GOE 518 AIRFOIL (goe518-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 518 AIRFOIL (goe518-il) Reynolds number: 500,000 Max Cl/Cd: 64.47 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe518-il-500000.txt Download as CSV file: xf-goe518-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 518 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 0.1280 0.10125 0.09865 -0.1268 0.9561 0.0314
-11.500 0.1077 0.09548 0.09289 -0.1319 0.9488 0.0336
-11.250 0.1218 0.09183 0.08923 -0.1339 0.9465 0.0338
-11.000 0.1438 0.08945 0.08686 -0.1354 0.9448 0.0340
-10.750 0.1628 0.08651 0.08391 -0.1383 0.9432 0.0343
-10.500 0.1837 0.08367 0.08107 -0.1415 0.9417 0.0349
-10.250 0.1935 0.08096 0.07835 -0.1432 0.9367 0.0354
-10.000 0.2038 0.07791 0.07531 -0.1456 0.9312 0.0363
-9.750 0.2020 0.06897 0.06633 -0.1581 0.9268 0.0384
-9.500 0.2266 0.06682 0.06416 -0.1607 0.9233 0.0387
-9.250 0.2330 0.06502 0.06237 -0.1603 0.9144 0.0390
-9.000 0.2554 0.06211 0.05943 -0.1647 0.9097 0.0397
-8.750 0.2570 0.05957 0.05689 -0.1656 0.8994 0.0405
-8.500 0.2594 0.05494 0.05221 -0.1719 0.8897 0.0414
-8.250 0.1635 0.04500 0.04186 -0.1694 0.8683 0.0433
-8.000 0.1784 0.04348 0.04032 -0.1690 0.8607 0.0436
-7.750 0.1829 0.04230 0.03911 -0.1664 0.8512 0.0438
-7.500 0.1937 0.04073 0.03745 -0.1654 0.8425 0.0441
-7.250 0.1957 0.03953 0.03619 -0.1621 0.8315 0.0445
-7.000 0.1655 0.03607 0.03208 -0.1544 0.8202 0.0485
-6.750 0.1699 0.03328 0.02922 -0.1518 0.8100 0.0490
-6.500 0.1822 0.03216 0.02809 -0.1496 0.7993 0.0494
-6.250 0.1973 0.03119 0.02705 -0.1479 0.7882 0.0498
-6.000 0.2061 0.03038 0.02619 -0.1448 0.7752 0.0504
-5.750 0.1928 0.02842 0.02362 -0.1371 0.7622 0.0551
-5.500 0.2062 0.02702 0.02222 -0.1349 0.7477 0.0555
-5.250 0.2176 0.02615 0.02130 -0.1320 0.7312 0.0560
-5.000 0.2272 0.02546 0.02050 -0.1286 0.7125 0.0566
-4.750 0.2342 0.02478 0.01968 -0.1245 0.6920 0.0576
-4.500 0.2289 0.02368 0.01811 -0.1176 0.6743 0.0624
-4.250 0.2354 0.02292 0.01726 -0.1135 0.6566 0.0629
-4.000 0.2440 0.02237 0.01662 -0.1097 0.6406 0.0637
-3.750 0.2383 0.01691 0.00984 -0.1007 0.6304 0.0434
-3.500 0.2523 0.01676 0.00954 -0.0975 0.6166 0.0432
-3.250 0.2683 0.01609 0.00875 -0.0950 0.6041 0.0429
-3.000 0.2835 0.01563 0.00814 -0.0923 0.5915 0.0429
-2.750 0.2999 0.01526 0.00768 -0.0898 0.5792 0.0429
-2.500 0.3161 0.01496 0.00727 -0.0873 0.5669 0.0430
-2.250 0.3312 0.01476 0.00694 -0.0846 0.5540 0.0431
-2.000 0.3480 0.01440 0.00652 -0.0822 0.5405 0.0433
-1.750 0.3636 0.01413 0.00620 -0.0797 0.5270 0.0437
-1.500 0.3779 0.01400 0.00601 -0.0769 0.5128 0.0440
-1.250 0.3915 0.01395 0.00590 -0.0740 0.4983 0.0448
-1.000 0.4058 0.01394 0.00583 -0.0713 0.4837 0.0456
-0.750 0.4211 0.01393 0.00575 -0.0687 0.4706 0.0463
-0.500 0.4356 0.01396 0.00569 -0.0660 0.4576 0.0470
-0.250 0.4500 0.01400 0.00565 -0.0634 0.4463 0.0474
0.000 0.4669 0.01402 0.00562 -0.0612 0.4361 0.0482
0.250 0.4817 0.01414 0.00565 -0.0586 0.4267 0.0487
0.500 0.4987 0.01404 0.00556 -0.0565 0.4185 0.0499
0.750 0.5147 0.01413 0.00559 -0.0542 0.4110 0.0511
1.000 0.5330 0.01419 0.00563 -0.0524 0.4043 0.0528
1.250 0.5511 0.01430 0.00569 -0.0505 0.3980 0.0546
1.500 0.5673 0.01441 0.00576 -0.0484 0.3921 0.0585
1.750 0.5871 0.01448 0.00583 -0.0469 0.3873 0.0629
2.000 0.6050 0.01446 0.00598 -0.0450 0.3822 0.1059
2.250 0.6179 0.01421 0.00619 -0.0424 0.3777 0.2795
2.500 0.8985 0.01406 0.00769 -0.0965 0.3641 1.0000
2.750 0.9115 0.01428 0.00785 -0.0938 0.3609 1.0000
3.000 0.9246 0.01455 0.00804 -0.0912 0.3575 1.0000
3.250 0.9401 0.01477 0.00822 -0.0891 0.3548 1.0000
3.500 0.9564 0.01494 0.00839 -0.0871 0.3524 1.0000
3.750 0.9724 0.01514 0.00857 -0.0850 0.3500 1.0000
4.000 0.9887 0.01536 0.00876 -0.0831 0.3476 1.0000
4.250 1.0049 0.01561 0.00897 -0.0811 0.3452 1.0000
4.500 1.0213 0.01588 0.00919 -0.0792 0.3428 1.0000
4.750 1.0383 0.01619 0.00944 -0.0775 0.3402 1.0000
5.000 1.0568 0.01648 0.00969 -0.0761 0.3379 1.0000
5.250 1.0738 0.01671 0.00994 -0.0744 0.3361 1.0000
5.500 1.0918 0.01696 0.01019 -0.0728 0.3343 1.0000
5.750 1.1095 0.01722 0.01045 -0.0713 0.3322 1.0000
6.000 1.1276 0.01749 0.01071 -0.0699 0.3304 1.0000
6.250 1.1455 0.01779 0.01100 -0.0685 0.3287 1.0000
6.500 1.1635 0.01811 0.01129 -0.0671 0.3268 1.0000
6.750 1.1823 0.01844 0.01159 -0.0659 0.3250 1.0000
7.000 1.2035 0.01878 0.01189 -0.0651 0.3228 1.0000
7.250 1.2250 0.01910 0.01220 -0.0644 0.3211 1.0000
7.500 1.2431 0.01940 0.01254 -0.0632 0.3200 1.0000
7.750 1.2609 0.01973 0.01289 -0.0619 0.3187 1.0000
8.000 1.2786 0.02007 0.01326 -0.0606 0.3172 1.0000
8.250 1.2963 0.02042 0.01363 -0.0594 0.3156 1.0000
8.500 1.3133 0.02079 0.01401 -0.0581 0.3136 1.0000
8.750 1.3315 0.02115 0.01439 -0.0570 0.3121 1.0000
9.000 1.3485 0.02156 0.01479 -0.0558 0.3102 1.0000
9.250 1.3665 0.02197 0.01519 -0.0548 0.3082 1.0000
9.500 1.3893 0.02234 0.01551 -0.0545 0.3060 1.0000
9.750 1.4108 0.02272 0.01591 -0.0540 0.3045 1.0000
10.000 1.4261 0.02317 0.01643 -0.0527 0.3035 1.0000
10.250 1.4419 0.02363 0.01695 -0.0515 0.3023 1.0000
10.500 1.4576 0.02412 0.01748 -0.0502 0.3009 1.0000
10.750 1.4723 0.02463 0.01805 -0.0490 0.2991 1.0000
11.000 1.4871 0.02515 0.01860 -0.0477 0.2972 1.0000
11.250 1.5039 0.02564 0.01913 -0.0468 0.2958 1.0000
11.500 1.5197 0.02617 0.01968 -0.0458 0.2942 1.0000
11.750 1.5357 0.02671 0.02023 -0.0448 0.2925 1.0000
12.000 1.5556 0.02717 0.02067 -0.0444 0.2905 1.0000
12.250 1.5756 0.02765 0.02116 -0.0440 0.2884 1.0000
12.500 1.5854 0.02843 0.02204 -0.0424 0.2872 1.0000
12.750 1.5962 0.02921 0.02291 -0.0410 0.2856 1.0000
13.000 1.6063 0.03004 0.02381 -0.0396 0.2837 1.0000
13.250 1.6183 0.03082 0.02465 -0.0385 0.2817 1.0000
13.500 1.6300 0.03163 0.02551 -0.0374 0.2798 1.0000
13.750 1.6408 0.03251 0.02642 -0.0362 0.2777 1.0000
14.000 1.6537 0.03330 0.02721 -0.0353 0.2750 1.0000
14.250 1.6716 0.03388 0.02780 -0.0349 0.2729 1.0000
14.500 1.6769 0.03516 0.02921 -0.0335 0.2714 1.0000
14.750 1.6835 0.03643 0.03058 -0.0323 0.2694 1.0000
15.000 1.6907 0.03770 0.03193 -0.0312 0.2671 1.0000
15.250 1.6969 0.03909 0.03338 -0.0302 0.2643 1.0000
15.500 1.7032 0.04050 0.03483 -0.0293 0.2614 1.0000
15.750 1.7145 0.04154 0.03585 -0.0286 0.2587 1.0000
16.000 1.7149 0.04358 0.03803 -0.0276 0.2557 1.0000
16.250 1.7183 0.04543 0.03999 -0.0269 0.2527 1.0000
16.500 1.7217 0.04734 0.04198 -0.0263 0.2493 1.0000
16.750 1.7252 0.04923 0.04390 -0.0257 0.2461 1.0000
17.000 1.7277 0.05126 0.04597 -0.0251 0.2428 1.0000
17.250 1.7276 0.05369 0.04855 -0.0247 0.2389 1.0000
17.500 1.7283 0.05604 0.05098 -0.0243 0.2349 1.0000
17.750 1.7247 0.05881 0.05376 -0.0238 0.2306 1.0000
18.000 1.7232 0.06147 0.05653 -0.0236 0.2264 1.0000
18.250 1.7174 0.06464 0.05980 -0.0234 0.2209 1.0000
18.500 1.7064 0.06839 0.06357 -0.0232 0.2154 1.0000
18.750 1.6941 0.07242 0.06770 -0.0231 0.2074 1.0000
19.000 1.6773 0.07696 0.07228 -0.0231 0.2008 1.0000
19.250 1.6525 0.08258 0.07794 -0.0233 0.1916 1.0000
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