GOE 57 AIRFOIL (goe57-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 57 AIRFOIL (goe57-il) Reynolds number: 200,000 Max Cl/Cd: 70.23 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe57-il-200000-n5.txt Download as CSV file: xf-goe57-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 57 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3050 0.09490 0.09157 -0.0250 1.0000 0.0236
-7.500 -0.3099 0.09294 0.08967 -0.0236 1.0000 0.0235
-7.250 -0.3209 0.09172 0.08855 -0.0215 1.0000 0.0242
-7.000 -0.2871 0.08681 0.08361 -0.0375 0.9907 0.0252
-6.750 -0.2626 0.08162 0.07839 -0.0438 0.9860 0.0252
-6.500 -0.2538 0.07852 0.07532 -0.0403 0.9826 0.0269
-6.250 -0.2247 0.07578 0.07255 -0.0463 0.9770 0.0326
-6.000 -0.1750 0.07105 0.06769 -0.0631 0.9676 0.0342
-5.750 -0.1425 0.06620 0.06274 -0.0702 0.9623 0.0343
-5.250 -0.0963 0.05699 0.05346 -0.0773 0.9518 0.0360
-5.000 -0.0757 0.05492 0.05138 -0.0781 0.9448 0.0386
-4.750 -0.0394 0.05149 0.04784 -0.0841 0.9392 0.0420
-4.250 0.0576 0.04460 0.04035 -0.0999 0.9254 0.0462
-4.000 0.0911 0.04108 0.03664 -0.1034 0.9184 0.0462
-3.750 0.1143 0.03682 0.03236 -0.1055 0.9105 0.0447
-3.500 0.1442 0.03378 0.02917 -0.1079 0.9016 0.0428
-3.250 0.1802 0.03099 0.02610 -0.1107 0.8935 0.0434
-3.000 0.2123 0.02855 0.02340 -0.1123 0.8815 0.0437
-2.750 0.2426 0.02617 0.02076 -0.1135 0.8678 0.0423
-2.500 0.2730 0.02388 0.01817 -0.1143 0.8537 0.0412
-2.250 0.3032 0.02173 0.01567 -0.1149 0.8409 0.0407
-2.000 0.3328 0.01987 0.01348 -0.1152 0.8294 0.0408
-1.750 0.3620 0.01831 0.01158 -0.1153 0.8175 0.0413
-1.500 0.3904 0.01705 0.01001 -0.1152 0.8041 0.0420
-1.250 0.4181 0.01609 0.00876 -0.1149 0.7885 0.0429
-1.000 0.4454 0.01552 0.00796 -0.1145 0.7714 0.0448
-0.750 0.4726 0.01491 0.00713 -0.1142 0.7543 0.0454
-0.500 0.4998 0.01424 0.00626 -0.1138 0.7362 0.0454
-0.250 0.5267 0.01370 0.00554 -0.1133 0.7162 0.0455
0.000 0.5532 0.01327 0.00494 -0.1128 0.6928 0.0457
0.250 0.5792 0.01296 0.00444 -0.1122 0.6663 0.0461
0.500 0.6048 0.01257 0.00390 -0.1115 0.6397 0.0472
0.750 0.6304 0.01234 0.00356 -0.1110 0.6153 0.0491
1.000 0.6561 0.01228 0.00340 -0.1104 0.5901 0.0515
1.250 0.6814 0.01229 0.00328 -0.1098 0.5596 0.0549
1.500 0.7064 0.01238 0.00319 -0.1092 0.5247 0.0587
1.750 0.7313 0.01247 0.00317 -0.1086 0.4897 0.0660
2.000 0.7558 0.01265 0.00323 -0.1079 0.4552 0.0782
2.250 0.7804 0.01284 0.00330 -0.1073 0.4237 0.0976
2.500 0.8052 0.01290 0.00348 -0.1069 0.3956 0.1944
3.000 0.8512 0.01212 0.00383 -0.1051 0.3447 1.0000
3.250 0.8758 0.01249 0.00403 -0.1045 0.3185 1.0000
3.500 0.9002 0.01288 0.00426 -0.1039 0.2918 1.0000
3.750 0.9244 0.01329 0.00452 -0.1033 0.2656 1.0000
4.000 0.9486 0.01371 0.00479 -0.1027 0.2435 1.0000
4.250 0.9730 0.01410 0.00508 -0.1021 0.2284 1.0000
4.500 0.9975 0.01446 0.00541 -0.1016 0.2185 1.0000
4.750 1.0216 0.01488 0.00574 -0.1010 0.2071 1.0000
5.000 1.0452 0.01532 0.00610 -0.1004 0.1951 1.0000
5.250 1.0688 0.01576 0.00650 -0.0998 0.1875 1.0000
5.750 1.1156 0.01665 0.00728 -0.0985 0.1629 1.0000
6.000 1.1394 0.01704 0.00765 -0.0979 0.1509 1.0000
6.250 1.1633 0.01742 0.00800 -0.0973 0.1336 1.0000
6.500 1.1816 0.01846 0.00865 -0.0961 0.0690 1.0000
6.750 1.1970 0.01994 0.00987 -0.0943 0.0214 1.0000
7.000 1.2181 0.02068 0.01069 -0.0932 0.0177 1.0000
7.250 1.2394 0.02138 0.01153 -0.0921 0.0162 1.0000
7.500 1.2603 0.02209 0.01240 -0.0910 0.0156 1.0000
7.750 1.2803 0.02287 0.01338 -0.0897 0.0146 1.0000
8.000 1.2988 0.02377 0.01444 -0.0884 0.0134 1.0000
8.250 1.3156 0.02479 0.01562 -0.0868 0.0126 1.0000
8.500 1.3300 0.02594 0.01695 -0.0849 0.0121 1.0000
8.750 1.3408 0.02728 0.01844 -0.0826 0.0117 1.0000
9.000 1.3471 0.02882 0.02011 -0.0797 0.0113 1.0000
9.250 1.3481 0.03051 0.02190 -0.0761 0.0111 1.0000
9.500 1.3473 0.03245 0.02397 -0.0726 0.0109 1.0000
10.000 1.3533 0.03608 0.02780 -0.0672 0.0103 1.0000
10.250 1.3608 0.03758 0.02942 -0.0653 0.0099 1.0000
10.500 1.3667 0.03930 0.03128 -0.0634 0.0095 1.0000
10.750 1.3707 0.04131 0.03340 -0.0616 0.0092 1.0000
11.000 1.3742 0.04349 0.03570 -0.0598 0.0090 1.0000
11.250 1.3778 0.04577 0.03808 -0.0582 0.0088 1.0000
11.500 1.3816 0.04811 0.04055 -0.0566 0.0087 1.0000
11.750 1.3852 0.05056 0.04311 -0.0552 0.0085 1.0000
12.000 1.3886 0.05310 0.04579 -0.0539 0.0084 1.0000
12.250 1.3912 0.05579 0.04861 -0.0527 0.0083 1.0000
12.500 1.3927 0.05864 0.05166 -0.0517 0.0082 1.0000
12.750 1.3930 0.06169 0.05487 -0.0508 0.0081 1.0000
13.000 1.3918 0.06498 0.05833 -0.0502 0.0081 1.0000
13.250 1.3887 0.06852 0.06206 -0.0498 0.0080 1.0000
13.500 1.3840 0.07237 0.06610 -0.0498 0.0080 1.0000
13.750 1.3777 0.07651 0.07044 -0.0501 0.0080 1.0000
14.000 1.3695 0.08100 0.07513 -0.0508 0.0080 1.0000
14.250 1.3599 0.08584 0.08018 -0.0519 0.0080 1.0000
14.500 1.3493 0.09103 0.08557 -0.0536 0.0080 1.0000
14.750 1.3384 0.09646 0.09119 -0.0556 0.0079 1.0000
15.000 1.3269 0.10227 0.09718 -0.0582 0.0079 1.0000
15.250 1.3145 0.10854 0.10365 -0.0613 0.0079 1.0000
15.500 1.3021 0.11509 0.11039 -0.0648 0.0079 1.0000
15.750 1.2885 0.12221 0.11771 -0.0690 0.0080 1.0000
16.000 1.2770 0.12913 0.12478 -0.0731 0.0079 1.0000
16.250 1.2625 0.13724 0.13309 -0.0783 0.0080 1.0000
16.500 1.2482 0.14576 0.14180 -0.0840 0.0081 1.0000
16.750 1.2338 0.15474 0.15095 -0.0900 0.0082 1.0000
17.000 1.2182 0.16471 0.16110 -0.0968 0.0084 1.0000
17.250 1.2033 0.17508 0.17162 -0.1038 0.0085 1.0000
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Polar data table (+)
Polar graphs
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