GOE 515 AIRFOIL (goe515-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 515 AIRFOIL (goe515-il) Reynolds number: 100,000 Max Cl/Cd: 54.91 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe515-il-100000-n5.txt Download as CSV file: xf-goe515-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 515 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4546 0.09164 0.08644 -0.0342 1.0000 0.0393
-9.250 -0.4585 0.08756 0.08242 -0.0357 1.0000 0.0396
-9.000 -0.4648 0.08338 0.07832 -0.0372 1.0000 0.0400
-8.750 -0.4733 0.07943 0.07444 -0.0385 1.0000 0.0406
-8.500 -0.4873 0.07551 0.07064 -0.0396 1.0000 0.0413
-8.250 -0.5005 0.07076 0.06596 -0.0415 1.0000 0.0416
-8.000 -0.5133 0.06527 0.06050 -0.0438 1.0000 0.0424
-7.750 -0.5277 0.05875 0.05393 -0.0458 1.0000 0.0430
-7.500 -0.5469 0.05006 0.04501 -0.0472 1.0000 0.0436
-7.250 -0.5674 0.04069 0.03502 -0.0468 1.0000 0.0447
-7.000 -0.5732 0.03441 0.02785 -0.0449 1.0000 0.0462
-6.750 -0.5594 0.03395 0.02749 -0.0432 1.0000 0.0483
-6.500 -0.5455 0.03325 0.02671 -0.0415 1.0000 0.0506
-6.250 -0.5175 0.03013 0.02300 -0.0433 0.9950 0.0540
-6.000 -0.4898 0.02710 0.01917 -0.0445 0.9900 0.0579
-5.750 -0.4578 0.02629 0.01831 -0.0461 0.9856 0.0609
-5.500 -0.4283 0.02500 0.01674 -0.0469 0.9804 0.0638
-5.250 -0.3967 0.02351 0.01486 -0.0480 0.9761 0.0672
-5.000 -0.3665 0.02236 0.01342 -0.0488 0.9711 0.0712
-4.750 -0.3351 0.02196 0.01297 -0.0498 0.9660 0.0762
-4.500 -0.3005 0.02103 0.01170 -0.0512 0.9624 0.0829
-4.250 -0.2730 0.02046 0.01114 -0.0514 0.9560 0.0880
-4.000 -0.2399 0.01981 0.01025 -0.0525 0.9516 0.0968
-3.750 -0.2061 0.01932 0.00974 -0.0539 0.9477 0.1056
-3.500 -0.1787 0.01896 0.00930 -0.0540 0.9409 0.1157
-3.250 -0.1449 0.01862 0.00886 -0.0553 0.9366 0.1273
-3.000 -0.1115 0.01833 0.00854 -0.0566 0.9322 0.1390
-2.750 -0.0837 0.01805 0.00828 -0.0568 0.9255 0.1493
-2.500 -0.0491 0.01770 0.00790 -0.0581 0.9214 0.1590
-2.250 -0.0187 0.01742 0.00759 -0.0587 0.9158 0.1686
-2.000 0.0106 0.01712 0.00734 -0.0590 0.9096 0.1770
-1.750 0.0451 0.01680 0.00702 -0.0603 0.9056 0.1873
-1.500 0.0717 0.01660 0.00684 -0.0600 0.8982 0.2006
-1.250 0.1036 0.01630 0.00663 -0.0608 0.8929 0.2179
-1.000 0.1348 0.01602 0.00643 -0.0614 0.8873 0.2417
-0.750 0.1639 0.01574 0.00630 -0.0616 0.8801 0.2779
-0.500 0.1997 0.01519 0.00610 -0.0632 0.8756 0.3605
-0.250 0.3068 0.01336 0.00600 -0.0788 0.8774 1.0000
0.000 0.3350 0.01328 0.00580 -0.0784 0.8653 1.0000
0.250 0.3629 0.01323 0.00564 -0.0781 0.8538 1.0000
0.500 0.3918 0.01319 0.00551 -0.0779 0.8441 1.0000
0.750 0.4186 0.01319 0.00546 -0.0774 0.8339 1.0000
1.000 0.4433 0.01324 0.00546 -0.0765 0.8230 1.0000
1.250 0.4696 0.01327 0.00545 -0.0759 0.8130 1.0000
1.500 0.4967 0.01329 0.00544 -0.0754 0.8032 1.0000
1.750 0.5203 0.01338 0.00552 -0.0743 0.7912 1.0000
2.000 0.5447 0.01345 0.00560 -0.0734 0.7796 1.0000
2.250 0.5697 0.01352 0.00567 -0.0725 0.7679 1.0000
2.500 0.5951 0.01357 0.00574 -0.0716 0.7561 1.0000
2.750 0.6194 0.01363 0.00581 -0.0706 0.7421 1.0000
3.000 0.6421 0.01370 0.00591 -0.0692 0.7239 1.0000
3.250 0.6653 0.01373 0.00594 -0.0677 0.7027 1.0000
3.500 0.6885 0.01377 0.00595 -0.0663 0.6792 1.0000
3.750 0.7120 0.01384 0.00601 -0.0649 0.6551 1.0000
4.000 0.7345 0.01397 0.00611 -0.0634 0.6283 1.0000
4.250 0.7568 0.01415 0.00624 -0.0619 0.5993 1.0000
4.500 0.7789 0.01437 0.00644 -0.0605 0.5704 1.0000
4.750 0.8005 0.01464 0.00669 -0.0590 0.5398 1.0000
5.000 0.8214 0.01496 0.00693 -0.0573 0.5054 1.0000
5.250 0.8407 0.01537 0.00721 -0.0554 0.4646 1.0000
5.500 0.8582 0.01592 0.00755 -0.0533 0.4189 1.0000
5.750 0.8748 0.01655 0.00800 -0.0512 0.3714 1.0000
6.000 0.8916 0.01721 0.00850 -0.0492 0.3267 1.0000
6.250 0.9081 0.01792 0.00906 -0.0472 0.2778 1.0000
6.500 0.9231 0.01876 0.00967 -0.0452 0.2232 1.0000
6.750 0.9372 0.01975 0.01039 -0.0430 0.1815 1.0000
7.000 0.9518 0.02075 0.01126 -0.0410 0.1540 1.0000
7.250 0.9668 0.02173 0.01214 -0.0391 0.1276 1.0000
7.500 0.9827 0.02262 0.01298 -0.0374 0.1017 1.0000
7.750 0.9982 0.02355 0.01386 -0.0356 0.0807 1.0000
8.000 1.0122 0.02459 0.01484 -0.0335 0.0648 1.0000
8.250 1.0242 0.02579 0.01601 -0.0312 0.0535 1.0000
8.500 1.0334 0.02719 0.01737 -0.0286 0.0466 1.0000
8.750 1.0454 0.02839 0.01876 -0.0263 0.0408 1.0000
9.000 1.0533 0.02981 0.02016 -0.0237 0.0367 1.0000
9.250 1.0645 0.03106 0.02160 -0.0213 0.0338 1.0000
9.500 1.0745 0.03249 0.02314 -0.0189 0.0315 1.0000
9.750 1.0834 0.03395 0.02465 -0.0166 0.0295 1.0000
10.000 1.0928 0.03571 0.02648 -0.0145 0.0279 1.0000
10.250 1.1048 0.03735 0.02836 -0.0127 0.0261 1.0000
10.500 1.1154 0.03915 0.03037 -0.0108 0.0247 1.0000
10.750 1.1246 0.04113 0.03253 -0.0090 0.0237 1.0000
11.000 1.1322 0.04322 0.03485 -0.0071 0.0229 1.0000
11.250 1.1374 0.04543 0.03722 -0.0053 0.0222 1.0000
11.500 1.1407 0.04781 0.03975 -0.0036 0.0216 1.0000
11.750 1.1408 0.05085 0.04293 -0.0020 0.0210 1.0000
12.000 1.1369 0.05370 0.04611 -0.0002 0.0206 1.0000
12.250 1.1285 0.05698 0.04974 0.0012 0.0201 1.0000
12.500 1.1186 0.06066 0.05371 0.0021 0.0198 1.0000
12.750 1.1056 0.06474 0.05808 0.0024 0.0196 1.0000
13.000 1.0900 0.06941 0.06302 0.0018 0.0194 1.0000
13.250 1.0742 0.07452 0.06836 0.0006 0.0196 1.0000
13.500 1.0536 0.08063 0.07472 -0.0019 0.0194 1.0000
13.750 1.0331 0.08741 0.08171 -0.0053 0.0195 1.0000
14.000 1.0100 0.09541 0.08990 -0.0100 0.0197 1.0000
14.250 0.9865 0.10442 0.09906 -0.0157 0.0200 1.0000
14.500 0.9629 0.11449 0.10926 -0.0221 0.0203 1.0000
14.750 0.9427 0.12445 0.11927 -0.0280 0.0208 1.0000
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Polar data table (+)
Polar graphs
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