GOE 364 AIRFOIL (goe364-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
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Airfoil: GOE 364 AIRFOIL (goe364-il) Reynolds number: 1,000,000 Max Cl/Cd: 133.36 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe364-il-1000000.txt Download as CSV file: xf-goe364-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.2479 0.12818 0.12653 -0.0314 1.0000 0.0129
-11.500 -0.2452 0.12559 0.12395 -0.0314 1.0000 0.0133
-11.250 -0.2414 0.12224 0.12061 -0.0325 0.9998 0.0138
-11.000 -0.2286 0.11802 0.11639 -0.0369 0.9989 0.0139
-10.750 -0.2167 0.11359 0.11197 -0.0416 0.9974 0.0139
-10.500 -0.2024 0.10921 0.10759 -0.0442 0.9952 0.0141
-10.250 -0.1875 0.10607 0.10445 -0.0464 0.9919 0.0142
-10.000 -0.1720 0.10296 0.10134 -0.0492 0.9882 0.0144
-9.750 -0.1554 0.09954 0.09792 -0.0528 0.9843 0.0145
-9.500 -0.1413 0.09630 0.09467 -0.0557 0.9768 0.0147
-9.250 -0.1224 0.09266 0.09104 -0.0601 0.9712 0.0151
-9.000 -0.1018 0.08794 0.08628 -0.0669 0.9614 0.0167
-8.750 -0.0725 0.08170 0.08001 -0.0791 0.9506 0.0168
-8.500 -0.0399 0.07571 0.07395 -0.0892 0.9320 0.0169
-8.250 -0.0045 0.07218 0.07025 -0.0953 0.8890 0.0171
-8.000 0.0033 0.07045 0.06822 -0.0954 0.8296 0.0173
-7.750 0.0053 0.06881 0.06646 -0.0946 0.8011 0.0174
-7.500 0.0069 0.06731 0.06488 -0.0937 0.7820 0.0180
-7.250 0.0060 0.06517 0.06269 -0.0938 0.7668 0.0181
-7.000 0.0120 0.06273 0.06021 -0.0952 0.7541 0.0191
-6.750 0.0159 0.05737 0.05476 -0.1019 0.7430 0.0200
-6.500 0.0273 0.05351 0.05081 -0.1047 0.7331 0.0200
-6.250 0.0363 0.04934 0.04658 -0.1065 0.7247 0.0202
-6.000 0.0507 0.04772 0.04490 -0.1064 0.7157 0.0204
-5.750 0.0675 0.04574 0.04286 -0.1071 0.7080 0.0206
-5.500 0.0855 0.04386 0.04092 -0.1077 0.7001 0.0210
-5.250 0.1049 0.04171 0.03870 -0.1087 0.6932 0.0218
-5.000 0.1319 0.03508 0.03174 -0.1119 0.6870 0.0237
-4.750 0.1349 0.01645 0.01317 -0.1044 0.6682 0.0240
-4.500 0.1669 0.02996 0.02639 -0.1119 0.6739 0.0243
-4.250 0.1886 0.02871 0.02506 -0.1117 0.6670 0.0246
-4.000 0.2112 0.02733 0.02357 -0.1115 0.6605 0.0253
-3.750 0.2314 0.02111 0.01671 -0.1100 0.6551 0.0282
-3.250 0.2784 0.01941 0.01490 -0.1092 0.6409 0.0289
-3.000 0.3023 0.01858 0.01395 -0.1087 0.6329 0.0295
-2.750 0.3296 0.01806 0.01308 -0.1076 0.6248 0.0326
-2.500 0.3498 0.01538 0.01011 -0.1065 0.6167 0.0335
-2.250 0.3749 0.01468 0.00937 -0.1061 0.6077 0.0340
-0.750 0.5284 0.01051 0.00415 -0.1017 0.5412 0.0336
-0.500 0.5544 0.01036 0.00389 -0.1010 0.5259 0.0331
-0.250 0.5801 0.01024 0.00369 -0.1004 0.5099 0.0329
0.000 0.6048 0.00983 0.00320 -0.0997 0.4950 0.0332
0.250 0.6294 0.00957 0.00288 -0.0989 0.4817 0.0336
0.500 0.6542 0.00943 0.00268 -0.0982 0.4700 0.0339
0.750 0.6797 0.00931 0.00254 -0.0976 0.4606 0.0344
1.000 0.7050 0.00926 0.00245 -0.0969 0.4526 0.0350
1.250 0.7308 0.00920 0.00237 -0.0964 0.4455 0.0355
1.500 0.7561 0.00920 0.00233 -0.0958 0.4385 0.0360
1.750 0.7824 0.00916 0.00229 -0.0953 0.4331 0.0368
2.000 0.8082 0.00918 0.00228 -0.0949 0.4273 0.0379
2.250 0.8336 0.00922 0.00228 -0.0943 0.4215 0.0389
2.500 0.8598 0.00919 0.00226 -0.0939 0.4164 0.0407
2.750 0.8856 0.00923 0.00229 -0.0933 0.4106 0.0431
3.000 0.9110 0.00932 0.00234 -0.0928 0.4052 0.0468
3.250 0.9301 0.00852 0.00258 -0.0914 0.4012 0.5473
3.500 1.0114 0.00788 0.00285 -0.1035 0.3929 1.0000
3.750 1.0359 0.00801 0.00294 -0.1028 0.3876 1.0000
4.000 1.0609 0.00811 0.00302 -0.1022 0.3819 1.0000
4.250 1.0847 0.00827 0.00313 -0.1014 0.3752 1.0000
4.500 1.1095 0.00838 0.00323 -0.1007 0.3693 1.0000
4.750 1.1336 0.00852 0.00334 -0.1000 0.3620 1.0000
5.000 1.1576 0.00868 0.00346 -0.0992 0.3543 1.0000
5.250 1.1809 0.00886 0.00360 -0.0984 0.3437 1.0000
5.500 1.2040 0.00905 0.00374 -0.0975 0.3306 1.0000
5.750 1.2255 0.00933 0.00392 -0.0963 0.3127 1.0000
6.000 1.2461 0.00965 0.00413 -0.0950 0.2926 1.0000
6.250 1.2662 0.01000 0.00438 -0.0937 0.2750 1.0000
6.500 1.2866 0.01032 0.00463 -0.0923 0.2621 1.0000
6.750 1.3065 0.01066 0.00490 -0.0910 0.2512 1.0000
7.000 1.3279 0.01091 0.00513 -0.0898 0.2439 1.0000
7.250 1.3477 0.01123 0.00541 -0.0885 0.2368 1.0000
7.500 1.3694 0.01144 0.00564 -0.0874 0.2324 1.0000
7.750 1.3898 0.01171 0.00589 -0.0862 0.2276 1.0000
8.000 1.4086 0.01204 0.00620 -0.0846 0.2220 1.0000
8.250 1.4298 0.01225 0.00644 -0.0835 0.2188 1.0000
8.500 1.4485 0.01252 0.00671 -0.0820 0.2138 1.0000
8.750 1.4643 0.01285 0.00703 -0.0799 0.2086 1.0000
9.000 1.4822 0.01311 0.00730 -0.0782 0.2046 1.0000
9.250 1.5006 0.01336 0.00757 -0.0767 0.2007 1.0000
9.500 1.5176 0.01368 0.00790 -0.0749 0.1968 1.0000
9.750 1.5331 0.01409 0.00830 -0.0730 0.1916 1.0000
10.000 1.5526 0.01433 0.00859 -0.0718 0.1882 1.0000
10.250 1.5699 0.01468 0.00894 -0.0703 0.1832 1.0000
10.500 1.5848 0.01515 0.00939 -0.0684 0.1768 1.0000
10.750 1.6025 0.01550 0.00977 -0.0671 0.1712 1.0000
11.000 1.6163 0.01605 0.01030 -0.0652 0.1640 1.0000
11.250 1.6319 0.01653 0.01079 -0.0637 0.1565 1.0000
11.500 1.6442 0.01720 0.01142 -0.0618 0.1479 1.0000
11.750 1.6547 0.01799 0.01218 -0.0597 0.1379 1.0000
12.000 1.6650 0.01882 0.01299 -0.0578 0.1285 1.0000
12.250 1.6730 0.01983 0.01397 -0.0557 0.1188 1.0000
12.500 1.6799 0.02098 0.01509 -0.0537 0.1101 1.0000
12.750 1.6841 0.02237 0.01644 -0.0516 0.1005 1.0000
13.000 1.6892 0.02378 0.01784 -0.0498 0.0921 1.0000
13.250 1.6938 0.02530 0.01936 -0.0482 0.0843 1.0000
13.500 1.6961 0.02710 0.02114 -0.0465 0.0764 1.0000
13.750 1.6951 0.02924 0.02325 -0.0449 0.0666 1.0000
14.000 1.6888 0.03193 0.02588 -0.0433 0.0537 1.0000
14.250 1.6648 0.03640 0.03023 -0.0412 0.0330 1.0000
14.500 1.6437 0.04090 0.03471 -0.0398 0.0202 1.0000
14.750 1.6376 0.04406 0.03794 -0.0391 0.0173 1.0000
15.000 1.6331 0.04717 0.04112 -0.0386 0.0159 1.0000
15.250 1.6268 0.05057 0.04460 -0.0382 0.0148 1.0000
15.500 1.6236 0.05370 0.04782 -0.0380 0.0141 1.0000
15.750 1.6204 0.05691 0.05113 -0.0380 0.0138 1.0000
16.000 1.6156 0.06040 0.05471 -0.0381 0.0133 1.0000
16.250 1.6093 0.06414 0.05854 -0.0383 0.0129 1.0000
16.500 1.5995 0.06843 0.06292 -0.0387 0.0123 1.0000
16.750 1.5890 0.07291 0.06751 -0.0393 0.0120 1.0000
17.000 1.5751 0.07793 0.07265 -0.0401 0.0116 1.0000
17.250 1.5682 0.08203 0.07685 -0.0407 0.0115 1.0000
17.500 1.5596 0.08641 0.08133 -0.0415 0.0113 1.0000
17.750 1.5505 0.09092 0.08593 -0.0425 0.0111 1.0000
18.000 1.5393 0.09576 0.09089 -0.0435 0.0109 1.0000
18.250 1.5273 0.10076 0.09598 -0.0448 0.0107 1.0000
18.500 1.5161 0.10573 0.10105 -0.0461 0.0106 1.0000
18.750 1.5035 0.11100 0.10642 -0.0476 0.0104 1.0000
19.000 1.4909 0.11633 0.11185 -0.0493 0.0103 1.0000
19.250 1.4787 0.12166 0.11728 -0.0511 0.0101 1.0000
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