GOE 6K AIRFOIL (goe06k-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 6K AIRFOIL (goe06k-il) Reynolds number: 200,000 Max Cl/Cd: 74.36 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe06k-il-200000.txt Download as CSV file: xf-goe06k-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 6K 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4897 0.09762 0.09432 -0.0255 1.0000 0.0322
-7.750 -0.5025 0.09564 0.09240 -0.0239 1.0000 0.0322
-7.500 -0.5178 0.09374 0.09056 -0.0235 1.0000 0.0325
-7.250 -0.5237 0.09084 0.08767 -0.0243 1.0000 0.0326
-7.000 -0.5267 0.08767 0.08448 -0.0264 1.0000 0.0329
-6.750 -0.5267 0.08439 0.08116 -0.0273 1.0000 0.0330
-6.500 -0.5246 0.08106 0.07775 -0.0278 1.0000 0.0331
-6.250 -0.5213 0.07757 0.07417 -0.0281 1.0000 0.0332
-6.000 -0.5167 0.07408 0.07056 -0.0279 1.0000 0.0333
-5.750 -0.5227 0.06699 0.06354 -0.0272 1.0000 0.0342
-5.500 -0.5107 0.06324 0.05980 -0.0277 0.9982 0.0353
-5.250 -0.4885 0.05952 0.05599 -0.0303 0.9951 0.0372
-5.000 -0.4644 0.05548 0.05178 -0.0333 0.9911 0.0396
-4.750 -0.4239 0.05287 0.04851 -0.0371 0.9867 0.0454
-4.250 -0.3894 0.04338 0.03886 -0.0393 0.9809 0.0500
-4.000 -0.3656 0.04057 0.03581 -0.0398 0.9772 0.0538
-3.750 -0.3348 0.03771 0.03221 -0.0405 0.9739 0.0603
-3.500 -0.3090 0.03466 0.02916 -0.0417 0.9722 0.0633
-3.250 -0.2890 0.03288 0.02713 -0.0404 0.9681 0.0692
-3.000 -0.2663 0.03065 0.02462 -0.0400 0.9649 0.0779
-2.750 -0.2396 0.02912 0.02287 -0.0404 0.9621 0.0941
-2.500 -0.1996 0.02518 0.01772 -0.0378 0.9608 0.0447
-2.250 -0.1673 0.02323 0.01541 -0.0383 0.9594 0.0441
-2.000 -0.1479 0.02229 0.01423 -0.0363 0.9548 0.0452
-1.750 -0.1219 0.02085 0.01271 -0.0361 0.9521 0.0503
-1.500 -0.0917 0.02018 0.01195 -0.0364 0.9496 0.0555
-1.250 -0.0603 0.01941 0.01113 -0.0371 0.9477 0.0624
-1.000 -0.0378 0.01910 0.01080 -0.0362 0.9437 0.0727
-0.750 -0.0161 0.01859 0.01035 -0.0352 0.9397 0.0849
-0.500 0.0971 0.01584 0.01047 -0.0547 0.9499 1.0000
-0.250 0.1312 0.01609 0.01053 -0.0563 0.9477 1.0000
0.000 0.1536 0.01625 0.01058 -0.0555 0.9427 1.0000
0.250 0.1805 0.01643 0.01067 -0.0557 0.9386 1.0000
0.500 0.2136 0.01664 0.01080 -0.0572 0.9359 1.0000
0.750 0.2513 0.01686 0.01094 -0.0595 0.9338 1.0000
1.000 0.2715 0.01689 0.01093 -0.0582 0.9255 1.0000
1.250 0.3130 0.01692 0.01093 -0.0611 0.9220 1.0000
1.500 0.3367 0.01704 0.01106 -0.0605 0.9155 1.0000
1.750 0.3682 0.01714 0.01117 -0.0615 0.9111 1.0000
2.000 0.4066 0.01720 0.01125 -0.0638 0.9084 1.0000
2.250 0.4269 0.01738 0.01146 -0.0625 0.9013 1.0000
2.500 0.4690 0.01717 0.01131 -0.0653 0.8963 1.0000
2.750 0.5064 0.01684 0.01108 -0.0668 0.8882 1.0000
3.000 0.5828 0.01520 0.00961 -0.0751 0.8811 1.0000
3.250 0.6552 0.01312 0.00776 -0.0821 0.8685 1.0000
3.500 0.7296 0.01098 0.00581 -0.0893 0.8384 1.0000
3.750 0.7607 0.01023 0.00506 -0.0883 0.7783 1.0000
4.000 0.7739 0.01130 0.00458 -0.0837 0.4700 1.0000
4.250 0.7521 0.01328 0.00534 -0.0738 0.2368 1.0000
4.500 0.7477 0.01513 0.00626 -0.0678 0.0885 1.0000
4.750 0.7571 0.01623 0.00728 -0.0640 0.0644 1.0000
5.000 0.7677 0.01735 0.00838 -0.0605 0.0539 1.0000
5.250 0.7829 0.01828 0.00928 -0.0581 0.0456 1.0000
5.500 0.8034 0.01965 0.01071 -0.0566 0.0413 1.0000
5.750 0.8304 0.02103 0.01216 -0.0563 0.0377 1.0000
6.000 0.8681 0.02384 0.01498 -0.0587 0.0323 1.0000
6.250 0.8978 0.02547 0.01687 -0.0587 0.0313 1.0000
6.500 0.9295 0.02820 0.01992 -0.0589 0.0310 1.0000
6.750 0.9561 0.03216 0.02427 -0.0583 0.0317 1.0000
7.000 0.9797 0.03482 0.02718 -0.0569 0.0332 1.0000
7.250 0.9922 0.03896 0.03170 -0.0541 0.0328 1.0000
8.250 1.0047 0.05468 0.04958 -0.0330 0.0519 1.0000
8.500 1.0034 0.05742 0.05255 -0.0289 0.0493 1.0000
8.750 1.0020 0.06030 0.05561 -0.0254 0.0479 1.0000
9.000 1.0012 0.06330 0.05872 -0.0223 0.0468 1.0000
9.250 1.0031 0.06699 0.06244 -0.0201 0.0456 1.0000
14.000 0.6391 0.14753 0.14412 -0.0281 0.0420 1.0000
14.250 0.6353 0.15089 0.14748 -0.0306 0.0404 1.0000
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