GOE 318 (HANSA-BRANDENBURG VI.5) AIRFOIL (goe318-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 318 (HANSA-BRANDENBURG VI.5) AIRFOIL (goe318-il) Reynolds number: 50,000 Max Cl/Cd: 35.54 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe318-il-50000-n5.txt Download as CSV file: xf-goe318-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 318 (HANSA-BRANDENBURG VI.5) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4207 0.11969 0.11350 0.0067 1.0000 0.0939
-9.000 -0.4226 0.11792 0.11182 0.0024 1.0000 0.0970
-8.750 -0.4275 0.11651 0.11054 -0.0031 1.0000 0.0979
-8.500 -0.4107 0.11024 0.10430 -0.0018 1.0000 0.0999
-8.250 -0.3961 0.10583 0.09991 -0.0014 1.0000 0.1035
-8.000 -0.3892 0.10264 0.09679 -0.0035 1.0000 0.1083
-7.750 -0.3921 0.10085 0.09513 -0.0105 1.0000 0.1126
-7.500 -0.3835 0.09660 0.09096 -0.0140 1.0000 0.1149
-7.250 -0.3674 0.09240 0.08680 -0.0119 1.0000 0.1211
-7.000 -0.3610 0.08998 0.08443 -0.0219 1.0000 0.1284
-6.750 -0.3490 0.08556 0.08009 -0.0242 1.0000 0.1308
-6.500 -0.3358 0.08185 0.07643 -0.0238 1.0000 0.1346
-6.250 -0.3092 0.07845 0.07281 -0.0383 0.9514 0.1448
-6.000 -0.2887 0.07355 0.06797 -0.0357 0.9351 0.1503
-5.750 -0.2658 0.06980 0.06408 -0.0415 0.9167 0.1629
-5.250 -0.1973 0.05865 0.05193 -0.0577 0.8874 0.0976
-5.000 -0.1698 0.05369 0.04650 -0.0610 0.8750 0.0834
-4.750 -0.1461 0.05051 0.04303 -0.0625 0.8634 0.0833
-4.500 -0.1225 0.04753 0.03976 -0.0635 0.8528 0.0829
-4.250 -0.0993 0.04473 0.03676 -0.0640 0.8431 0.0814
-4.000 -0.0740 0.04209 0.03382 -0.0649 0.8327 0.0797
-3.750 -0.0476 0.03964 0.03099 -0.0655 0.8235 0.0783
-3.500 -0.0207 0.03742 0.02835 -0.0659 0.8147 0.0776
-3.250 0.0069 0.03561 0.02610 -0.0664 0.8054 0.0794
-3.000 0.0344 0.03397 0.02399 -0.0663 0.7977 0.0809
-2.750 0.0625 0.03242 0.02208 -0.0665 0.7883 0.0809
-2.500 0.0901 0.03104 0.02034 -0.0663 0.7806 0.0809
-2.250 0.1181 0.02985 0.01881 -0.0662 0.7719 0.0812
-2.000 0.1460 0.02883 0.01747 -0.0659 0.7641 0.0818
-1.750 0.1739 0.02796 0.01632 -0.0656 0.7557 0.0828
-1.500 0.2010 0.02721 0.01545 -0.0653 0.7477 0.0859
-1.250 0.2278 0.02668 0.01482 -0.0648 0.7397 0.0906
-1.000 0.2559 0.02621 0.01416 -0.0645 0.7314 0.0943
-0.750 0.2832 0.02575 0.01348 -0.0638 0.7236 0.0971
-0.500 0.3099 0.02536 0.01305 -0.0635 0.7149 0.1009
-0.250 0.3361 0.02501 0.01262 -0.0628 0.7074 0.1069
0.000 0.3630 0.02481 0.01237 -0.0627 0.6981 0.1163
0.250 0.3890 0.02446 0.01205 -0.0619 0.6909 0.1401
0.500 0.4126 0.02297 0.01197 -0.0620 0.6808 0.4342
0.750 0.4440 0.02197 0.01160 -0.0612 0.6703 1.0000
1.000 0.4691 0.02204 0.01133 -0.0598 0.6601 1.0000
1.250 0.4944 0.02220 0.01127 -0.0591 0.6469 1.0000
1.500 0.5197 0.02236 0.01124 -0.0583 0.6342 1.0000
1.750 0.5451 0.02252 0.01122 -0.0575 0.6223 1.0000
2.000 0.5706 0.02261 0.01113 -0.0566 0.6122 1.0000
2.250 0.5964 0.02283 0.01126 -0.0561 0.6007 1.0000
2.500 0.6221 0.02310 0.01146 -0.0557 0.5890 1.0000
2.750 0.6478 0.02331 0.01159 -0.0551 0.5781 1.0000
3.000 0.6736 0.02343 0.01162 -0.0543 0.5682 1.0000
3.250 0.6991 0.02374 0.01191 -0.0540 0.5556 1.0000
3.500 0.7246 0.02402 0.01219 -0.0536 0.5432 1.0000
3.750 0.7501 0.02428 0.01244 -0.0531 0.5313 1.0000
4.000 0.7757 0.02449 0.01262 -0.0525 0.5201 1.0000
4.250 0.8012 0.02469 0.01281 -0.0519 0.5086 1.0000
4.500 0.8263 0.02504 0.01321 -0.0515 0.4955 1.0000
4.750 0.8512 0.02540 0.01358 -0.0510 0.4826 1.0000
5.000 0.8762 0.02576 0.01397 -0.0506 0.4702 1.0000
5.250 0.9011 0.02612 0.01435 -0.0500 0.4587 1.0000
5.500 0.9265 0.02640 0.01460 -0.0494 0.4487 1.0000
5.750 0.9506 0.02705 0.01534 -0.0491 0.4371 1.0000
6.000 0.9749 0.02768 0.01604 -0.0487 0.4272 1.0000
6.250 1.0001 0.02814 0.01653 -0.0482 0.4193 1.0000
6.500 1.0232 0.02904 0.01758 -0.0480 0.4098 1.0000
6.750 1.0484 0.02954 0.01810 -0.0475 0.4032 1.0000
7.000 1.0704 0.03061 0.01940 -0.0473 0.3945 1.0000
7.250 1.0957 0.03115 0.01999 -0.0468 0.3889 1.0000
7.500 1.1163 0.03249 0.02160 -0.0467 0.3816 1.0000
7.750 1.1399 0.03337 0.02264 -0.0464 0.3766 1.0000
8.000 1.1626 0.03444 0.02392 -0.0461 0.3720 1.0000
8.250 1.1811 0.03605 0.02584 -0.0459 0.3664 1.0000
8.500 1.2036 0.03707 0.02706 -0.0455 0.3618 1.0000
8.750 1.2247 0.03829 0.02852 -0.0451 0.3574 1.0000
9.000 1.2378 0.04042 0.03101 -0.0449 0.3517 1.0000
9.250 1.2604 0.04129 0.03214 -0.0443 0.3466 1.0000
9.500 1.2721 0.04289 0.03404 -0.0435 0.3373 1.0000
9.750 1.2914 0.04289 0.03421 -0.0421 0.3242 1.0000
10.000 1.3086 0.04228 0.03368 -0.0402 0.3053 1.0000
10.250 1.3160 0.04218 0.03359 -0.0380 0.2821 1.0000
10.500 1.3131 0.04340 0.03488 -0.0362 0.2608 1.0000
10.750 1.3062 0.04522 0.03680 -0.0345 0.2430 1.0000
11.000 1.2978 0.04799 0.03972 -0.0341 0.2272 1.0000
11.250 1.2886 0.05136 0.04326 -0.0343 0.2102 1.0000
11.500 1.2750 0.05590 0.04809 -0.0354 0.1922 1.0000
11.750 1.2570 0.06165 0.05419 -0.0373 0.1725 1.0000
12.000 1.2448 0.06580 0.05803 -0.0381 0.1292 1.0000
12.250 1.2274 0.07096 0.06279 -0.0392 0.1109 1.0000
12.500 1.2092 0.07673 0.06841 -0.0407 0.1001 1.0000
12.750 1.1919 0.08261 0.07422 -0.0423 0.0914 1.0000
13.000 1.1772 0.08831 0.07992 -0.0438 0.0836 1.0000
13.250 1.1635 0.09395 0.08547 -0.0454 0.0779 1.0000
13.500 1.1544 0.09902 0.09058 -0.0468 0.0717 1.0000
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Polar data table (+)
Polar graphs
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