GOE 12K AIRFOIL (goe12k-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 12K AIRFOIL (goe12k-il) Reynolds number: 50,000 Max Cl/Cd: 27.25 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe12k-il-50000-n5.txt Download as CSV file: xf-goe12k-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 12K AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4234 0.12087 0.11467 -0.0235 1.0000 0.1379
-8.500 -0.5046 0.11539 0.10863 -0.0265 1.0000 0.0904
-8.250 -0.5131 0.11227 0.10557 -0.0258 1.0000 0.0895
-8.000 -0.5246 0.10914 0.10249 -0.0250 1.0000 0.0885
-7.750 -0.5396 0.10612 0.09954 -0.0240 1.0000 0.0878
-7.500 -0.5567 0.10297 0.09644 -0.0229 1.0000 0.0864
-7.250 -0.5701 0.09907 0.09259 -0.0230 1.0000 0.0852
-7.000 -0.5729 0.09349 0.08696 -0.0270 0.9967 0.0837
-6.750 -0.5745 0.08724 0.08059 -0.0312 0.9930 0.0824
-6.500 -0.5679 0.08343 0.07667 -0.0324 0.9899 0.0841
-6.250 -0.5598 0.07912 0.07220 -0.0345 0.9868 0.0861
-6.000 -0.5544 0.07443 0.06731 -0.0358 0.9835 0.0870
-5.750 -0.5469 0.06983 0.06245 -0.0369 0.9807 0.0878
-5.500 -0.5360 0.06533 0.05758 -0.0381 0.9781 0.0902
-5.250 -0.5261 0.06096 0.05273 -0.0382 0.9751 0.0919
-5.000 -0.5137 0.05709 0.04836 -0.0379 0.9721 0.0928
-4.750 -0.4980 0.05443 0.04539 -0.0374 0.9697 0.0957
-4.250 -0.4652 0.05043 0.04085 -0.0356 0.9656 0.0995
-4.000 -0.4488 0.04835 0.03839 -0.0343 0.9633 0.1011
-3.750 -0.4299 0.04664 0.03626 -0.0334 0.9609 0.1041
-3.500 -0.4088 0.04493 0.03399 -0.0326 0.9586 0.1069
-3.250 -0.3869 0.04346 0.03205 -0.0318 0.9567 0.1078
-3.000 -0.3682 0.04214 0.03031 -0.0303 0.9545 0.1087
-2.750 -0.3484 0.04103 0.02904 -0.0292 0.9527 0.1100
-2.500 -0.3271 0.04031 0.02821 -0.0285 0.9506 0.1129
-2.250 -0.3038 0.03976 0.02747 -0.0280 0.9484 0.1168
-2.000 -0.2777 0.03916 0.02658 -0.0278 0.9464 0.1199
-1.750 -0.2524 0.03858 0.02572 -0.0275 0.9446 0.1215
-1.500 -0.2296 0.03803 0.02494 -0.0268 0.9427 0.1233
-1.250 -0.2056 0.03756 0.02443 -0.0264 0.9408 0.1255
-1.000 -0.1778 0.03726 0.02406 -0.0268 0.9386 0.1288
-0.750 -0.1460 0.03713 0.02379 -0.0279 0.9366 0.1330
-0.500 -0.1158 0.03715 0.02361 -0.0287 0.9348 0.1385
-0.250 -0.0865 0.03717 0.02368 -0.0296 0.9333 0.1473
0.000 -0.0608 0.03713 0.02359 -0.0296 0.9310 0.1578
0.250 -0.0363 0.03703 0.02348 -0.0295 0.9280 0.1691
0.500 -0.0095 0.03699 0.02350 -0.0298 0.9256 0.1872
0.750 0.0214 0.03679 0.02371 -0.0312 0.9234 0.2415
1.250 0.1482 0.03663 0.02545 -0.0477 0.9219 1.0000
1.500 0.1772 0.03718 0.02582 -0.0484 0.9172 1.0000
1.750 0.2013 0.03749 0.02599 -0.0482 0.9094 1.0000
2.000 0.2358 0.03795 0.02631 -0.0497 0.9014 1.0000
2.250 0.2680 0.03822 0.02649 -0.0507 0.8911 1.0000
2.500 0.2958 0.03845 0.02664 -0.0509 0.8809 1.0000
2.750 0.3299 0.03889 0.02703 -0.0523 0.8742 1.0000
3.000 0.3509 0.03922 0.02733 -0.0515 0.8663 1.0000
3.250 0.3810 0.03964 0.02774 -0.0523 0.8596 1.0000
3.500 0.4047 0.03996 0.02808 -0.0519 0.8512 1.0000
3.750 0.4353 0.04031 0.02845 -0.0526 0.8438 1.0000
4.000 0.4576 0.04057 0.02876 -0.0520 0.8340 1.0000
4.250 0.4930 0.04084 0.02910 -0.0534 0.8270 1.0000
4.500 0.5136 0.04101 0.02934 -0.0524 0.8154 1.0000
4.750 0.5385 0.04117 0.02959 -0.0520 0.8045 1.0000
5.000 0.5737 0.04120 0.02974 -0.0532 0.7961 1.0000
5.250 0.5989 0.04120 0.02987 -0.0527 0.7836 1.0000
5.500 0.6229 0.04117 0.02998 -0.0520 0.7700 1.0000
5.750 0.6486 0.04102 0.02998 -0.0514 0.7558 1.0000
6.000 0.6761 0.04066 0.02978 -0.0508 0.7404 1.0000
6.250 0.7071 0.03990 0.02922 -0.0503 0.7233 1.0000
6.500 0.7264 0.03918 0.02865 -0.0478 0.6975 1.0000
6.750 0.7484 0.03806 0.02767 -0.0452 0.6672 1.0000
7.000 0.7647 0.03727 0.02702 -0.0420 0.6309 1.0000
7.250 0.7810 0.03676 0.02661 -0.0390 0.5886 1.0000
7.500 0.8197 0.03491 0.02479 -0.0379 0.5414 1.0000
7.750 0.8762 0.03252 0.02195 -0.0387 0.4683 1.0000
8.000 0.8971 0.03292 0.02199 -0.0368 0.4092 1.0000
8.250 0.9059 0.03401 0.02290 -0.0339 0.3521 1.0000
8.500 0.9109 0.03536 0.02395 -0.0308 0.2885 1.0000
8.750 0.9161 0.03687 0.02505 -0.0279 0.2396 1.0000
9.000 0.9254 0.03833 0.02623 -0.0257 0.2077 1.0000
9.250 0.9390 0.03964 0.02742 -0.0240 0.1875 1.0000
9.500 0.9564 0.04082 0.02854 -0.0227 0.1727 1.0000
9.750 0.9768 0.04191 0.02964 -0.0217 0.1597 1.0000
10.000 0.9987 0.04297 0.03072 -0.0210 0.1479 1.0000
10.250 1.0285 0.04396 0.03167 -0.0212 0.1380 1.0000
10.500 1.0537 0.04507 0.03303 -0.0208 0.1275 1.0000
10.750 1.0787 0.04638 0.03443 -0.0205 0.1180 1.0000
11.000 1.0995 0.04777 0.03587 -0.0199 0.1093 1.0000
11.250 1.1185 0.04944 0.03784 -0.0190 0.1009 1.0000
11.500 1.1394 0.05110 0.03939 -0.0185 0.0935 1.0000
11.750 1.1489 0.05314 0.04188 -0.0165 0.0870 1.0000
12.000 1.1623 0.05493 0.04368 -0.0153 0.0814 1.0000
12.250 1.1692 0.05743 0.04655 -0.0132 0.0765 1.0000
12.500 1.1739 0.05978 0.04916 -0.0111 0.0722 1.0000
12.750 1.1864 0.06187 0.05124 -0.0101 0.0687 1.0000
13.000 1.1767 0.06508 0.05494 -0.0068 0.0662 1.0000
13.250 1.1682 0.06837 0.05861 -0.0041 0.0640 1.0000
13.500 1.1593 0.07164 0.06217 -0.0017 0.0620 1.0000
13.750 1.1515 0.07474 0.06546 0.0003 0.0602 1.0000
14.000 1.1484 0.07755 0.06836 0.0018 0.0585 1.0000
14.250 1.1375 0.08127 0.07223 0.0032 0.0574 1.0000
14.500 1.1139 0.08610 0.07738 0.0045 0.0571 1.0000
14.750 1.0866 0.09167 0.08324 0.0048 0.0568 1.0000
15.000 1.0601 0.09773 0.08954 0.0041 0.0568 1.0000
15.250 1.0318 0.10471 0.09673 0.0020 0.0570 1.0000
15.500 1.0053 0.11235 0.10452 -0.0011 0.0573 1.0000
15.750 0.9765 0.12151 0.11380 -0.0059 0.0576 1.0000
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Polar data table (+)
Polar graphs
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