GOE 364 AIRFOIL (goe364-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 364 AIRFOIL (goe364-il) Reynolds number: 1,000,000 Max Cl/Cd: 124.47 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe364-il-1000000-n5.txt Download as CSV file: xf-goe364-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 364 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.0441 0.08626 0.08367 -0.0916 0.7946 0.0089
-9.750 -0.0433 0.08327 0.08059 -0.0921 0.7728 0.0091
-9.500 -0.0405 0.08066 0.07791 -0.0925 0.7550 0.0091
-9.250 -0.0284 0.07967 0.07688 -0.0927 0.7425 0.0094
-9.000 -0.0241 0.07730 0.07446 -0.0932 0.7286 0.0094
-8.750 -0.0187 0.07519 0.07232 -0.0936 0.7177 0.0097
-8.500 -0.0148 0.07274 0.06985 -0.0941 0.7089 0.0099
-8.250 -0.0144 0.07006 0.06715 -0.0946 0.7011 0.0100
-7.750 -0.0312 0.06267 0.05977 -0.0967 0.6865 0.0113
-7.500 -0.0229 0.06017 0.05725 -0.0986 0.6800 0.0114
-7.250 -0.0102 0.05828 0.05534 -0.1001 0.6729 0.0117
-7.000 0.0016 0.05577 0.05279 -0.1021 0.6668 0.0119
-6.500 0.0187 0.04436 0.04119 -0.1109 0.6555 0.0138
-6.250 0.0379 0.04221 0.03898 -0.1122 0.6492 0.0140
-6.000 0.0589 0.04060 0.03730 -0.1131 0.6429 0.0142
-5.500 0.0913 0.02870 0.02487 -0.1170 0.6318 0.0167
-5.250 0.1147 0.02756 0.02365 -0.1169 0.6251 0.0169
-4.750 0.1445 0.01629 0.01129 -0.1149 0.6156 0.0199
-4.500 0.1702 0.01593 0.01085 -0.1145 0.6089 0.0201
-4.250 0.1953 0.01542 0.01023 -0.1140 0.6022 0.0203
-4.000 0.2208 0.01480 0.00949 -0.1135 0.5958 0.0206
-3.750 0.2460 0.01420 0.00874 -0.1130 0.5882 0.0209
-3.500 0.2712 0.01347 0.00784 -0.1124 0.5808 0.0214
-3.250 0.2964 0.01280 0.00697 -0.1118 0.5716 0.0220
-3.000 0.3220 0.01212 0.00610 -0.1112 0.5625 0.0225
-2.750 0.3474 0.01165 0.00545 -0.1105 0.5495 0.0228
-2.500 0.3731 0.01134 0.00498 -0.1099 0.5354 0.0230
-2.250 0.3987 0.01113 0.00462 -0.1093 0.5181 0.0232
-2.000 0.4237 0.01064 0.00402 -0.1087 0.5049 0.0236
-1.750 0.4495 0.01046 0.00379 -0.1082 0.4918 0.0239
-1.500 0.4753 0.01038 0.00363 -0.1076 0.4776 0.0242
-1.250 0.5007 0.01029 0.00345 -0.1070 0.4630 0.0245
-1.000 0.5263 0.01017 0.00326 -0.1065 0.4517 0.0248
-0.750 0.5521 0.01007 0.00309 -0.1059 0.4424 0.0252
-0.500 0.5781 0.00996 0.00294 -0.1054 0.4348 0.0255
-0.250 0.6039 0.00988 0.00281 -0.1049 0.4271 0.0258
0.000 0.6298 0.00981 0.00270 -0.1044 0.4203 0.0261
0.250 0.6558 0.00974 0.00261 -0.1039 0.4138 0.0265
0.500 0.6816 0.00971 0.00254 -0.1034 0.4085 0.0267
0.750 0.7079 0.00966 0.00248 -0.1030 0.4045 0.0270
1.000 0.7342 0.00964 0.00244 -0.1026 0.3995 0.0273
1.250 0.7597 0.00958 0.00236 -0.1020 0.3940 0.0280
1.500 0.7856 0.00957 0.00233 -0.1015 0.3896 0.0286
1.750 0.8119 0.00955 0.00232 -0.1012 0.3857 0.0292
2.000 0.8380 0.00956 0.00233 -0.1007 0.3810 0.0298
2.250 0.8637 0.00961 0.00236 -0.1002 0.3762 0.0304
2.500 0.8897 0.00964 0.00239 -0.0998 0.3720 0.0311
2.750 0.9158 0.00968 0.00243 -0.0994 0.3671 0.0318
3.000 0.9412 0.00976 0.00248 -0.0989 0.3609 0.0325
3.250 0.9668 0.00982 0.00253 -0.0985 0.3555 0.0347
3.500 0.9920 0.00991 0.00261 -0.0979 0.3471 0.0373
3.750 1.0170 0.01000 0.00270 -0.0974 0.3401 0.0453
4.000 1.0818 0.00870 0.00323 -0.1065 0.3272 1.0000
4.250 1.1053 0.00888 0.00335 -0.1056 0.3157 1.0000
4.500 1.1278 0.00911 0.00349 -0.1046 0.3016 1.0000
4.750 1.1492 0.00940 0.00368 -0.1035 0.2852 1.0000
5.000 1.1707 0.00968 0.00388 -0.1023 0.2713 1.0000
5.250 1.1923 0.00995 0.00407 -0.1012 0.2601 1.0000
5.500 1.2134 0.01024 0.00430 -0.0999 0.2491 1.0000
5.750 1.2345 0.01052 0.00452 -0.0987 0.2391 1.0000
6.000 1.2553 0.01081 0.00475 -0.0975 0.2290 1.0000
6.250 1.2755 0.01112 0.00501 -0.0962 0.2204 1.0000
6.500 1.2977 0.01132 0.00520 -0.0952 0.2166 1.0000
6.750 1.3196 0.01152 0.00540 -0.0942 0.2132 1.0000
7.000 1.3407 0.01175 0.00562 -0.0930 0.2098 1.0000
7.250 1.3611 0.01201 0.00587 -0.0918 0.2060 1.0000
7.500 1.3821 0.01223 0.00610 -0.0906 0.2031 1.0000
7.750 1.4019 0.01243 0.00632 -0.0892 0.2004 1.0000
8.000 1.4204 0.01267 0.00656 -0.0876 0.1971 1.0000
8.250 1.4383 0.01293 0.00683 -0.0859 0.1939 1.0000
8.500 1.4558 0.01322 0.00712 -0.0842 0.1907 1.0000
8.750 1.4745 0.01347 0.00740 -0.0827 0.1884 1.0000
9.000 1.4936 0.01372 0.00768 -0.0813 0.1854 1.0000
9.250 1.5109 0.01406 0.00801 -0.0797 0.1802 1.0000
9.500 1.5269 0.01447 0.00840 -0.0780 0.1740 1.0000
9.750 1.5436 0.01486 0.00878 -0.0764 0.1667 1.0000
10.000 1.5582 0.01536 0.00925 -0.0745 0.1584 1.0000
10.250 1.5710 0.01596 0.00980 -0.0725 0.1481 1.0000
10.500 1.5836 0.01659 0.01040 -0.0705 0.1379 1.0000
10.750 1.5960 0.01726 0.01104 -0.0686 0.1297 1.0000
11.000 1.6059 0.01808 0.01183 -0.0664 0.1203 1.0000
11.250 1.6150 0.01899 0.01271 -0.0643 0.1111 1.0000
11.500 1.6243 0.01993 0.01364 -0.0624 0.1030 1.0000
11.750 1.6317 0.02104 0.01472 -0.0603 0.0949 1.0000
12.000 1.6389 0.02223 0.01590 -0.0585 0.0878 1.0000
12.250 1.6469 0.02343 0.01711 -0.0568 0.0814 1.0000
12.500 1.6517 0.02492 0.01857 -0.0551 0.0744 1.0000
12.750 1.6557 0.02656 0.02021 -0.0535 0.0665 1.0000
13.000 1.6557 0.02859 0.02220 -0.0518 0.0566 1.0000
13.250 1.6436 0.03176 0.02528 -0.0497 0.0399 1.0000
13.500 1.6238 0.03583 0.02930 -0.0476 0.0205 1.0000
13.750 1.6188 0.03870 0.03222 -0.0465 0.0155 1.0000
14.000 1.6192 0.04114 0.03471 -0.0457 0.0137 1.0000
14.250 1.6210 0.04348 0.03713 -0.0451 0.0126 1.0000
14.500 1.6215 0.04601 0.03973 -0.0446 0.0116 1.0000
14.750 1.6216 0.04866 0.04245 -0.0442 0.0110 1.0000
15.000 1.6205 0.05148 0.04534 -0.0438 0.0102 1.0000
15.250 1.6202 0.05428 0.04823 -0.0436 0.0098 1.0000
15.500 1.6182 0.05736 0.05137 -0.0435 0.0091 1.0000
15.750 1.6157 0.06054 0.05464 -0.0435 0.0088 1.0000
16.000 1.6104 0.06411 0.05829 -0.0436 0.0082 1.0000
16.500 1.6018 0.07123 0.06558 -0.0441 0.0077 1.0000
16.750 1.5970 0.07494 0.06938 -0.0445 0.0075 1.0000
17.000 1.5906 0.07888 0.07341 -0.0451 0.0072 1.0000
17.250 1.5838 0.08292 0.07753 -0.0456 0.0070 1.0000
17.500 1.5756 0.08722 0.08193 -0.0464 0.0068 1.0000
17.750 1.5673 0.09159 0.08638 -0.0472 0.0066 1.0000
18.000 1.5567 0.09629 0.09118 -0.0482 0.0064 1.0000
18.250 1.5478 0.10080 0.09577 -0.0492 0.0062 1.0000
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