GOE 617 AIRFOIL (goe617-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 617 AIRFOIL (goe617-il) Reynolds number: 50,000 Max Cl/Cd: 31.4 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe617-il-50000-n5.txt Download as CSV file: xf-goe617-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 617 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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4589 0.10144 0.09361 -0.0458 1.0000 0.0819
-11.000 -0.4696 0.09588 0.08811 -0.0481 1.0000 0.0818
-10.750 -0.4870 0.08911 0.08140 -0.0516 1.0000 0.0820
-10.500 -0.5148 0.08094 0.07330 -0.0565 1.0000 0.0816
-10.250 -0.5502 0.07442 0.06680 -0.0588 1.0000 0.0808
-10.000 -0.5860 0.06988 0.06224 -0.0576 1.0000 0.0803
-9.750 -0.6191 0.06675 0.05909 -0.0535 1.0000 0.0801
-9.500 -0.6465 0.06366 0.05591 -0.0493 1.0000 0.0803
-9.250 -0.6690 0.06078 0.05289 -0.0450 1.0000 0.0808
-9.000 -0.6881 0.05802 0.04994 -0.0405 1.0000 0.0815
-8.750 -0.7037 0.05533 0.04700 -0.0359 1.0000 0.0822
-8.500 -0.7161 0.05267 0.04404 -0.0315 1.0000 0.0831
-8.250 -0.7247 0.05006 0.04107 -0.0271 1.0000 0.0840
-8.000 -0.7297 0.04754 0.03815 -0.0230 1.0000 0.0849
-7.750 -0.7286 0.04530 0.03561 -0.0196 1.0000 0.0860
-7.500 -0.7200 0.04373 0.03401 -0.0172 1.0000 0.0879
-7.250 -0.7116 0.04235 0.03253 -0.0146 1.0000 0.0904
-7.000 -0.7033 0.04080 0.03074 -0.0120 1.0000 0.0930
-6.750 -0.6940 0.03910 0.02872 -0.0093 1.0000 0.0954
-6.500 -0.6826 0.03741 0.02663 -0.0069 1.0000 0.0977
-6.250 -0.6688 0.03607 0.02516 -0.0050 1.0000 0.1004
-6.000 -0.6511 0.03508 0.02416 -0.0038 0.9989 0.1042
-5.750 -0.6164 0.03381 0.02257 -0.0056 0.9922 0.1101
-5.500 -0.5812 0.03263 0.02129 -0.0075 0.9855 0.1155
-5.250 -0.5468 0.03175 0.02031 -0.0092 0.9782 0.1231
-5.000 -0.5095 0.03090 0.01939 -0.0114 0.9717 0.1311
-4.750 -0.4757 0.03020 0.01852 -0.0127 0.9635 0.1413
-4.500 -0.4391 0.02954 0.01791 -0.0148 0.9564 0.1526
-4.250 -0.4051 0.02891 0.01726 -0.0163 0.9480 0.1658
-4.000 -0.3687 0.02826 0.01660 -0.0182 0.9404 0.1831
-3.750 -0.3347 0.02754 0.01590 -0.0197 0.9319 0.2069
-3.500 -0.3027 0.02665 0.01524 -0.0210 0.9237 0.2424
-3.250 -0.2740 0.02562 0.01475 -0.0218 0.9149 0.3090
-3.000 -0.2518 0.02477 0.01451 -0.0210 0.9051 0.4271
-2.750 -0.2219 0.02403 0.01448 -0.0208 0.8973 0.5730
-2.500 -0.1472 0.02412 0.01523 -0.0271 0.8956 0.7568
-2.250 -0.0804 0.02491 0.01597 -0.0323 0.8902 0.8555
-2.000 -0.0127 0.02556 0.01637 -0.0383 0.8848 0.9038
-1.750 0.0621 0.02579 0.01634 -0.0465 0.8808 0.9340
-1.500 0.1276 0.02579 0.01614 -0.0536 0.8742 0.9583
-1.250 0.1981 0.02548 0.01565 -0.0620 0.8668 0.9776
-1.000 0.2661 0.02494 0.01495 -0.0701 0.8604 0.9920
-0.750 0.3110 0.02457 0.01446 -0.0740 0.8482 1.0000
-0.500 0.3346 0.02441 0.01420 -0.0737 0.8340 1.0000
-0.250 0.3586 0.02427 0.01396 -0.0733 0.8203 1.0000
0.000 0.3841 0.02411 0.01371 -0.0730 0.8073 1.0000
0.250 0.4111 0.02393 0.01345 -0.0729 0.7950 1.0000
0.500 0.4304 0.02394 0.01339 -0.0715 0.7805 1.0000
0.750 0.4502 0.02396 0.01336 -0.0701 0.7665 1.0000
1.000 0.4710 0.02398 0.01332 -0.0689 0.7533 1.0000
1.250 0.4941 0.02395 0.01323 -0.0680 0.7412 1.0000
1.500 0.5178 0.02392 0.01315 -0.0671 0.7295 1.0000
1.750 0.5354 0.02407 0.01328 -0.0653 0.7161 1.0000
2.000 0.5549 0.02420 0.01338 -0.0638 0.7037 1.0000
2.250 0.5780 0.02424 0.01339 -0.0628 0.6927 1.0000
2.500 0.5998 0.02433 0.01346 -0.0615 0.6812 1.0000
2.750 0.6172 0.02459 0.01371 -0.0597 0.6688 1.0000
3.000 0.6383 0.02476 0.01388 -0.0584 0.6578 1.0000
3.250 0.6624 0.02484 0.01395 -0.0574 0.6475 1.0000
3.500 0.6784 0.02521 0.01434 -0.0554 0.6352 1.0000
3.750 0.6983 0.02546 0.01461 -0.0539 0.6240 1.0000
4.000 0.7237 0.02549 0.01461 -0.0530 0.6129 1.0000
4.250 0.7395 0.02582 0.01498 -0.0508 0.5993 1.0000
4.500 0.7561 0.02608 0.01525 -0.0486 0.5852 1.0000
4.750 0.7735 0.02628 0.01546 -0.0464 0.5705 1.0000
5.000 0.7909 0.02647 0.01565 -0.0442 0.5556 1.0000
5.250 0.8081 0.02665 0.01583 -0.0419 0.5405 1.0000
5.500 0.8255 0.02685 0.01605 -0.0398 0.5260 1.0000
5.750 0.8450 0.02704 0.01623 -0.0380 0.5129 1.0000
6.000 0.8576 0.02746 0.01672 -0.0353 0.4988 1.0000
6.250 0.8706 0.02784 0.01716 -0.0326 0.4844 1.0000
6.500 0.8836 0.02821 0.01760 -0.0299 0.4697 1.0000
6.750 0.8960 0.02855 0.01798 -0.0270 0.4541 1.0000
7.000 0.9068 0.02888 0.01831 -0.0239 0.4368 1.0000
7.250 0.9166 0.02920 0.01863 -0.0206 0.4186 1.0000
7.500 0.9259 0.02953 0.01894 -0.0173 0.3997 1.0000
7.750 0.9311 0.03003 0.01943 -0.0135 0.3800 1.0000
8.000 0.9359 0.03061 0.02000 -0.0098 0.3601 1.0000
8.250 0.9396 0.03122 0.02057 -0.0059 0.3404 1.0000
8.500 0.9419 0.03189 0.02117 -0.0019 0.3214 1.0000
8.750 0.9443 0.03266 0.02187 0.0019 0.3028 1.0000
9.000 0.9469 0.03357 0.02271 0.0054 0.2850 1.0000
9.250 0.9494 0.03461 0.02372 0.0085 0.2679 1.0000
9.500 0.9529 0.03573 0.02478 0.0114 0.2525 1.0000
9.750 0.9570 0.03691 0.02590 0.0140 0.2389 1.0000
10.000 0.9621 0.03818 0.02714 0.0163 0.2267 1.0000
10.250 0.9678 0.03953 0.02849 0.0184 0.2156 1.0000
10.500 0.9748 0.04088 0.02983 0.0203 0.2061 1.0000
10.750 0.9830 0.04220 0.03109 0.0220 0.1973 1.0000
11.000 0.9914 0.04370 0.03266 0.0236 0.1892 1.0000
11.250 1.0051 0.04492 0.03381 0.0248 0.1823 1.0000
11.500 1.0154 0.04651 0.03555 0.0261 0.1758 1.0000
11.750 1.0278 0.04794 0.03705 0.0273 0.1696 1.0000
12.000 1.0449 0.04924 0.03833 0.0282 0.1639 1.0000
12.250 1.0491 0.05133 0.04067 0.0294 0.1591 1.0000
12.500 1.0602 0.05308 0.04255 0.0304 0.1548 1.0000
12.750 1.0871 0.05408 0.04350 0.0308 0.1502 1.0000
13.000 1.0817 0.05685 0.04657 0.0322 0.1472 1.0000
13.250 1.0743 0.05990 0.04989 0.0333 0.1441 1.0000
13.500 1.0697 0.06289 0.05309 0.0341 0.1412 1.0000
13.750 1.0723 0.06534 0.05566 0.0347 0.1379 1.0000
14.000 1.0985 0.06634 0.05662 0.0353 0.1346 1.0000
14.250 1.0717 0.07135 0.06195 0.0355 0.1335 1.0000
14.500 1.0364 0.07785 0.06874 0.0343 0.1325 1.0000
14.750 0.9846 0.08747 0.07862 0.0310 0.1319 1.0000
15.000 0.8406 0.11649 0.10776 0.0156 0.1316 1.0000
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