GOE 508 AIRFOIL (goe508-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 508 AIRFOIL (goe508-il) Reynolds number: 500,000 Max Cl/Cd: 105.71 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe508-il-500000.txt Download as CSV file: xf-goe508-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.1073 0.05680 0.05345 -0.1370 0.8253 0.0422
-10.250 -0.3549 0.03155 0.02711 -0.1376 0.8061 0.0388
-10.000 -0.3586 0.02943 0.02474 -0.1346 0.7993 0.0390
-9.750 -0.3500 0.02809 0.02322 -0.1326 0.7933 0.0393
-9.500 -0.3432 0.02638 0.02125 -0.1303 0.7877 0.0395
-9.250 -0.3313 0.02505 0.01974 -0.1284 0.7821 0.0398
-9.000 -0.3175 0.02378 0.01825 -0.1267 0.7768 0.0401
-8.750 -0.3006 0.02277 0.01702 -0.1253 0.7719 0.0406
-8.500 -0.2831 0.02180 0.01587 -0.1238 0.7669 0.0412
-8.250 -0.2646 0.02084 0.01471 -0.1225 0.7616 0.0416
-8.000 -0.2444 0.02005 0.01371 -0.1212 0.7564 0.0419
-7.750 -0.2226 0.01943 0.01287 -0.1202 0.7515 0.0422
-7.500 -0.2018 0.01821 0.01158 -0.1192 0.7464 0.0428
-7.250 -0.1786 0.01748 0.01082 -0.1185 0.7412 0.0433
-7.000 -0.1545 0.01696 0.01024 -0.1178 0.7364 0.0439
-6.750 -0.1300 0.01651 0.00972 -0.1172 0.7316 0.0445
-6.500 -0.1059 0.01604 0.00921 -0.1165 0.7264 0.0452
-6.250 -0.0813 0.01561 0.00870 -0.1158 0.7211 0.0460
-6.000 -0.0561 0.01525 0.00821 -0.1151 0.7160 0.0469
-5.750 -0.0312 0.01493 0.00781 -0.1145 0.7106 0.0476
-5.500 -0.0077 0.01423 0.00713 -0.1137 0.7050 0.0487
-5.250 0.0173 0.01388 0.00675 -0.1131 0.6998 0.0497
-5.000 0.0426 0.01359 0.00642 -0.1125 0.6947 0.0509
-4.750 0.0676 0.01329 0.00610 -0.1118 0.6889 0.0521
-4.500 0.0932 0.01307 0.00580 -0.1112 0.6835 0.0532
-4.250 0.1171 0.01262 0.00533 -0.1104 0.6783 0.0549
-4.000 0.1418 0.01236 0.00510 -0.1097 0.6725 0.0567
-3.750 0.1672 0.01217 0.00487 -0.1091 0.6666 0.0589
-3.500 0.1919 0.01190 0.00455 -0.1084 0.6612 0.0613
-3.250 0.2169 0.01169 0.00437 -0.1077 0.6557 0.0642
-3.000 0.2421 0.01149 0.00416 -0.1071 0.6501 0.0676
-2.750 0.2677 0.01135 0.00399 -0.1065 0.6450 0.0721
-2.500 0.2932 0.01120 0.00388 -0.1059 0.6398 0.0784
-2.250 0.3186 0.01107 0.00380 -0.1053 0.6341 0.0878
-2.000 0.3442 0.01098 0.00371 -0.1048 0.6283 0.1011
-1.750 0.3698 0.01091 0.00364 -0.1042 0.6224 0.1146
-1.500 0.3950 0.01080 0.00358 -0.1036 0.6164 0.1267
-1.250 0.4206 0.01073 0.00351 -0.1031 0.6113 0.1375
-1.000 0.4467 0.01071 0.00347 -0.1026 0.6066 0.1480
-0.750 0.4719 0.01063 0.00344 -0.1020 0.6015 0.1601
-0.500 0.4969 0.01055 0.00340 -0.1014 0.5962 0.1769
-0.250 0.5220 0.01047 0.00338 -0.1008 0.5913 0.2045
0.250 0.5684 0.01005 0.00340 -0.0991 0.5819 0.3393
0.500 0.5868 0.00959 0.00343 -0.0973 0.5773 0.5043
0.750 0.5996 0.00905 0.00352 -0.0942 0.5729 0.7164
1.000 0.6410 0.00875 0.00379 -0.0965 0.5686 0.9129
1.250 0.7118 0.00895 0.00396 -0.1053 0.5631 0.9572
1.500 0.7546 0.00914 0.00405 -0.1083 0.5581 0.9722
1.750 0.7970 0.00932 0.00416 -0.1113 0.5532 0.9822
2.000 0.8416 0.00941 0.00423 -0.1148 0.5476 0.9892
2.250 0.8844 0.00953 0.00428 -0.1180 0.5422 0.9949
2.500 0.9340 0.00969 0.00433 -0.1227 0.5372 1.0000
2.750 0.9532 0.00973 0.00439 -0.1210 0.5331 1.0000
3.000 0.9726 0.00980 0.00445 -0.1194 0.5284 1.0000
3.250 0.9920 0.00991 0.00450 -0.1178 0.5240 1.0000
3.500 1.0120 0.01006 0.00459 -0.1163 0.5197 1.0000
3.750 1.0311 0.01013 0.00469 -0.1146 0.5155 1.0000
4.000 1.0503 0.01022 0.00478 -0.1129 0.5109 1.0000
4.250 1.0693 0.01035 0.00487 -0.1112 0.5063 1.0000
4.500 1.0884 0.01051 0.00498 -0.1095 0.5017 1.0000
4.750 1.1070 0.01059 0.00510 -0.1077 0.4968 1.0000
5.000 1.1251 0.01071 0.00521 -0.1058 0.4914 1.0000
5.250 1.1425 0.01089 0.00533 -0.1038 0.4861 1.0000
5.500 1.1601 0.01099 0.00547 -0.1018 0.4806 1.0000
5.750 1.1765 0.01113 0.00561 -0.0996 0.4742 1.0000
6.000 1.1908 0.01133 0.00576 -0.0970 0.4678 1.0000
6.250 1.2030 0.01144 0.00590 -0.0939 0.4601 1.0000
6.500 1.2116 0.01165 0.00606 -0.0902 0.4518 1.0000
6.750 1.2236 0.01183 0.00626 -0.0873 0.4414 1.0000
7.000 1.2338 0.01211 0.00650 -0.0841 0.4301 1.0000
7.250 1.2424 0.01247 0.00681 -0.0807 0.4160 1.0000
7.500 1.2492 0.01296 0.00723 -0.0773 0.3963 1.0000
7.750 1.2512 0.01368 0.00783 -0.0732 0.3720 1.0000
8.000 1.2520 0.01460 0.00862 -0.0693 0.3472 1.0000
8.250 1.2519 0.01570 0.00958 -0.0656 0.3231 1.0000
8.500 1.2527 0.01690 0.01065 -0.0623 0.3035 1.0000
8.750 1.2580 0.01799 0.01166 -0.0597 0.2891 1.0000
9.000 1.2676 0.01893 0.01257 -0.0578 0.2799 1.0000
9.250 1.2751 0.02002 0.01362 -0.0557 0.2721 1.0000
9.500 1.2874 0.02089 0.01449 -0.0543 0.2664 1.0000
9.750 1.2983 0.02186 0.01546 -0.0528 0.2611 1.0000
10.000 1.3063 0.02304 0.01660 -0.0511 0.2559 1.0000
10.250 1.3195 0.02391 0.01751 -0.0499 0.2519 1.0000
10.500 1.3322 0.02485 0.01847 -0.0488 0.2479 1.0000
10.750 1.3429 0.02592 0.01954 -0.0475 0.2441 1.0000
11.000 1.3514 0.02716 0.02077 -0.0461 0.2405 1.0000
11.250 1.3630 0.02821 0.02185 -0.0450 0.2375 1.0000
11.500 1.3770 0.02913 0.02282 -0.0441 0.2351 1.0000
11.750 1.3900 0.03013 0.02386 -0.0432 0.2323 1.0000
12.000 1.4014 0.03126 0.02501 -0.0422 0.2296 1.0000
12.250 1.4112 0.03250 0.02627 -0.0412 0.2267 1.0000
12.500 1.4194 0.03387 0.02762 -0.0400 0.2234 1.0000
12.750 1.4320 0.03497 0.02878 -0.0393 0.2209 1.0000
13.000 1.4449 0.03608 0.02996 -0.0387 0.2179 1.0000
13.250 1.4557 0.03736 0.03129 -0.0379 0.2147 1.0000
13.500 1.4643 0.03882 0.03275 -0.0371 0.2111 1.0000
13.750 1.4702 0.04047 0.03437 -0.0361 0.2069 1.0000
14.000 1.4831 0.04168 0.03568 -0.0357 0.2046 1.0000
14.250 1.4943 0.04303 0.03711 -0.0352 0.2016 1.0000
14.500 1.5037 0.04452 0.03864 -0.0346 0.1983 1.0000
14.750 1.5105 0.04625 0.04037 -0.0339 0.1949 1.0000
15.000 1.5168 0.04802 0.04216 -0.0333 0.1913 1.0000
15.250 1.5284 0.04940 0.04364 -0.0330 0.1884 1.0000
15.500 1.5370 0.05107 0.04538 -0.0326 0.1847 1.0000
15.750 1.5432 0.05296 0.04729 -0.0321 0.1808 1.0000
16.000 1.5470 0.05509 0.04943 -0.0317 0.1771 1.0000
16.250 1.5569 0.05669 0.05111 -0.0314 0.1725 1.0000
16.500 1.5616 0.05881 0.05328 -0.0311 0.1678 1.0000
16.750 1.5639 0.06119 0.05567 -0.0308 0.1625 1.0000
17.000 1.5698 0.06321 0.05775 -0.0306 0.1574 1.0000
17.250 1.5694 0.06593 0.06046 -0.0304 0.1516 1.0000
17.500 1.5729 0.06821 0.06279 -0.0302 0.1466 1.0000
17.750 1.5714 0.07107 0.06567 -0.0300 0.1403 1.0000
18.000 1.5715 0.07378 0.06841 -0.0299 0.1355 1.0000
18.250 1.5690 0.07681 0.07145 -0.0298 0.1296 1.0000
18.500 1.5657 0.07993 0.07460 -0.0298 0.1245 1.0000
18.750 1.5646 0.08283 0.07754 -0.0298 0.1200 1.0000
19.000 1.5573 0.08650 0.08122 -0.0300 0.1141 1.0000
19.250 1.5544 0.08970 0.08446 -0.0302 0.1091 1.0000
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