GOE 363 AIRFOIL (goe363-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: GOE 363 AIRFOIL (goe363-il) Reynolds number: 1,000,000 Max Cl/Cd: 110.52 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe363-il-1000000.txt Download as CSV file: xf-goe363-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 363 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.2672 0.11300 0.11142 -0.0379 1.0000 0.0142
-10.500 -0.2615 0.10917 0.10761 -0.0398 0.9986 0.0142
-9.750 -0.4516 0.02464 0.02192 -0.1133 0.9180 0.0138
-9.500 -0.4312 0.02229 0.01924 -0.1140 0.9072 0.0141
-9.250 -0.4132 0.01917 0.01569 -0.1147 0.8963 0.0147
-9.000 -0.3864 0.01897 0.01546 -0.1146 0.8881 0.0151
-8.750 -0.3590 0.01903 0.01550 -0.1144 0.8807 0.0154
-8.500 -0.3319 0.01882 0.01523 -0.1143 0.8731 0.0158
-8.250 -0.3057 0.01831 0.01459 -0.1142 0.8660 0.0163
-8.000 -0.2799 0.01738 0.01347 -0.1142 0.8599 0.0170
-7.750 -0.2534 0.01669 0.01259 -0.1142 0.8541 0.0175
-7.500 -0.2291 0.01520 0.01082 -0.1142 0.8486 0.0182
-7.250 -0.2017 0.01490 0.01050 -0.1141 0.8435 0.0187
-7.000 -0.1740 0.01471 0.01026 -0.1140 0.8381 0.0192
-6.750 -0.1467 0.01442 0.00987 -0.1139 0.8322 0.0198
-6.500 -0.1191 0.01405 0.00942 -0.1138 0.8265 0.0206
-6.250 -0.0913 0.01384 0.00908 -0.1137 0.8207 0.0214
-6.000 -0.0642 0.01316 0.00823 -0.1135 0.8154 0.0222
-5.750 -0.0375 0.01234 0.00736 -0.1135 0.8097 0.0230
-5.500 -0.0098 0.01208 0.00703 -0.1133 0.8043 0.0237
-5.250 0.0181 0.01177 0.00667 -0.1132 0.7985 0.0245
-5.000 0.0460 0.01152 0.00635 -0.1131 0.7916 0.0255
-4.750 0.0740 0.01133 0.00607 -0.1129 0.7852 0.0263
-4.500 0.1025 0.01118 0.00586 -0.1128 0.7789 0.0268
-4.250 0.1290 0.01014 0.00470 -0.1126 0.7725 0.0279
-4.000 0.1569 0.00978 0.00433 -0.1125 0.7651 0.0290
-3.750 0.1846 0.00953 0.00403 -0.1123 0.7564 0.0299
-3.500 0.2127 0.00925 0.00371 -0.1122 0.7468 0.0308
-3.250 0.2406 0.00902 0.00341 -0.1120 0.7376 0.0316
-3.000 0.2687 0.00883 0.00317 -0.1118 0.7270 0.0324
-2.750 0.2966 0.00871 0.00300 -0.1117 0.7124 0.0330
-2.500 0.3237 0.00842 0.00259 -0.1113 0.6919 0.0338
-2.250 0.3503 0.00824 0.00226 -0.1109 0.6637 0.0351
-2.000 0.3767 0.00821 0.00208 -0.1105 0.6291 0.0364
-1.750 0.4026 0.00828 0.00198 -0.1100 0.5913 0.0377
-1.500 0.4290 0.00835 0.00191 -0.1096 0.5625 0.0393
-1.000 0.4830 0.00844 0.00177 -0.1090 0.5241 0.0434
-0.750 0.5103 0.00844 0.00173 -0.1087 0.5084 0.0499
-0.250 0.5646 0.00836 0.00181 -0.1084 0.4783 0.1390
0.000 0.5921 0.00844 0.00184 -0.1083 0.4624 0.1482
0.250 0.6193 0.00854 0.00187 -0.1081 0.4435 0.1553
0.500 0.6457 0.00871 0.00192 -0.1078 0.4128 0.1624
0.750 0.6706 0.00902 0.00202 -0.1073 0.3661 0.1694
1.000 0.6957 0.00932 0.00215 -0.1068 0.3301 0.1779
1.250 0.7216 0.00951 0.00227 -0.1065 0.3074 0.1945
1.500 0.7479 0.00957 0.00241 -0.1063 0.2915 0.2568
1.750 0.7743 0.00958 0.00255 -0.1061 0.2790 0.3436
2.000 0.7995 0.00834 0.00279 -0.1058 0.2700 1.0000
2.250 0.8261 0.00854 0.00290 -0.1056 0.2615 1.0000
2.500 0.8531 0.00869 0.00299 -0.1054 0.2554 1.0000
2.750 0.8797 0.00888 0.00311 -0.1051 0.2491 1.0000
3.000 0.9066 0.00903 0.00322 -0.1049 0.2447 1.0000
3.250 0.9336 0.00918 0.00333 -0.1047 0.2407 1.0000
3.500 0.9602 0.00936 0.00346 -0.1045 0.2366 1.0000
3.750 0.9866 0.00955 0.00361 -0.1043 0.2319 1.0000
4.000 1.0136 0.00968 0.00373 -0.1041 0.2293 1.0000
4.250 1.0403 0.00983 0.00386 -0.1039 0.2264 1.0000
4.500 1.0667 0.01001 0.00401 -0.1037 0.2233 1.0000
4.750 1.0928 0.01021 0.00418 -0.1034 0.2199 1.0000
5.000 1.1190 0.01040 0.00435 -0.1032 0.2166 1.0000
5.250 1.1456 0.01053 0.00449 -0.1030 0.2144 1.0000
5.500 1.1718 0.01070 0.00465 -0.1028 0.2105 1.0000
5.750 1.1973 0.01093 0.00483 -0.1024 0.2052 1.0000
6.000 1.2231 0.01112 0.00501 -0.1022 0.2004 1.0000
6.250 1.2489 0.01130 0.00518 -0.1019 0.1951 1.0000
6.500 1.2737 0.01157 0.00540 -0.1015 0.1885 1.0000
6.750 1.2990 0.01177 0.00558 -0.1012 0.1812 1.0000
7.000 1.3227 0.01210 0.00583 -0.1006 0.1672 1.0000
7.250 1.3426 0.01272 0.00625 -0.0995 0.1395 1.0000
7.500 1.3629 0.01329 0.00671 -0.0985 0.1258 1.0000
7.750 1.3847 0.01372 0.00710 -0.0976 0.1188 1.0000
8.000 1.4058 0.01418 0.00752 -0.0967 0.1124 1.0000
8.250 1.4283 0.01452 0.00786 -0.0960 0.1082 1.0000
8.500 1.4484 0.01502 0.00831 -0.0949 0.1012 1.0000
8.750 1.4686 0.01548 0.00873 -0.0939 0.0908 1.0000
9.000 1.4594 0.01781 0.01062 -0.0884 0.0190 1.0000
9.250 1.4744 0.01849 0.01132 -0.0865 0.0149 1.0000
9.500 1.4912 0.01904 0.01192 -0.0850 0.0138 1.0000
9.750 1.5070 0.01966 0.01260 -0.0834 0.0130 1.0000
10.000 1.5212 0.02039 0.01338 -0.0816 0.0123 1.0000
10.250 1.5332 0.02129 0.01436 -0.0796 0.0115 1.0000
10.500 1.5458 0.02215 0.01529 -0.0778 0.0110 1.0000
10.750 1.5595 0.02295 0.01614 -0.0763 0.0106 1.0000
11.000 1.5719 0.02385 0.01710 -0.0746 0.0102 1.0000
11.250 1.5830 0.02488 0.01818 -0.0730 0.0098 1.0000
11.500 1.5928 0.02603 0.01940 -0.0713 0.0094 1.0000
11.750 1.6003 0.02739 0.02084 -0.0695 0.0091 1.0000
12.000 1.6023 0.02926 0.02282 -0.0674 0.0087 1.0000
12.250 1.6033 0.03129 0.02497 -0.0654 0.0085 1.0000
12.500 1.6111 0.03279 0.02654 -0.0642 0.0084 1.0000
12.750 1.6167 0.03452 0.02835 -0.0629 0.0082 1.0000
13.000 1.6203 0.03650 0.03043 -0.0617 0.0080 1.0000
13.250 1.6219 0.03873 0.03274 -0.0605 0.0078 1.0000
13.500 1.6225 0.04113 0.03524 -0.0594 0.0076 1.0000
13.750 1.6216 0.04380 0.03801 -0.0586 0.0074 1.0000
14.000 1.6200 0.04666 0.04096 -0.0580 0.0073 1.0000
14.250 1.6166 0.04988 0.04427 -0.0576 0.0071 1.0000
14.500 1.6112 0.05353 0.04803 -0.0576 0.0070 1.0000
14.750 1.6031 0.05774 0.05236 -0.0579 0.0069 1.0000
15.000 1.5918 0.06260 0.05733 -0.0586 0.0068 1.0000
15.250 1.5775 0.06812 0.06299 -0.0597 0.0067 1.0000
15.500 1.5605 0.07422 0.06923 -0.0611 0.0067 1.0000
15.750 1.5414 0.08070 0.07584 -0.0628 0.0067 1.0000
16.000 1.5197 0.08775 0.08304 -0.0648 0.0066 1.0000
16.250 1.4979 0.09497 0.09040 -0.0669 0.0066 1.0000
16.500 1.4751 0.10249 0.09806 -0.0693 0.0066 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 363 AIRFOIL (goe363-il)