GOE 308 (MVA H.40) AIRFOIL (goe308-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 308 (MVA H.40) AIRFOIL (goe308-il) Reynolds number: 1,000,000 Max Cl/Cd: 126.33 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe308-il-1000000.txt Download as CSV file: xf-goe308-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 308 (MVA H.40) 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2530 0.09504 0.09359 -0.0273 1.0000 0.0128
-9.250 -0.3365 0.10014 0.09858 -0.0261 1.0000 0.0124
-9.000 -0.3362 0.09748 0.09594 -0.0259 1.0000 0.0125
-8.750 -0.3338 0.09555 0.09403 -0.0251 1.0000 0.0126
-8.500 -0.3314 0.09401 0.09251 -0.0241 1.0000 0.0130
-8.250 -0.3187 0.09054 0.08904 -0.0276 0.9989 0.0132
-8.000 -0.3003 0.08693 0.08543 -0.0324 0.9969 0.0140
-7.500 -0.2650 0.07601 0.07449 -0.0499 0.9865 0.0158
-7.250 -0.2417 0.07074 0.06920 -0.0573 0.9837 0.0158
-7.000 -0.2250 0.06539 0.06381 -0.0630 0.9761 0.0159
-6.250 -0.1580 0.05435 0.05267 -0.0756 0.9586 0.0175
-6.000 -0.1183 0.04920 0.04739 -0.0835 0.9497 0.0204
-5.500 -0.0928 0.02076 0.01770 -0.0929 0.9106 0.0200
-5.250 -0.0787 0.01661 0.01288 -0.0914 0.8904 0.0214
-5.000 -0.0532 0.01626 0.01245 -0.0911 0.8735 0.0221
-4.750 -0.0290 0.01582 0.01190 -0.0905 0.8577 0.0228
-4.500 -0.0061 0.01505 0.01093 -0.0895 0.8437 0.0236
-4.250 0.0168 0.01425 0.00992 -0.0885 0.8306 0.0245
-4.000 0.0409 0.01373 0.00922 -0.0876 0.8179 0.0255
-3.750 0.0710 0.01528 0.01080 -0.0876 0.8047 0.0267
-3.500 0.0901 0.01315 0.00827 -0.0859 0.7930 0.0269
-3.250 0.1107 0.01110 0.00588 -0.0844 0.7810 0.0278
-3.000 0.1349 0.01045 0.00514 -0.0836 0.7674 0.0288
-2.750 0.1595 0.01002 0.00459 -0.0828 0.7522 0.0294
-2.500 0.1841 0.00965 0.00409 -0.0820 0.7353 0.0298
-2.250 0.2087 0.00930 0.00363 -0.0812 0.7164 0.0301
-2.000 0.2328 0.00901 0.00321 -0.0802 0.6944 0.0304
-1.750 0.2566 0.00879 0.00286 -0.0792 0.6709 0.0310
-1.250 0.3044 0.00851 0.00236 -0.0773 0.6265 0.0327
-1.000 0.3285 0.00841 0.00214 -0.0763 0.6061 0.0333
-0.750 0.3526 0.00835 0.00197 -0.0755 0.5852 0.0338
-0.500 0.3769 0.00830 0.00183 -0.0746 0.5632 0.0343
-0.250 0.4011 0.00830 0.00172 -0.0737 0.5412 0.0347
0.000 0.4255 0.00830 0.00163 -0.0729 0.5193 0.0349
0.500 0.4739 0.00831 0.00143 -0.0713 0.4806 0.0375
0.750 0.4985 0.00835 0.00139 -0.0705 0.4645 0.0406
1.000 0.5232 0.00838 0.00137 -0.0698 0.4514 0.0457
1.250 0.5478 0.00838 0.00146 -0.0691 0.4413 0.0936
1.500 0.5735 0.00842 0.00152 -0.0686 0.4329 0.1026
2.000 0.6246 0.00855 0.00160 -0.0676 0.4179 0.1128
2.250 0.6496 0.00862 0.00165 -0.0671 0.4103 0.1178
2.500 0.6755 0.00866 0.00169 -0.0667 0.4039 0.1217
2.750 0.7008 0.00870 0.00174 -0.0661 0.3978 0.1291
3.000 0.7261 0.00875 0.00181 -0.0656 0.3926 0.1357
3.250 0.7513 0.00873 0.00190 -0.0651 0.3878 0.1789
3.500 0.7673 0.00811 0.00207 -0.0629 0.3832 0.5664
3.750 0.8215 0.00743 0.00240 -0.0689 0.3770 0.9741
4.000 0.8631 0.00762 0.00258 -0.0719 0.3706 0.9848
4.250 0.9045 0.00781 0.00272 -0.0751 0.3639 0.9887
4.500 0.9421 0.00794 0.00286 -0.0773 0.3569 0.9922
4.750 0.9780 0.00811 0.00298 -0.0793 0.3442 0.9947
5.000 1.0217 0.00827 0.00309 -0.0830 0.3329 0.9973
5.250 1.0611 0.00845 0.00322 -0.0858 0.3204 0.9994
5.500 1.0890 0.00862 0.00335 -0.0861 0.3042 1.0000
5.750 1.1087 0.00885 0.00349 -0.0845 0.2837 1.0000
6.000 1.1266 0.00917 0.00370 -0.0827 0.2584 1.0000
6.250 1.1413 0.00969 0.00401 -0.0802 0.2206 1.0000
6.500 1.1534 0.01035 0.00443 -0.0773 0.1782 1.0000
6.750 1.1640 0.01110 0.00492 -0.0742 0.1350 1.0000
7.000 1.1559 0.01298 0.00616 -0.0677 0.0243 1.0000
7.250 1.1717 0.01340 0.00658 -0.0654 0.0186 1.0000
7.500 1.1887 0.01375 0.00698 -0.0633 0.0169 1.0000
7.750 1.2042 0.01420 0.00745 -0.0610 0.0152 1.0000
8.000 1.2181 0.01474 0.00808 -0.0584 0.0139 1.0000
8.250 1.2349 0.01510 0.00847 -0.0564 0.0134 1.0000
8.500 1.2509 0.01551 0.00891 -0.0543 0.0127 1.0000
8.750 1.2660 0.01596 0.00941 -0.0521 0.0120 1.0000
9.000 1.2800 0.01648 0.00997 -0.0497 0.0113 1.0000
9.250 1.2901 0.01705 0.01060 -0.0465 0.0109 1.0000
9.500 1.2924 0.01792 0.01157 -0.0420 0.0103 1.0000
9.750 1.2958 0.01883 0.01257 -0.0379 0.0099 1.0000
10.000 1.3059 0.01947 0.01327 -0.0352 0.0097 1.0000
10.250 1.3171 0.02009 0.01395 -0.0327 0.0094 1.0000
10.500 1.3242 0.02097 0.01491 -0.0298 0.0092 1.0000
10.750 1.3389 0.02148 0.01544 -0.0282 0.0085 1.0000
11.000 1.3438 0.02257 0.01662 -0.0253 0.0085 1.0000
11.250 1.3508 0.02360 0.01770 -0.0230 0.0081 1.0000
11.500 1.3572 0.02474 0.01891 -0.0208 0.0079 1.0000
11.750 1.3596 0.02624 0.02048 -0.0185 0.0077 1.0000
12.000 1.3529 0.02857 0.02290 -0.0159 0.0073 1.0000
12.250 1.3454 0.03121 0.02565 -0.0137 0.0072 1.0000
12.500 1.3311 0.03470 0.02927 -0.0116 0.0071 1.0000
12.750 1.3349 0.03671 0.03136 -0.0108 0.0071 1.0000
13.000 1.3353 0.03913 0.03387 -0.0100 0.0070 1.0000
13.250 1.3415 0.04111 0.03594 -0.0097 0.0068 1.0000
13.500 1.3423 0.04368 0.03860 -0.0094 0.0067 1.0000
13.750 1.3424 0.04639 0.04141 -0.0092 0.0066 1.0000
14.000 1.3408 0.04937 0.04447 -0.0090 0.0065 1.0000
14.250 1.3420 0.05217 0.04737 -0.0092 0.0062 1.0000
14.500 1.3366 0.05554 0.05083 -0.0088 0.0063 1.0000
14.750 1.3356 0.05867 0.05405 -0.0091 0.0062 1.0000
15.000 1.3340 0.06188 0.05735 -0.0094 0.0061 1.0000
15.250 1.3326 0.06519 0.06075 -0.0099 0.0059 1.0000
15.500 1.3292 0.06857 0.06424 -0.0099 0.0059 1.0000
15.750 1.3298 0.07223 0.06796 -0.0119 0.0056 1.0000
16.000 1.3233 0.07558 0.07144 -0.0108 0.0058 1.0000
16.250 1.3210 0.07935 0.07528 -0.0121 0.0056 1.0000
16.500 1.3187 0.08342 0.07942 -0.0140 0.0055 1.0000
16.750 1.3130 0.08749 0.08359 -0.0148 0.0054 1.0000
17.000 1.3088 0.09159 0.08777 -0.0161 0.0053 1.0000
17.250 1.3020 0.09562 0.09193 -0.0164 0.0054 1.0000
17.500 1.2984 0.10026 0.09660 -0.0192 0.0051 1.0000
17.750 1.2918 0.10464 0.10109 -0.0203 0.0052 1.0000
18.000 1.2868 0.10911 0.10561 -0.0222 0.0050 1.0000
18.250 1.2760 0.11412 0.11073 -0.0236 0.0049 1.0000
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