GOE 178 AIRFOIL (goe178-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 178 AIRFOIL (goe178-il) Reynolds number: 1,000,000 Max Cl/Cd: 110.48 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe178-il-1000000-n5.txt Download as CSV file: xf-goe178-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 178 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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.5000 0.15472 0.15308 0.0144 1.0000 0.0038
-12.500 -0.4871 0.14785 0.14622 0.0115 1.0000 0.0041
-10.000 -0.6760 0.02028 0.01719 -0.0850 0.9952 0.0075
-9.750 -0.6467 0.01820 0.01487 -0.0869 0.9888 0.0083
-9.500 -0.6169 0.01674 0.01320 -0.0883 0.9798 0.0091
-9.250 -0.5896 0.01563 0.01190 -0.0888 0.9697 0.0099
-9.000 -0.5631 0.01500 0.01118 -0.0888 0.9621 0.0110
-8.750 -0.5363 0.01478 0.01097 -0.0886 0.9551 0.0120
-8.500 -0.5100 0.01443 0.01055 -0.0883 0.9477 0.0130
-8.250 -0.4842 0.01377 0.00974 -0.0881 0.9381 0.0139
-8.000 -0.4571 0.01393 0.00993 -0.0877 0.9273 0.0145
-7.750 -0.4303 0.01411 0.01011 -0.0872 0.9116 0.0151
-7.500 -0.4048 0.01422 0.01014 -0.0864 0.8820 0.0159
-7.250 -0.3793 0.01420 0.00994 -0.0858 0.8461 0.0167
-6.750 -0.3252 0.01372 0.00908 -0.0855 0.7983 0.0181
-6.500 -0.2975 0.01364 0.00886 -0.0854 0.7776 0.0185
-6.250 -0.2696 0.01365 0.00874 -0.0853 0.7558 0.0188
-6.000 -0.2423 0.01275 0.00761 -0.0855 0.7316 0.0196
-5.750 -0.2145 0.01261 0.00735 -0.0856 0.7027 0.0201
-5.500 -0.1867 0.01252 0.00710 -0.0856 0.6686 0.0206
-5.250 -0.1588 0.01242 0.00684 -0.0857 0.6342 0.0212
-5.000 -0.1308 0.01224 0.00648 -0.0857 0.6030 0.0218
-4.750 -0.1027 0.01196 0.00601 -0.0858 0.5755 0.0223
-4.500 -0.0745 0.01172 0.00561 -0.0859 0.5513 0.0229
-4.250 -0.0462 0.01145 0.00519 -0.0860 0.5303 0.0233
-4.000 -0.0178 0.01116 0.00476 -0.0862 0.5115 0.0236
-3.750 0.0106 0.01088 0.00434 -0.0863 0.4961 0.0238
-3.500 0.0391 0.01061 0.00396 -0.0864 0.4841 0.0240
-3.250 0.0676 0.01036 0.00361 -0.0865 0.4743 0.0242
-3.000 0.0962 0.01012 0.00329 -0.0866 0.4659 0.0244
-2.750 0.1248 0.00993 0.00303 -0.0867 0.4588 0.0246
-2.500 0.1535 0.00978 0.00283 -0.0868 0.4524 0.0249
-2.000 0.2109 0.00946 0.00239 -0.0870 0.4403 0.0252
-1.750 0.2395 0.00934 0.00221 -0.0871 0.4339 0.0254
-1.500 0.2682 0.00925 0.00207 -0.0872 0.4286 0.0256
-1.250 0.2970 0.00909 0.00188 -0.0874 0.4237 0.0261
-1.000 0.3257 0.00895 0.00167 -0.0875 0.4186 0.0272
-0.750 0.3544 0.00888 0.00156 -0.0876 0.4147 0.0281
-0.500 0.3832 0.00882 0.00149 -0.0877 0.4113 0.0288
-0.250 0.4118 0.00878 0.00143 -0.0878 0.4072 0.0295
0.000 0.4404 0.00876 0.00139 -0.0879 0.4030 0.0301
0.250 0.4690 0.00875 0.00136 -0.0880 0.3995 0.0307
0.500 0.4977 0.00873 0.00134 -0.0881 0.3961 0.0313
0.750 0.5262 0.00873 0.00132 -0.0882 0.3919 0.0319
1.000 0.5547 0.00875 0.00132 -0.0882 0.3870 0.0332
1.500 0.6117 0.00872 0.00136 -0.0885 0.3750 0.0650
1.750 0.6401 0.00874 0.00141 -0.0886 0.3705 0.0776
2.000 0.6685 0.00876 0.00145 -0.0886 0.3667 0.0817
2.250 0.6968 0.00880 0.00149 -0.0887 0.3591 0.0884
2.500 0.7251 0.00884 0.00155 -0.0888 0.3530 0.0975
2.750 0.7536 0.00876 0.00164 -0.0890 0.3451 0.1772
3.000 0.7819 0.00869 0.00174 -0.0893 0.3351 0.2713
3.250 0.8070 0.00755 0.00201 -0.0893 0.3222 0.8721
3.750 0.8595 0.00778 0.00221 -0.0886 0.2800 1.0000
4.000 0.8863 0.00813 0.00241 -0.0886 0.2526 1.0000
4.250 0.9121 0.00868 0.00272 -0.0884 0.2124 1.0000
4.500 0.9389 0.00901 0.00295 -0.0884 0.1914 1.0000
4.750 0.9596 0.01047 0.00379 -0.0877 0.0657 1.0000
5.000 0.9863 0.01077 0.00405 -0.0876 0.0554 1.0000
5.250 1.0133 0.01100 0.00427 -0.0876 0.0507 1.0000
5.500 1.0399 0.01130 0.00455 -0.0874 0.0441 1.0000
5.750 1.0666 0.01154 0.00479 -0.0873 0.0390 1.0000
6.000 1.0917 0.01207 0.00517 -0.0871 0.0174 1.0000
6.250 1.1178 0.01238 0.00549 -0.0869 0.0130 1.0000
6.500 1.1440 0.01268 0.00582 -0.0867 0.0117 1.0000
6.750 1.1697 0.01303 0.00619 -0.0864 0.0104 1.0000
7.000 1.1948 0.01346 0.00665 -0.0861 0.0089 1.0000
7.250 1.2204 0.01379 0.00702 -0.0858 0.0084 1.0000
7.500 1.2456 0.01415 0.00740 -0.0856 0.0077 1.0000
7.750 1.2703 0.01455 0.00783 -0.0852 0.0071 1.0000
8.000 1.2945 0.01501 0.00830 -0.0848 0.0066 1.0000
8.250 1.3175 0.01562 0.00896 -0.0842 0.0060 1.0000
8.500 1.3413 0.01607 0.00947 -0.0837 0.0058 1.0000
8.750 1.3645 0.01658 0.01003 -0.0832 0.0055 1.0000
9.000 1.3871 0.01711 0.01061 -0.0826 0.0052 1.0000
9.250 1.4095 0.01765 0.01118 -0.0819 0.0049 1.0000
9.500 1.4315 0.01818 0.01175 -0.0813 0.0046 1.0000
9.750 1.4525 0.01879 0.01239 -0.0805 0.0044 1.0000
10.000 1.4710 0.01961 0.01329 -0.0794 0.0041 1.0000
10.250 1.4882 0.02051 0.01426 -0.0781 0.0039 1.0000
10.500 1.5062 0.02125 0.01508 -0.0769 0.0038 1.0000
10.750 1.5226 0.02207 0.01597 -0.0755 0.0037 1.0000
11.000 1.5373 0.02296 0.01694 -0.0739 0.0036 1.0000
11.250 1.5498 0.02392 0.01798 -0.0721 0.0035 1.0000
11.500 1.5575 0.02492 0.01908 -0.0695 0.0034 1.0000
11.750 1.5633 0.02609 0.02034 -0.0669 0.0033 1.0000
12.000 1.5680 0.02744 0.02179 -0.0645 0.0032 1.0000
12.250 1.5724 0.02897 0.02340 -0.0626 0.0032 1.0000
12.500 1.5758 0.03074 0.02527 -0.0609 0.0031 1.0000
12.750 1.5777 0.03288 0.02751 -0.0598 0.0031 1.0000
13.000 1.5802 0.03519 0.02991 -0.0591 0.0030 1.0000
13.250 1.5812 0.03786 0.03269 -0.0588 0.0029 1.0000
13.500 1.5802 0.04098 0.03592 -0.0588 0.0029 1.0000
13.750 1.5795 0.04424 0.03928 -0.0592 0.0028 1.0000
14.000 1.5760 0.04802 0.04317 -0.0599 0.0028 1.0000
14.250 1.5718 0.05200 0.04725 -0.0607 0.0028 1.0000
14.500 1.5650 0.05635 0.05171 -0.0617 0.0027 1.0000
14.750 1.5571 0.06087 0.05634 -0.0626 0.0027 1.0000
15.000 1.5478 0.06559 0.06118 -0.0637 0.0027 1.0000
15.250 1.5366 0.07052 0.06622 -0.0647 0.0026 1.0000
15.500 1.5249 0.07563 0.07143 -0.0659 0.0026 1.0000
15.750 1.5129 0.08082 0.07674 -0.0671 0.0026 1.0000
16.000 1.4987 0.08642 0.08244 -0.0685 0.0025 1.0000
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