GOE 178 AIRFOIL (goe178-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: GOE 178 AIRFOIL (goe178-il) Reynolds number: 500,000 Max Cl/Cd: 104.53 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe178-il-500000.txt Download as CSV file: xf-goe178-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3773 0.09436 0.09222 -0.0170 1.0000 0.0236
-8.000 -0.3729 0.09070 0.08859 -0.0205 1.0000 0.0238
-7.750 -0.3685 0.08705 0.08497 -0.0232 1.0000 0.0239
-7.500 -0.3604 0.08280 0.08074 -0.0274 1.0000 0.0239
-7.250 -0.3609 0.07630 0.07428 -0.0321 1.0000 0.0243
-7.000 -0.3567 0.07353 0.07152 -0.0320 1.0000 0.0247
-6.750 -0.3514 0.07135 0.06936 -0.0318 1.0000 0.0251
-6.500 -0.3357 0.06856 0.06657 -0.0343 0.9982 0.0257
-6.250 -0.3030 0.06412 0.06209 -0.0421 0.9943 0.0271
-6.000 -0.2483 0.05601 0.05381 -0.0594 0.9880 0.0311
-5.750 -0.2151 0.04540 0.04301 -0.0717 0.9829 0.0323
-5.500 -0.1875 0.04339 0.04094 -0.0742 0.9746 0.0333
-5.250 -0.1573 0.04068 0.03815 -0.0775 0.9652 0.0350
-5.000 -0.1195 0.03169 0.02861 -0.0853 0.9545 0.0418
-4.750 -0.0976 0.03106 0.02799 -0.0849 0.9392 0.0430
-4.500 -0.0744 0.02971 0.02653 -0.0848 0.9205 0.0451
-4.000 -0.0160 0.01800 0.01325 -0.0871 0.8762 0.0408
-3.750 0.0093 0.01506 0.00986 -0.0868 0.8480 0.0384
-3.500 0.0358 0.01358 0.00797 -0.0863 0.8201 0.0380
-3.250 0.0628 0.01267 0.00674 -0.0859 0.7932 0.0381
-3.000 0.0901 0.01205 0.00588 -0.0856 0.7645 0.0389
-2.750 0.1176 0.01144 0.00502 -0.0853 0.7305 0.0391
-2.500 0.1449 0.01102 0.00433 -0.0850 0.6887 0.0395
-2.250 0.1722 0.01075 0.00380 -0.0847 0.6446 0.0398
-2.000 0.1998 0.01056 0.00337 -0.0846 0.6069 0.0402
-1.750 0.2277 0.01036 0.00299 -0.0846 0.5778 0.0405
-1.500 0.2559 0.01012 0.00259 -0.0846 0.5558 0.0416
-1.250 0.2843 0.00997 0.00233 -0.0846 0.5389 0.0437
-1.000 0.3127 0.00990 0.00217 -0.0847 0.5252 0.0457
-0.750 0.3411 0.00987 0.00205 -0.0847 0.5134 0.0486
-0.500 0.3696 0.00981 0.00199 -0.0847 0.5030 0.0584
-0.250 0.3980 0.00979 0.00199 -0.0848 0.4947 0.0801
0.000 0.4264 0.00981 0.00198 -0.0848 0.4873 0.0939
0.250 0.4547 0.00984 0.00199 -0.0848 0.4804 0.1045
0.500 0.4830 0.00983 0.00199 -0.0849 0.4736 0.1176
0.750 0.5113 0.00981 0.00202 -0.0850 0.4677 0.1446
1.000 0.5398 0.00958 0.00208 -0.0853 0.4618 0.2508
1.250 0.5664 0.00851 0.00227 -0.0857 0.4570 0.7178
1.500 0.5894 0.00803 0.00227 -0.0842 0.4530 1.0000
1.750 0.6179 0.00811 0.00231 -0.0842 0.4477 1.0000
2.000 0.6460 0.00825 0.00237 -0.0842 0.4415 1.0000
2.250 0.6743 0.00836 0.00243 -0.0842 0.4360 1.0000
2.500 0.7025 0.00846 0.00250 -0.0843 0.4310 1.0000
2.750 0.7305 0.00862 0.00259 -0.0843 0.4262 1.0000
3.000 0.7587 0.00873 0.00270 -0.0843 0.4218 1.0000
3.250 0.7869 0.00882 0.00280 -0.0843 0.4171 1.0000
3.500 0.8148 0.00897 0.00290 -0.0843 0.4123 1.0000
3.750 0.8427 0.00910 0.00303 -0.0843 0.4072 1.0000
4.000 0.8708 0.00918 0.00313 -0.0844 0.4006 1.0000
4.250 0.8984 0.00933 0.00325 -0.0843 0.3937 1.0000
4.500 0.9265 0.00941 0.00336 -0.0843 0.3865 1.0000
4.750 0.9541 0.00952 0.00346 -0.0843 0.3763 1.0000
5.000 0.9816 0.00965 0.00357 -0.0843 0.3650 1.0000
5.250 1.0093 0.00976 0.00369 -0.0843 0.3532 1.0000
5.500 1.0365 0.00992 0.00383 -0.0842 0.3357 1.0000
5.750 1.0631 0.01017 0.00399 -0.0841 0.3062 1.0000
6.000 1.0883 0.01065 0.00427 -0.0839 0.2675 1.0000
6.250 1.1129 0.01123 0.00467 -0.0836 0.2337 1.0000
6.500 1.1370 0.01187 0.00516 -0.0832 0.2003 1.0000
6.750 1.1514 0.01404 0.00652 -0.0820 0.0632 1.0000
7.000 1.1749 0.01475 0.00719 -0.0814 0.0444 1.0000
7.250 1.1980 0.01546 0.00779 -0.0808 0.0247 1.0000
7.500 1.2211 0.01616 0.00851 -0.0801 0.0204 1.0000
7.750 1.2443 0.01679 0.00923 -0.0795 0.0189 1.0000
8.000 1.2663 0.01753 0.01006 -0.0787 0.0174 1.0000
8.250 1.2864 0.01848 0.01109 -0.0777 0.0162 1.0000
8.500 1.3025 0.01982 0.01258 -0.0762 0.0153 1.0000
8.750 1.3198 0.02089 0.01376 -0.0748 0.0149 1.0000
9.000 1.3368 0.02191 0.01489 -0.0734 0.0145 1.0000
9.250 1.3515 0.02307 0.01616 -0.0717 0.0141 1.0000
9.500 1.3642 0.02431 0.01749 -0.0698 0.0137 1.0000
9.750 1.3755 0.02557 0.01884 -0.0678 0.0132 1.0000
10.000 1.3842 0.02686 0.02020 -0.0655 0.0127 1.0000
10.250 1.3884 0.02824 0.02166 -0.0626 0.0123 1.0000
10.500 1.3907 0.02992 0.02343 -0.0599 0.0120 1.0000
10.750 1.3921 0.03187 0.02545 -0.0575 0.0118 1.0000
11.000 1.3931 0.03407 0.02772 -0.0553 0.0116 1.0000
11.250 1.3951 0.03646 0.03019 -0.0533 0.0114 1.0000
11.500 1.3998 0.03905 0.03286 -0.0511 0.0112 1.0000
11.750 1.4103 0.04171 0.03562 -0.0491 0.0111 1.0000
12.000 1.4159 0.04407 0.03813 -0.0477 0.0110 1.0000
12.250 1.4184 0.04633 0.04056 -0.0465 0.0109 1.0000
12.500 1.4209 0.04892 0.04332 -0.0455 0.0109 1.0000
12.750 1.4225 0.05188 0.04648 -0.0444 0.0108 1.0000
13.000 1.4232 0.05539 0.05017 -0.0431 0.0109 1.0000
13.250 1.4351 0.05838 0.05325 -0.0416 0.0112 1.0000
13.500 1.4307 0.06154 0.05659 -0.0413 0.0113 1.0000
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Polar data table (+)
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