GOE 502 AIRFOIL (goe502-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 502 AIRFOIL (goe502-il) Reynolds number: 1,000,000 Max Cl/Cd: 132.2 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe502-il-1000000.txt Download as CSV file: xf-goe502-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 502 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -0.5864 0.08223 0.07970 -0.0980 0.9940 0.0325
-15.250 -0.6242 0.07060 0.06786 -0.1085 0.9921 0.0327
-15.000 -0.6385 0.06361 0.06076 -0.1151 0.9890 0.0328
-14.750 -0.6414 0.05835 0.05541 -0.1210 0.9863 0.0330
-14.500 -0.6479 0.05235 0.04928 -0.1283 0.9836 0.0330
-14.250 -0.6423 0.04788 0.04473 -0.1346 0.9817 0.0332
-14.000 -0.6438 0.04364 0.04040 -0.1392 0.9757 0.0333
-13.750 -0.6361 0.03967 0.03635 -0.1449 0.9716 0.0335
-13.500 -0.6236 0.03569 0.03226 -0.1516 0.9686 0.0337
-13.250 -0.6140 0.03228 0.02876 -0.1566 0.9607 0.0339
-13.000 -0.5898 0.02858 0.02492 -0.1650 0.9563 0.0341
-12.750 -0.5604 0.02501 0.02119 -0.1750 0.9505 0.0344
-12.500 -0.5353 0.02334 0.01940 -0.1786 0.9441 0.0347
-12.250 -0.5060 0.02206 0.01799 -0.1818 0.9393 0.0350
-12.000 -0.4888 0.02109 0.01693 -0.1819 0.9318 0.0353
-11.750 -0.4656 0.02018 0.01591 -0.1828 0.9255 0.0355
-11.500 -0.4442 0.01949 0.01512 -0.1828 0.9187 0.0358
-11.250 -0.4243 0.01889 0.01442 -0.1823 0.9109 0.0360
-11.000 -0.3992 0.01840 0.01382 -0.1826 0.9040 0.0362
-10.750 -0.3870 0.01723 0.01260 -0.1810 0.8966 0.0368
-10.500 -0.3653 0.01659 0.01190 -0.1806 0.8894 0.0371
-10.250 -0.3435 0.01608 0.01135 -0.1800 0.8825 0.0374
-10.000 -0.3214 0.01565 0.01087 -0.1793 0.8749 0.0377
-9.750 -0.2968 0.01525 0.01040 -0.1790 0.8678 0.0381
-9.500 -0.2744 0.01483 0.00995 -0.1782 0.8602 0.0385
-9.250 -0.2505 0.01444 0.00949 -0.1777 0.8519 0.0389
-9.000 -0.2265 0.01408 0.00906 -0.1772 0.8435 0.0394
-8.750 -0.2025 0.01372 0.00863 -0.1766 0.8331 0.0398
-8.500 -0.1783 0.01340 0.00824 -0.1760 0.8214 0.0402
-8.250 -0.1541 0.01314 0.00788 -0.1753 0.8081 0.0405
-7.750 -0.1084 0.01228 0.00685 -0.1737 0.7807 0.0415
-7.500 -0.0843 0.01198 0.00649 -0.1731 0.7697 0.0421
-7.250 -0.0595 0.01178 0.00621 -0.1725 0.7596 0.0427
-7.000 -0.0339 0.01157 0.00596 -0.1720 0.7515 0.0434
-6.750 -0.0082 0.01137 0.00569 -0.1716 0.7438 0.0440
-6.500 0.0176 0.01120 0.00545 -0.1711 0.7370 0.0447
-6.250 0.0445 0.01100 0.00522 -0.1708 0.7319 0.0453
-6.000 0.0713 0.01087 0.00504 -0.1705 0.7262 0.0457
-5.750 0.0960 0.01047 0.00458 -0.1700 0.7204 0.0467
-5.500 0.1227 0.01024 0.00432 -0.1698 0.7156 0.0476
-5.250 0.1498 0.01005 0.00411 -0.1695 0.7109 0.0485
-5.000 0.1767 0.00990 0.00393 -0.1692 0.7061 0.0494
-4.750 0.2035 0.00981 0.00378 -0.1689 0.7008 0.0504
-4.500 0.2309 0.00971 0.00365 -0.1686 0.6962 0.0512
-4.250 0.2577 0.00941 0.00333 -0.1684 0.6917 0.0528
-4.000 0.2846 0.00925 0.00316 -0.1681 0.6867 0.0541
-3.750 0.3113 0.00916 0.00301 -0.1677 0.6813 0.0555
-3.500 0.3386 0.00906 0.00289 -0.1674 0.6764 0.0568
-3.250 0.3658 0.00888 0.00270 -0.1671 0.6713 0.0590
-3.000 0.3926 0.00875 0.00256 -0.1667 0.6656 0.0617
-2.750 0.4188 0.00868 0.00244 -0.1662 0.6594 0.0655
-2.500 0.4454 0.00835 0.00228 -0.1660 0.6541 0.0986
-2.250 0.4717 0.00817 0.00220 -0.1656 0.6472 0.1300
-2.000 0.4972 0.00811 0.00215 -0.1650 0.6400 0.1486
-1.750 0.5244 0.00801 0.00212 -0.1647 0.6331 0.1652
-1.500 0.5500 0.00798 0.00209 -0.1641 0.6243 0.1797
-1.250 0.5762 0.00795 0.00208 -0.1636 0.6159 0.1933
-1.000 0.6017 0.00795 0.00208 -0.1629 0.6059 0.2063
-0.750 0.6273 0.00796 0.00209 -0.1623 0.5959 0.2185
-0.250 0.6773 0.00804 0.00213 -0.1608 0.5748 0.2414
0.000 0.7014 0.00811 0.00218 -0.1599 0.5649 0.2518
0.250 0.7270 0.00817 0.00222 -0.1593 0.5560 0.2606
0.500 0.7507 0.00826 0.00229 -0.1583 0.5470 0.2712
0.750 0.7767 0.00831 0.00234 -0.1577 0.5400 0.2808
1.000 0.8011 0.00839 0.00241 -0.1569 0.5329 0.2900
1.250 0.8258 0.00848 0.00247 -0.1561 0.5265 0.2964
1.500 0.8512 0.00852 0.00254 -0.1555 0.5207 0.3066
1.750 0.8752 0.00862 0.00262 -0.1546 0.5144 0.3159
2.000 0.8989 0.00870 0.00271 -0.1536 0.5089 0.3267
2.250 0.9239 0.00874 0.00278 -0.1529 0.5045 0.3363
2.500 0.9472 0.00880 0.00285 -0.1519 0.4993 0.3473
2.750 0.9686 0.00892 0.00295 -0.1504 0.4932 0.3586
3.000 0.9923 0.00896 0.00305 -0.1495 0.4879 0.3747
3.250 1.0157 0.00901 0.00314 -0.1485 0.4822 0.3907
3.500 1.0375 0.00913 0.00326 -0.1472 0.4766 0.4075
3.750 1.0596 0.00924 0.00340 -0.1459 0.4716 0.4257
4.000 1.0839 0.00929 0.00351 -0.1451 0.4673 0.4458
4.250 1.1063 0.00939 0.00364 -0.1440 0.4618 0.4658
4.500 1.1266 0.00955 0.00381 -0.1424 0.4555 0.4854
4.750 1.1501 0.00961 0.00394 -0.1415 0.4514 0.5094
5.000 1.1732 0.00966 0.00409 -0.1405 0.4470 0.5427
5.250 1.1935 0.00967 0.00430 -0.1390 0.4419 0.6273
5.500 1.2242 0.00932 0.00461 -0.1398 0.4355 1.0000
5.750 1.2480 0.00944 0.00473 -0.1390 0.4305 1.0000
6.000 1.2698 0.00961 0.00489 -0.1378 0.4247 1.0000
6.250 1.2897 0.00985 0.00508 -0.1363 0.4189 1.0000
6.500 1.3126 0.01000 0.00524 -0.1353 0.4141 1.0000
6.750 1.3340 0.01020 0.00543 -0.1341 0.4078 1.0000
7.000 1.3519 0.01050 0.00567 -0.1323 0.4000 1.0000
7.250 1.3743 0.01068 0.00586 -0.1313 0.3934 1.0000
7.500 1.3928 0.01097 0.00612 -0.1297 0.3855 1.0000
7.750 1.4127 0.01123 0.00636 -0.1283 0.3789 1.0000
8.000 1.4318 0.01153 0.00663 -0.1268 0.3707 1.0000
8.250 1.4496 0.01187 0.00695 -0.1251 0.3632 1.0000
8.500 1.4689 0.01217 0.00725 -0.1237 0.3556 1.0000
8.750 1.4851 0.01260 0.00763 -0.1219 0.3472 1.0000
9.000 1.5026 0.01298 0.00800 -0.1203 0.3368 1.0000
9.250 1.5180 0.01347 0.00844 -0.1184 0.3264 1.0000
9.500 1.5319 0.01403 0.00895 -0.1163 0.3150 1.0000
9.750 1.5467 0.01457 0.00946 -0.1144 0.3026 1.0000
10.000 1.5600 0.01520 0.01004 -0.1124 0.2899 1.0000
10.250 1.5701 0.01600 0.01077 -0.1100 0.2739 1.0000
10.500 1.5780 0.01695 0.01162 -0.1073 0.2547 1.0000
10.750 1.5831 0.01808 0.01264 -0.1045 0.2344 1.0000
11.000 1.5865 0.01936 0.01381 -0.1016 0.2131 1.0000
11.250 1.5879 0.02082 0.01515 -0.0986 0.1919 1.0000
11.500 1.5941 0.02207 0.01634 -0.0963 0.1796 1.0000
11.750 1.6002 0.02337 0.01761 -0.0941 0.1700 1.0000
12.000 1.6084 0.02459 0.01881 -0.0922 0.1627 1.0000
12.250 1.6168 0.02586 0.02008 -0.0905 0.1566 1.0000
12.500 1.6268 0.02705 0.02129 -0.0890 0.1519 1.0000
12.750 1.6335 0.02852 0.02275 -0.0874 0.1463 1.0000
13.000 1.6435 0.02980 0.02406 -0.0861 0.1426 1.0000
13.250 1.6533 0.03113 0.02541 -0.0848 0.1387 1.0000
13.500 1.6604 0.03271 0.02700 -0.0835 0.1343 1.0000
13.750 1.6674 0.03432 0.02864 -0.0822 0.1301 1.0000
14.000 1.6766 0.03578 0.03013 -0.0811 0.1263 1.0000
14.250 1.6820 0.03759 0.03194 -0.0799 0.1219 1.0000
14.500 1.6872 0.03946 0.03383 -0.0788 0.1173 1.0000
14.750 1.6938 0.04120 0.03560 -0.0777 0.1130 1.0000
15.000 1.6943 0.04353 0.03793 -0.0764 0.1074 1.0000
15.250 1.6981 0.04559 0.04001 -0.0754 0.1018 1.0000
15.500 1.6977 0.04808 0.04249 -0.0743 0.0956 1.0000
15.750 1.6937 0.05099 0.04538 -0.0731 0.0879 1.0000
16.000 1.6907 0.05384 0.04824 -0.0721 0.0811 1.0000
16.250 1.6853 0.05701 0.05141 -0.0712 0.0744 1.0000
16.500 1.6805 0.06019 0.05460 -0.0704 0.0696 1.0000
16.750 1.6755 0.06345 0.05788 -0.0697 0.0655 1.0000
17.000 1.6712 0.06670 0.06117 -0.0692 0.0627 1.0000
17.250 1.6679 0.06991 0.06442 -0.0688 0.0601 1.0000
17.500 1.6637 0.07326 0.06780 -0.0684 0.0581 1.0000
17.750 1.6599 0.07665 0.07125 -0.0683 0.0564 1.0000
18.000 1.6586 0.07974 0.07440 -0.0682 0.0549 1.0000
18.250 1.6571 0.08289 0.07761 -0.0681 0.0538 1.0000
18.500 1.6522 0.08656 0.08133 -0.0683 0.0524 1.0000
18.750 1.6474 0.09024 0.08506 -0.0685 0.0511 1.0000
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