -0.0658 0.8997 0.0681
-3.500 -0.2657 0.04108 0.03541 -0.0596 0.8917 0.0808
-3.250 -0.2473 0.03994 0.03402 -0.0581 0.8892 0.0871
-3.000 -0.2237 0.03403 0.02664 -0.0527 0.8876 0.0499
-2.750 -0.1996 0.03241 0.02499 -0.0527 0.8863 0.0537
-2.500 -0.1703 0.03119 0.02347 -0.0526 0.8851 0.0557
-2.250 -0.1656 0.03054 0.02262 -0.0481 0.8800 0.0565
-2.000 -0.1478 0.02991 0.02177 -0.0461 0.8772 0.0587
-1.750 -0.1239 0.02936 0.02096 -0.0452 0.8750 0.0633
-1.500 -0.0949 0.02838 0.01994 -0.0455 0.8733 0.0672
-1.250 -0.0630 0.02808 0.01956 -0.0463 0.8718 0.0743
-1.000 -0.0312 0.02747 0.01894 -0.0471 0.8707 0.0796
-0.750 -0.0354 0.02753 0.01901 -0.0414 0.8645 0.0825
-0.500 -0.0127 0.02747 0.01891 -0.0406 0.8615 0.0895
-0.250 0.0139 0.02714 0.01864 -0.0405 0.8594 0.0974
0.000 0.0473 0.02702 0.01850 -0.0417 0.8576 0.1071
0.250 0.2355 0.02548 0.01978 -0.0789 0.8655 1.0000
0.500 0.2595 0.02568 0.01985 -0.0784 0.8614 1.0000
0.750 0.2943 0.02572 0.01978 -0.0799 0.8588 1.0000
1.000 0.3350 0.02567 0.01963 -0.0824 0.8570 1.0000
1.250 0.3374 0.02613 0.02004 -0.0780 0.8484 1.0000
1.500 0.3698 0.02618 0.02003 -0.0790 0.8456 1.0000
1.750 0.4066 0.02617 0.01997 -0.0809 0.8437 1.0000
2.000 0.4457 0.02614 0.01991 -0.0831 0.8424 1.0000
2.250 0.4427 0.02677 0.02053 -0.0778 0.8326 1.0000
2.500 0.4781 0.02673 0.02048 -0.0794 0.8305 1.0000
2.750 0.5171 0.02661 0.02036 -0.0815 0.8290 1.0000
3.000 0.5187 0.02725 0.02100 -0.0772 0.8194 1.0000
3.250 0.5539 0.02715 0.02092 -0.0786 0.8170 1.0000
3.500 0.5919 0.02698 0.02079 -0.0805 0.8154 1.0000
3.750 0.5981 0.02752 0.02136 -0.0769 0.8057 1.0000
4.000 0.6340 0.02733 0.02123 -0.0784 0.8032 1.0000
4.250 0.6803 0.02659 0.02057 -0.0813 0.8014 1.0000
4.500 0.6947 0.02667 0.02069 -0.0788 0.7910 1.0000
4.750 0.7674 0.02400 0.01815 -0.0851 0.7884 1.0000
5.000 0.8306 0.02166 0.01595 -0.0900 0.7862 1.0000
5.500 0.9131 0.01840 0.01294 -0.0923 0.7693 1.0000
5.750 0.9536 0.01653 0.01117 -0.0929 0.7520 1.0000
6.000 0.9849 0.01533 0.01004 -0.0922 0.7244 1.0000
6.250 1.0109 0.01473 0.00943 -0.0908 0.6852 1.0000
6.500 1.0244 0.01470 0.00864 -0.0867 0.5361 1.0000
6.750 1.0053 0.01615 0.00943 -0.0776 0.4392 1.0000
7.000 0.9855 0.01787 0.01056 -0.0691 0.3349 1.0000
7.250 0.9657 0.01997 0.01193 -0.0613 0.2177 1.0000
7.500 0.9545 0.02204 0.01330 -0.0554 0.1137 1.0000
7.750 0.9549 0.02361 0.01462 -0.0512 0.0809 1.0000
8.000 0.9597 0.02497 0.01594 -0.0477 0.0663 1.0000
8.250 0.9643 0.02640 0.01738 -0.0443 0.0584 1.0000
8.500 0.9758 0.02742 0.01843 -0.0420 0.0522 1.0000
8.750 0.9848 0.02888 0.01987 -0.0393 0.0471 1.0000
9.000 1.0008 0.02983 0.02091 -0.0376 0.0438 1.0000
9.250 1.0183 0.03089 0.02199 -0.0362 0.0408 1.0000
9.500 1.0508 0.03262 0.02369 -0.0369 0.0371 1.0000
9.750 1.0707 0.03350 0.02473 -0.0357 0.0349 1.0000
10.000 1.1059 0.03503 0.02642 -0.0367 0.0330 1.0000
10.250 1.1446 0.03701 0.02859 -0.0383 0.0317 1.0000
10.500 1.1686 0.03875 0.03042 -0.0382 0.0298 1.0000
10.750 1.2172 0.04457 0.03669 -0.0422 0.0282 1.0000
11.000 1.2406 0.04958 0.04213 -0.0422 0.0284 1.0000
11.250 1.2441 0.05211 0.04494 -0.0386 0.0285 1.0000
11.500 1.2441 0.05357 0.04665 -0.0343 0.0289 1.0000
11.750 1.2082 0.05913 0.05316 -0.0240 0.0342 1.0000
12.000 1.1003 0.05139 0.04582 -0.0082 0.0326 1.0000
12.250 1.0787 0.05603 0.05076 -0.0035 0.0340 1.0000
12.500 1.0561 0.06072 0.05567 0.0006 0.0351 1.0000
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Polar data table (+)
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