GOE 511 AIRFOIL (goe511-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 511 AIRFOIL (goe511-il) Reynolds number: 500,000 Max Cl/Cd: 66.98 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe511-il-500000-n5.txt Download as CSV file: xf-goe511-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 511 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 0.1364 0.10196 0.09914 -0.1333 0.9413 0.0200
-12.250 0.1376 0.09958 0.09677 -0.1329 0.9365 0.0204
-12.000 0.1260 0.09277 0.08994 -0.1363 0.9326 0.0220
-11.750 0.1427 0.09046 0.08763 -0.1387 0.9294 0.0222
-11.500 0.1627 0.08793 0.08508 -0.1420 0.9267 0.0224
-11.250 0.1805 0.08561 0.08275 -0.1448 0.9240 0.0228
-11.000 0.1828 0.08324 0.08039 -0.1447 0.9172 0.0229
-10.750 0.1985 0.08004 0.07716 -0.1484 0.9114 0.0234
-10.500 0.2120 0.07642 0.07351 -0.1525 0.9058 0.0243
-10.250 0.2042 0.07116 0.06823 -0.1553 0.8975 0.0250
-10.000 0.1935 0.06291 0.05993 -0.1627 0.8915 0.0256
-9.750 0.1854 0.05904 0.05605 -0.1643 0.8791 0.0257
-9.250 -0.0703 0.02878 0.02492 -0.1559 0.8523 0.0268
-9.000 -0.0750 0.02654 0.02239 -0.1516 0.8381 0.0270
-8.750 -0.0744 0.02479 0.02035 -0.1475 0.8165 0.0272
-8.500 -0.0627 0.02309 0.01820 -0.1453 0.7762 0.0275
-8.000 -0.0574 0.02137 0.01571 -0.1360 0.7097 0.0281
-7.750 -0.0545 0.02066 0.01472 -0.1312 0.6894 0.0285
-7.500 -0.0518 0.02000 0.01382 -0.1262 0.6711 0.0287
-7.250 -0.0477 0.01939 0.01298 -0.1214 0.6533 0.0289
-7.000 -0.0416 0.01884 0.01220 -0.1170 0.6349 0.0291
-6.750 -0.0342 0.01841 0.01156 -0.1128 0.6155 0.0292
-6.500 -0.0271 0.01797 0.01093 -0.1085 0.5952 0.0293
-6.250 -0.0176 0.01754 0.01034 -0.1048 0.5784 0.0295
-6.000 -0.0055 0.01723 0.00992 -0.1015 0.5636 0.0298
-5.750 0.0087 0.01690 0.00948 -0.0987 0.5514 0.0299
-5.500 0.0237 0.01666 0.00913 -0.0960 0.5413 0.0301
-5.250 0.0411 0.01639 0.00877 -0.0938 0.5317 0.0303
-4.750 0.0778 0.01590 0.00810 -0.0897 0.5172 0.0309
-4.500 0.0973 0.01568 0.00780 -0.0879 0.5109 0.0312
-4.250 0.1161 0.01549 0.00752 -0.0859 0.5049 0.0315
-4.000 0.1367 0.01531 0.00727 -0.0843 0.4998 0.0319
-3.750 0.1579 0.01514 0.00703 -0.0828 0.4941 0.0325
-3.500 0.1783 0.01499 0.00680 -0.0811 0.4884 0.0328
-3.250 0.1979 0.01488 0.00660 -0.0793 0.4821 0.0332
-3.000 0.2201 0.01472 0.00640 -0.0780 0.4777 0.0334
-2.750 0.2406 0.01450 0.00616 -0.0764 0.4722 0.0338
-2.500 0.2605 0.01440 0.00603 -0.0747 0.4669 0.0342
-2.250 0.2809 0.01431 0.00591 -0.0731 0.4621 0.0346
-2.000 0.3029 0.01420 0.00579 -0.0718 0.4575 0.0351
-1.750 0.3242 0.01413 0.00569 -0.0704 0.4522 0.0357
-1.500 0.3444 0.01409 0.00561 -0.0688 0.4469 0.0362
-1.250 0.3653 0.01405 0.00553 -0.0673 0.4420 0.0367
-1.000 0.3869 0.01399 0.00545 -0.0659 0.4366 0.0375
-0.750 0.4068 0.01399 0.00540 -0.0643 0.4303 0.0382
-0.500 0.4260 0.01398 0.00537 -0.0626 0.4247 0.0390
-0.250 0.4476 0.01395 0.00535 -0.0613 0.4194 0.0401
0.000 0.4682 0.01397 0.00534 -0.0598 0.4136 0.0410
0.250 0.4874 0.01403 0.00535 -0.0581 0.4081 0.0421
0.500 0.5087 0.01404 0.00534 -0.0567 0.4031 0.0434
0.750 0.5288 0.01406 0.00536 -0.0552 0.3975 0.0453
1.000 0.5476 0.01415 0.00540 -0.0535 0.3920 0.0472
1.250 0.5673 0.01422 0.00545 -0.0519 0.3875 0.0499
1.500 0.5876 0.01427 0.00550 -0.0505 0.3825 0.0547
1.750 0.6067 0.01432 0.00557 -0.0488 0.3776 0.0653
2.000 0.6233 0.01430 0.00568 -0.0467 0.3730 0.1172
2.250 0.6417 0.01431 0.00587 -0.0450 0.3689 0.1834
2.500 0.6619 0.01444 0.00602 -0.0437 0.3647 0.2006
2.750 0.6811 0.01460 0.00619 -0.0422 0.3602 0.2119
3.000 0.6997 0.01482 0.00637 -0.0406 0.3558 0.2227
3.250 0.7196 0.01498 0.00654 -0.0393 0.3525 0.2306
3.500 0.7405 0.01513 0.00670 -0.0381 0.3493 0.2378
3.750 0.7605 0.01530 0.00688 -0.0368 0.3460 0.2471
4.000 0.7796 0.01550 0.00709 -0.0354 0.3428 0.2557
4.250 0.7985 0.01573 0.00730 -0.0340 0.3399 0.2610
4.500 0.8172 0.01597 0.00752 -0.0326 0.3371 0.2653
4.750 0.8376 0.01615 0.00773 -0.0315 0.3348 0.2718
5.000 0.8584 0.01634 0.00793 -0.0304 0.3328 0.2778
5.250 0.8785 0.01654 0.00816 -0.0294 0.3303 0.2854
5.500 0.8980 0.01677 0.00841 -0.0282 0.3281 0.2971
5.750 0.9171 0.01701 0.00869 -0.0270 0.3258 0.3079
6.000 0.9361 0.01728 0.00897 -0.0258 0.3235 0.3213
6.250 0.9550 0.01754 0.00928 -0.0247 0.3214 0.3446
6.500 0.9748 0.01766 0.00965 -0.0240 0.3190 0.4803
7.000 1.2419 0.01854 0.01170 -0.0713 0.3093 1.0000
7.250 1.2579 0.01890 0.01205 -0.0696 0.3074 1.0000
7.500 1.2727 0.01931 0.01244 -0.0678 0.3052 1.0000
7.750 1.2871 0.01975 0.01286 -0.0660 0.3029 1.0000
8.000 1.3032 0.02014 0.01327 -0.0645 0.3011 1.0000
8.250 1.3206 0.02048 0.01363 -0.0632 0.2995 1.0000
8.500 1.3372 0.02086 0.01404 -0.0618 0.2976 1.0000
8.750 1.3535 0.02127 0.01447 -0.0604 0.2960 1.0000
9.000 1.3696 0.02170 0.01492 -0.0590 0.2942 1.0000
9.250 1.3849 0.02217 0.01541 -0.0575 0.2922 1.0000
9.500 1.3981 0.02274 0.01597 -0.0559 0.2893 1.0000
9.750 1.4108 0.02337 0.01659 -0.0542 0.2866 1.0000
10.000 1.4243 0.02398 0.01722 -0.0527 0.2849 1.0000
10.250 1.4406 0.02447 0.01775 -0.0515 0.2833 1.0000
10.500 1.4564 0.02499 0.01832 -0.0504 0.2817 1.0000
10.750 1.4715 0.02555 0.01893 -0.0492 0.2799 1.0000
11.000 1.4857 0.02618 0.01960 -0.0479 0.2781 1.0000
11.250 1.4995 0.02685 0.02030 -0.0467 0.2761 1.0000
11.500 1.5121 0.02761 0.02108 -0.0453 0.2740 1.0000
11.750 1.5238 0.02844 0.02194 -0.0440 0.2720 1.0000
12.000 1.5341 0.02937 0.02289 -0.0425 0.2697 1.0000
12.250 1.5469 0.03019 0.02376 -0.0414 0.2678 1.0000
12.500 1.5605 0.03097 0.02460 -0.0404 0.2656 1.0000
12.750 1.5725 0.03187 0.02557 -0.0393 0.2632 1.0000
13.000 1.5837 0.03285 0.02660 -0.0383 0.2606 1.0000
13.250 1.5928 0.03400 0.02779 -0.0371 0.2579 1.0000
13.500 1.6006 0.03527 0.02908 -0.0359 0.2554 1.0000
13.750 1.6091 0.03654 0.03040 -0.0348 0.2529 1.0000
14.000 1.6198 0.03766 0.03160 -0.0340 0.2499 1.0000
14.250 1.6266 0.03912 0.03311 -0.0329 0.2452 1.0000
14.500 1.6301 0.04089 0.03491 -0.0318 0.2412 1.0000
14.750 1.6335 0.04271 0.03677 -0.0308 0.2354 1.0000
15.000 1.6358 0.04467 0.03878 -0.0298 0.2294 1.0000
15.250 1.6331 0.04714 0.04127 -0.0287 0.2234 1.0000
15.500 1.6312 0.04961 0.04378 -0.0277 0.2158 1.0000
15.750 1.6242 0.05261 0.04681 -0.0267 0.2091 1.0000
16.000 1.6156 0.05589 0.05011 -0.0258 0.2010 1.0000
16.250 1.5998 0.06001 0.05426 -0.0250 0.1919 1.0000
16.500 1.5853 0.06409 0.05837 -0.0243 0.1858 1.0000
16.750 1.5720 0.06812 0.06244 -0.0238 0.1798 1.0000
17.000 1.5528 0.07289 0.06725 -0.0234 0.1737 1.0000
17.250 1.5394 0.07707 0.07147 -0.0232 0.1692 1.0000
17.500 1.5304 0.08077 0.07525 -0.0231 0.1660 1.0000
17.750 1.5192 0.08480 0.07933 -0.0231 0.1628 1.0000
18.000 1.4995 0.08993 0.08449 -0.0233 0.1582 1.0000
18.250 1.4971 0.09296 0.08759 -0.0235 0.1564 1.0000
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