GOE 265 AIRFOIL (goe265-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: GOE 265 AIRFOIL (goe265-il) Reynolds number: 200,000 Max Cl/Cd: 81.98 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe265-il-200000-n5.txt Download as CSV file: xf-goe265-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 265 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2310 0.10953 0.10622 -0.0223 1.0000 0.0245
-8.750 -0.2246 0.10677 0.10350 -0.0239 1.0000 0.0246
-8.500 -0.2183 0.10408 0.10086 -0.0262 0.9933 0.0247
-8.250 -0.1997 0.09987 0.09665 -0.0278 0.9603 0.0253
-8.000 -0.1807 0.09664 0.09338 -0.0308 0.9287 0.0262
-7.500 -0.1569 0.09081 0.08743 -0.0347 0.8747 0.0273
-7.250 -0.1492 0.08672 0.08327 -0.0413 0.8502 0.0247
-7.000 -0.1378 0.08393 0.08041 -0.0406 0.8305 0.0244
-6.750 -0.1253 0.08119 0.07760 -0.0417 0.8118 0.0237
-6.500 -0.1099 0.07836 0.07470 -0.0447 0.7942 0.0257
-6.000 -0.0739 0.07281 0.06898 -0.0510 0.7642 0.0287
-5.750 -0.0540 0.06917 0.06525 -0.0551 0.7518 0.0269
-5.500 -0.0305 0.06534 0.06132 -0.0601 0.7407 0.0263
-5.250 -0.0058 0.06219 0.05806 -0.0644 0.7295 0.0272
-5.000 0.0253 0.05827 0.05402 -0.0710 0.7192 0.0292
-4.750 0.0589 0.05386 0.04944 -0.0780 0.7099 0.0296
-4.500 0.0895 0.05049 0.04596 -0.0828 0.6996 0.0309
-4.250 0.1131 0.04924 0.04463 -0.0837 0.6881 0.0329
-4.000 0.1478 0.04583 0.04103 -0.0889 0.6773 0.0343
-3.750 0.1954 0.04034 0.03523 -0.0979 0.6666 0.0363
-3.500 0.2237 0.03850 0.03328 -0.0998 0.6561 0.0379
-3.250 0.2553 0.03623 0.03083 -0.1023 0.6469 0.0387
-3.000 0.2883 0.03395 0.02838 -0.1050 0.6377 0.0401
-2.750 0.3249 0.03101 0.02516 -0.1084 0.6295 0.0422
-2.250 0.4025 0.02274 0.01599 -0.1155 0.6136 0.0455
-2.000 0.4333 0.02110 0.01411 -0.1165 0.6047 0.0467
-1.750 0.4654 0.01863 0.01116 -0.1177 0.5971 0.0485
-1.500 0.4965 0.01669 0.00873 -0.1184 0.5885 0.0513
-1.250 0.5258 0.01557 0.00716 -0.1186 0.5806 0.0542
-1.000 0.5539 0.01525 0.00678 -0.1185 0.5719 0.0560
-0.750 0.5818 0.01501 0.00641 -0.1184 0.5641 0.0583
-0.500 0.6100 0.01463 0.00588 -0.1182 0.5553 0.0616
-0.250 0.6379 0.01431 0.00540 -0.1180 0.5473 0.0655
0.000 0.6655 0.01435 0.00543 -0.1178 0.5386 0.0697
0.250 0.6933 0.01422 0.00518 -0.1176 0.5309 0.0753
0.500 0.7209 0.01411 0.00502 -0.1174 0.5224 0.0798
0.750 0.7483 0.01416 0.00503 -0.1171 0.5141 0.0860
1.000 0.7757 0.01410 0.00488 -0.1169 0.5052 0.0918
1.250 0.8031 0.01413 0.00491 -0.1167 0.4968 0.0976
1.500 0.8303 0.01413 0.00484 -0.1164 0.4884 0.1033
1.750 0.8576 0.01409 0.00480 -0.1162 0.4794 0.1085
2.000 0.8844 0.01414 0.00480 -0.1159 0.4696 0.1141
2.250 0.9114 0.01415 0.00478 -0.1156 0.4583 0.1191
2.500 0.9382 0.01416 0.00480 -0.1153 0.4473 0.1244
2.750 0.9647 0.01425 0.00485 -0.1150 0.4368 0.1310
3.000 0.9914 0.01432 0.00491 -0.1147 0.4265 0.1368
3.250 1.0181 0.01439 0.00501 -0.1145 0.4173 0.1433
3.750 1.0706 0.01465 0.00524 -0.1138 0.3976 0.1632
4.000 1.0964 0.01480 0.00540 -0.1135 0.3878 0.1764
4.250 1.1222 0.01498 0.00559 -0.1131 0.3786 0.1976
4.500 1.1485 0.01508 0.00583 -0.1129 0.3711 0.2761
4.750 1.1727 0.01435 0.00605 -0.1122 0.3642 1.0000
5.000 1.1984 0.01464 0.00628 -0.1118 0.3576 1.0000
5.250 1.2239 0.01493 0.00654 -0.1114 0.3507 1.0000
5.500 1.2490 0.01526 0.00683 -0.1110 0.3443 1.0000
5.750 1.2743 0.01556 0.00712 -0.1106 0.3374 1.0000
6.000 1.2988 0.01593 0.00743 -0.1101 0.3307 1.0000
6.250 1.3240 0.01622 0.00777 -0.1097 0.3240 1.0000
6.500 1.3485 0.01657 0.00812 -0.1092 0.3186 1.0000
6.750 1.3729 0.01693 0.00849 -0.1087 0.3139 1.0000
7.000 1.3976 0.01725 0.00889 -0.1082 0.3086 1.0000
7.250 1.4214 0.01763 0.00928 -0.1077 0.3029 1.0000
7.500 1.4451 0.01801 0.00970 -0.1071 0.2968 1.0000
7.750 1.4689 0.01837 0.01013 -0.1066 0.2908 1.0000
8.000 1.4914 0.01881 0.01060 -0.1059 0.2851 1.0000
8.250 1.5149 0.01917 0.01106 -0.1053 0.2793 1.0000
8.500 1.5375 0.01959 0.01155 -0.1046 0.2732 1.0000
8.750 1.5592 0.02005 0.01206 -0.1038 0.2672 1.0000
9.000 1.5813 0.02046 0.01261 -0.1031 0.2601 1.0000
9.250 1.6015 0.02098 0.01318 -0.1021 0.2527 1.0000
9.500 1.6213 0.02149 0.01376 -0.1011 0.2409 1.0000
9.750 1.6387 0.02213 0.01442 -0.0998 0.2253 1.0000
10.000 1.6537 0.02291 0.01520 -0.0983 0.2067 1.0000
10.250 1.6663 0.02384 0.01609 -0.0965 0.1858 1.0000
10.500 1.6737 0.02503 0.01720 -0.0941 0.1660 1.0000
10.750 1.6771 0.02636 0.01847 -0.0912 0.1510 1.0000
11.000 1.6789 0.02790 0.01998 -0.0886 0.1403 1.0000
11.250 1.6818 0.02951 0.02162 -0.0863 0.1323 1.0000
11.500 1.6828 0.03141 0.02355 -0.0843 0.1260 1.0000
11.750 1.6867 0.03321 0.02546 -0.0828 0.1202 1.0000
12.000 1.6863 0.03551 0.02782 -0.0814 0.1150 1.0000
12.250 1.6880 0.03777 0.03018 -0.0804 0.1105 1.0000
12.500 1.6914 0.03995 0.03250 -0.0796 0.1050 1.0000
12.750 1.6880 0.04299 0.03559 -0.0790 0.0993 1.0000
13.000 1.6912 0.04536 0.03811 -0.0784 0.0928 1.0000
13.250 1.6896 0.04836 0.04119 -0.0781 0.0834 1.0000
13.500 1.6811 0.05225 0.04507 -0.0779 0.0664 1.0000
13.750 1.6625 0.05750 0.05023 -0.0781 0.0522 1.0000
14.000 1.6431 0.06298 0.05569 -0.0784 0.0401 1.0000
14.250 1.6207 0.06903 0.06174 -0.0790 0.0289 1.0000
14.500 1.6031 0.07467 0.06742 -0.0798 0.0238 1.0000
14.750 1.5884 0.08009 0.07294 -0.0807 0.0215 1.0000
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Polar data table (+)
Polar graphs
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