GOE 508 AIRFOIL (goe508-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 508 AIRFOIL (goe508-il) Reynolds number: 200,000 Max Cl/Cd: 69.56 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe508-il-200000-n5.txt Download as CSV file: xf-goe508-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 508 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.0098 0.09273 0.08814 -0.1133 0.8561 0.0401
-11.000 -0.0074 0.08863 0.08397 -0.1158 0.8468 0.0405
-10.750 -0.0074 0.08472 0.08001 -0.1176 0.8373 0.0406
-10.500 -0.0095 0.08051 0.07575 -0.1196 0.8294 0.0406
-10.000 -0.2485 0.04059 0.03532 -0.1394 0.8064 0.0396
-9.750 -0.2880 0.03662 0.03095 -0.1351 0.7974 0.0397
-9.500 -0.2995 0.03376 0.02769 -0.1322 0.7911 0.0400
-9.250 -0.3015 0.03148 0.02507 -0.1296 0.7841 0.0404
-9.000 -0.2967 0.02955 0.02275 -0.1274 0.7782 0.0410
-8.750 -0.2878 0.02783 0.02056 -0.1254 0.7734 0.0416
-8.500 -0.2717 0.02678 0.01941 -0.1240 0.7675 0.0420
-8.250 -0.2530 0.02595 0.01850 -0.1229 0.7616 0.0425
-8.000 -0.2331 0.02515 0.01756 -0.1219 0.7566 0.0430
-7.750 -0.2133 0.02433 0.01661 -0.1208 0.7514 0.0435
-7.500 -0.1935 0.02352 0.01568 -0.1197 0.7456 0.0440
-7.250 -0.1724 0.02273 0.01472 -0.1187 0.7405 0.0446
-7.000 -0.1500 0.02196 0.01375 -0.1178 0.7362 0.0454
-6.750 -0.1285 0.02127 0.01292 -0.1168 0.7305 0.0461
-6.500 -0.1059 0.02065 0.01212 -0.1158 0.7248 0.0469
-6.250 -0.0824 0.02006 0.01151 -0.1151 0.7198 0.0477
-6.000 -0.0588 0.01961 0.01103 -0.1144 0.7147 0.0488
-5.750 -0.0357 0.01916 0.01054 -0.1136 0.7089 0.0498
-5.500 -0.0115 0.01870 0.00998 -0.1128 0.7038 0.0511
-5.250 0.0135 0.01825 0.00939 -0.1122 0.6996 0.0523
-5.000 0.0365 0.01781 0.00895 -0.1113 0.6938 0.0534
-4.750 0.0602 0.01743 0.00856 -0.1105 0.6882 0.0546
-4.500 0.0850 0.01709 0.00816 -0.1099 0.6832 0.0563
-4.250 0.1094 0.01679 0.00780 -0.1092 0.6779 0.0584
-4.000 0.1329 0.01647 0.00750 -0.1083 0.6721 0.0605
-3.750 0.1577 0.01621 0.00720 -0.1077 0.6672 0.0630
-3.500 0.1832 0.01596 0.00687 -0.1071 0.6631 0.0659
-3.250 0.2068 0.01573 0.00670 -0.1063 0.6574 0.0689
-3.000 0.2315 0.01555 0.00650 -0.1056 0.6522 0.0733
-2.750 0.2570 0.01538 0.00632 -0.1050 0.6475 0.0787
-2.500 0.2818 0.01523 0.00619 -0.1044 0.6425 0.0857
-2.250 0.3063 0.01511 0.00609 -0.1037 0.6370 0.0948
-2.000 0.3316 0.01500 0.00596 -0.1031 0.6324 0.1051
-1.750 0.3579 0.01490 0.00581 -0.1027 0.6286 0.1162
-1.500 0.3819 0.01480 0.00577 -0.1019 0.6237 0.1271
-1.250 0.4063 0.01471 0.00571 -0.1012 0.6188 0.1381
-1.000 0.4315 0.01462 0.00562 -0.1007 0.6143 0.1502
-0.750 0.4575 0.01455 0.00553 -0.1002 0.6104 0.1642
-0.500 0.4807 0.01448 0.00555 -0.0993 0.6052 0.1815
-0.250 0.5044 0.01437 0.00554 -0.0985 0.6000 0.2080
0.000 0.5285 0.01421 0.00548 -0.0978 0.5952 0.2514
0.500 0.5691 0.01365 0.00554 -0.0951 0.5842 0.4292
0.750 0.5853 0.01315 0.00560 -0.0927 0.5795 0.6009
1.000 0.6129 0.01275 0.00575 -0.0920 0.5753 0.7995
1.250 0.6901 0.01287 0.00603 -0.1018 0.5694 0.9230
1.500 0.7382 0.01302 0.00610 -0.1059 0.5637 0.9564
1.750 0.7803 0.01318 0.00613 -0.1088 0.5590 0.9767
2.000 0.8278 0.01335 0.00626 -0.1130 0.5528 0.9954
2.250 0.8589 0.01348 0.00632 -0.1138 0.5466 1.0000
2.500 0.8788 0.01361 0.00634 -0.1123 0.5415 1.0000
2.750 0.8964 0.01375 0.00646 -0.1104 0.5356 1.0000
3.000 0.9144 0.01389 0.00656 -0.1085 0.5294 1.0000
3.250 0.9342 0.01404 0.00663 -0.1069 0.5246 1.0000
3.500 0.9532 0.01420 0.00676 -0.1053 0.5202 1.0000
3.750 0.9713 0.01437 0.00693 -0.1035 0.5152 1.0000
4.000 0.9901 0.01454 0.00706 -0.1018 0.5103 1.0000
4.250 1.0100 0.01471 0.00717 -0.1003 0.5058 1.0000
4.500 1.0269 0.01490 0.00738 -0.0983 0.5006 1.0000
4.750 1.0439 0.01509 0.00756 -0.0962 0.4949 1.0000
5.000 1.0616 0.01527 0.00770 -0.0943 0.4894 1.0000
5.250 1.0768 0.01548 0.00791 -0.0920 0.4832 1.0000
5.500 1.0910 0.01570 0.00813 -0.0895 0.4764 1.0000
5.750 1.1049 0.01591 0.00829 -0.0870 0.4701 1.0000
6.000 1.1152 0.01614 0.00856 -0.0838 0.4630 1.0000
6.250 1.1268 0.01640 0.00879 -0.0809 0.4557 1.0000
6.500 1.1384 0.01669 0.00909 -0.0781 0.4479 1.0000
6.750 1.1496 0.01701 0.00940 -0.0753 0.4391 1.0000
7.000 1.1607 0.01739 0.00978 -0.0727 0.4294 1.0000
7.250 1.1704 0.01782 0.01018 -0.0699 0.4189 1.0000
7.500 1.1796 0.01833 0.01068 -0.0671 0.4062 1.0000
7.750 1.1876 0.01893 0.01124 -0.0644 0.3923 1.0000
8.000 1.1935 0.01967 0.01191 -0.0614 0.3767 1.0000
8.250 1.1976 0.02056 0.01273 -0.0585 0.3601 1.0000
8.500 1.2010 0.02159 0.01367 -0.0556 0.3441 1.0000
8.750 1.2037 0.02275 0.01475 -0.0529 0.3287 1.0000
9.000 1.2082 0.02392 0.01585 -0.0505 0.3164 1.0000
9.250 1.2110 0.02524 0.01709 -0.0481 0.3043 1.0000
9.500 1.2152 0.02656 0.01836 -0.0460 0.2933 1.0000
9.750 1.2210 0.02785 0.01961 -0.0442 0.2840 1.0000
10.000 1.2255 0.02925 0.02095 -0.0423 0.2754 1.0000
10.250 1.2335 0.03049 0.02218 -0.0409 0.2683 1.0000
10.500 1.2420 0.03172 0.02340 -0.0395 0.2625 1.0000
10.750 1.2496 0.03303 0.02468 -0.0381 0.2577 1.0000
11.000 1.2606 0.03415 0.02583 -0.0371 0.2532 1.0000
11.250 1.2716 0.03529 0.02701 -0.0360 0.2491 1.0000
11.500 1.2813 0.03653 0.02825 -0.0350 0.2450 1.0000
11.750 1.2902 0.03785 0.02955 -0.0339 0.2413 1.0000
12.000 1.3013 0.03903 0.03076 -0.0330 0.2378 1.0000
12.250 1.3127 0.04023 0.03202 -0.0322 0.2341 1.0000
12.500 1.3237 0.04146 0.03330 -0.0314 0.2309 1.0000
12.750 1.3332 0.04282 0.03468 -0.0306 0.2273 1.0000
13.000 1.3429 0.04415 0.03600 -0.0298 0.2244 1.0000
13.250 1.3543 0.04538 0.03727 -0.0290 0.2218 1.0000
13.500 1.3657 0.04666 0.03865 -0.0285 0.2189 1.0000
13.750 1.3758 0.04807 0.04014 -0.0279 0.2158 1.0000
14.000 1.3852 0.04953 0.04165 -0.0273 0.2126 1.0000
14.250 1.3940 0.05104 0.04319 -0.0267 0.2096 1.0000
14.500 1.4033 0.05249 0.04462 -0.0260 0.2068 1.0000
14.750 1.4131 0.05398 0.04623 -0.0256 0.2043 1.0000
15.000 1.4217 0.05563 0.04799 -0.0252 0.2013 1.0000
15.250 1.4291 0.05740 0.04985 -0.0248 0.1979 1.0000
15.500 1.4355 0.05927 0.05177 -0.0244 0.1945 1.0000
15.750 1.4410 0.06118 0.05368 -0.0240 0.1911 1.0000
16.000 1.4451 0.06345 0.05610 -0.0239 0.1865 1.0000
16.250 1.4485 0.06577 0.05851 -0.0237 0.1818 1.0000
16.500 1.4498 0.06832 0.06108 -0.0236 0.1772 1.0000
16.750 1.4535 0.07068 0.06357 -0.0236 0.1726 1.0000
17.000 1.4558 0.07322 0.06620 -0.0236 0.1680 1.0000
17.250 1.4563 0.07595 0.06898 -0.0236 0.1637 1.0000
17.500 1.4584 0.07857 0.07170 -0.0237 0.1591 1.0000
17.750 1.4578 0.08153 0.07474 -0.0240 0.1535 1.0000
18.000 1.4558 0.08470 0.07795 -0.0243 0.1487 1.0000
18.250 1.4545 0.08782 0.08116 -0.0246 0.1434 1.0000
18.500 1.4494 0.09143 0.08480 -0.0251 0.1383 1.0000
18.750 1.4470 0.09474 0.08820 -0.0256 0.1337 1.0000
19.000 1.4420 0.09843 0.09195 -0.0263 0.1289 1.0000
19.250 1.4361 0.10227 0.09583 -0.0271 0.1249 1.0000
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