GOE 381 AIRFOIL (goe381-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: GOE 381 AIRFOIL (goe381-il) Reynolds number: 500,000 Max Cl/Cd: 100.71 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe381-il-500000.txt Download as CSV file: xf-goe381-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 381 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.2894 0.09915 0.09714 -0.0233 1.0000 0.0122
-7.750 -0.2925 0.09756 0.09559 -0.0235 1.0000 0.0122
-7.500 -0.2899 0.09297 0.09104 -0.0211 0.9999 0.0125
-7.250 -0.2710 0.08892 0.08698 -0.0248 0.9955 0.0127
-7.000 -0.2485 0.08500 0.08306 -0.0303 0.9904 0.0131
-6.750 -0.2239 0.08106 0.07911 -0.0365 0.9847 0.0135
-6.500 -0.1993 0.07722 0.07525 -0.0424 0.9771 0.0139
-6.250 -0.1732 0.07332 0.07133 -0.0485 0.9698 0.0146
-6.000 -0.1507 0.06980 0.06778 -0.0533 0.9592 0.0153
-5.750 -0.1201 0.06645 0.06437 -0.0602 0.9486 0.0163
-5.500 -0.0875 0.06311 0.06093 -0.0675 0.9389 0.0165
-5.250 -0.0606 0.05965 0.05738 -0.0717 0.9292 0.0166
-5.000 -0.0342 0.05608 0.05372 -0.0751 0.9199 0.0166
-4.750 -0.0230 0.05125 0.04886 -0.0757 0.9113 0.0171
-4.500 -0.0039 0.04866 0.04623 -0.0766 0.9013 0.0177
-4.250 0.0207 0.04613 0.04362 -0.0786 0.8915 0.0188
-4.000 0.0505 0.04351 0.04087 -0.0811 0.8819 0.0210
-3.750 0.0929 0.04128 0.03840 -0.0848 0.8716 0.0223
-3.500 0.1237 0.03846 0.03542 -0.0866 0.8610 0.0225
-3.250 0.1539 0.03545 0.03222 -0.0881 0.8505 0.0226
-3.000 0.1798 0.03021 0.02676 -0.0903 0.8402 0.0235
-2.750 0.2032 0.02858 0.02505 -0.0907 0.8270 0.0246
-2.500 0.2301 0.02711 0.02344 -0.0912 0.8118 0.0275
-2.250 0.2653 0.02637 0.02241 -0.0909 0.7941 0.0310
-2.000 0.2951 0.02435 0.02008 -0.0910 0.7744 0.0312
-1.750 0.3209 0.02044 0.01588 -0.0922 0.7519 0.0336
-1.500 0.3465 0.01963 0.01487 -0.0922 0.7216 0.0367
-1.250 0.3773 0.01978 0.01464 -0.0912 0.6905 0.0425
-1.000 0.4033 0.01704 0.01161 -0.0919 0.6639 0.0458
-0.750 0.4300 0.01650 0.01086 -0.0918 0.6390 0.0503
-0.500 0.4580 0.01566 0.00973 -0.0917 0.6175 0.0581
-0.250 0.4850 0.01526 0.00916 -0.0916 0.5987 0.0636
0.000 0.5132 0.01448 0.00812 -0.0915 0.5829 0.0706
0.250 0.5406 0.01394 0.00746 -0.0914 0.5696 0.0742
0.500 0.5693 0.01474 0.00803 -0.0908 0.5575 0.0809
0.750 0.5990 0.01076 0.00361 -0.0903 0.5488 0.0425
1.000 0.6262 0.01029 0.00304 -0.0901 0.5385 0.0427
1.250 0.6534 0.00988 0.00255 -0.0900 0.5283 0.0438
1.500 0.6809 0.00970 0.00232 -0.0899 0.5180 0.0450
1.750 0.7084 0.00964 0.00222 -0.0898 0.5078 0.0466
2.000 0.7357 0.00964 0.00219 -0.0897 0.4971 0.0495
2.250 0.7631 0.00965 0.00216 -0.0897 0.4855 0.0518
2.500 0.7906 0.00968 0.00217 -0.0896 0.4724 0.0574
2.750 0.8176 0.00976 0.00227 -0.0895 0.4558 0.0937
3.000 0.8447 0.00986 0.00236 -0.0894 0.4358 0.1146
3.250 0.8712 0.01002 0.00245 -0.0892 0.4122 0.1280
3.500 0.8973 0.01023 0.00258 -0.0890 0.3818 0.1408
3.750 0.9227 0.00998 0.00284 -0.0892 0.3488 0.5292
4.000 0.9447 0.00938 0.00303 -0.0881 0.3220 1.0000
4.250 0.9700 0.00977 0.00325 -0.0878 0.2979 1.0000
4.500 0.9950 0.01018 0.00351 -0.0875 0.2737 1.0000
4.750 1.0206 0.01051 0.00375 -0.0873 0.2590 1.0000
5.250 1.0716 0.01114 0.00422 -0.0868 0.2312 1.0000
5.500 1.0971 0.01145 0.00449 -0.0866 0.2178 1.0000
5.750 1.1221 0.01181 0.00475 -0.0863 0.1970 1.0000
6.000 1.1434 0.01266 0.00518 -0.0857 0.1342 1.0000
6.250 1.1651 0.01345 0.00576 -0.0850 0.1050 1.0000
6.750 1.2049 0.01551 0.00744 -0.0829 0.0183 1.0000
7.000 1.2284 0.01603 0.00810 -0.0823 0.0160 1.0000
7.250 1.2513 0.01661 0.00880 -0.0815 0.0153 1.0000
7.500 1.2732 0.01730 0.00962 -0.0807 0.0146 1.0000
7.750 1.2936 0.01814 0.01058 -0.0796 0.0140 1.0000
8.000 1.3128 0.01906 0.01164 -0.0784 0.0131 1.0000
8.250 1.3301 0.02012 0.01280 -0.0771 0.0122 1.0000
8.500 1.3452 0.02133 0.01411 -0.0754 0.0117 1.0000
8.750 1.3573 0.02271 0.01561 -0.0733 0.0114 1.0000
9.000 1.3657 0.02429 0.01730 -0.0708 0.0111 1.0000
9.250 1.3701 0.02598 0.01909 -0.0678 0.0109 1.0000
9.500 1.3724 0.02768 0.02087 -0.0644 0.0108 1.0000
9.750 1.3769 0.02933 0.02263 -0.0616 0.0109 1.0000
10.000 1.3847 0.03083 0.02424 -0.0593 0.0112 1.0000
10.250 1.3952 0.03290 0.02650 -0.0565 0.0137 1.0000
10.500 1.4329 0.03477 0.02846 -0.0557 0.0204 1.0000
10.750 1.4453 0.03661 0.03038 -0.0541 0.0191 1.0000
11.000 1.4605 0.03886 0.03265 -0.0530 0.0178 1.0000
14.250 1.2211 0.08019 0.07641 -0.0256 0.0126 1.0000
14.500 1.2008 0.08535 0.08173 -0.0266 0.0126 1.0000
14.750 1.1785 0.09053 0.08706 -0.0278 0.0126 1.0000
15.000 1.1502 0.09522 0.09191 -0.0289 0.0127 1.0000
15.250 1.1247 0.10011 0.09695 -0.0307 0.0128 1.0000
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Polar data table (+)
Polar graphs
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