GOE 117 (MVA MK.4) AIRFOIL (goe117-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 117 (MVA MK.4) AIRFOIL (goe117-il) Reynolds number: 1,000,000 Max Cl/Cd: 116.88 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe117-il-1000000-n5.txt Download as CSV file: xf-goe117-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 117 (MVA MK.4) 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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3732 0.11609 0.11444 -0.0332 1.0000 0.0035
-11.000 -0.3726 0.11195 0.11032 -0.0343 1.0000 0.0036
-10.500 -0.6148 0.02608 0.02366 -0.1071 0.9501 0.0034
-10.250 -0.5832 0.02240 0.01954 -0.1123 0.9302 0.0035
-10.000 -0.5592 0.02043 0.01724 -0.1137 0.9102 0.0036
-9.750 -0.5386 0.01898 0.01552 -0.1137 0.8953 0.0038
-9.250 -0.4959 0.01680 0.01288 -0.1129 0.8716 0.0041
-9.000 -0.4731 0.01599 0.01188 -0.1126 0.8617 0.0042
-8.750 -0.4522 0.01475 0.01037 -0.1120 0.8514 0.0044
-8.500 -0.4289 0.01394 0.00940 -0.1116 0.8425 0.0047
-8.250 -0.4046 0.01332 0.00864 -0.1112 0.8352 0.0050
-8.000 -0.3798 0.01278 0.00798 -0.1109 0.8278 0.0052
-7.750 -0.3547 0.01226 0.00731 -0.1106 0.8213 0.0056
-7.500 -0.3294 0.01179 0.00671 -0.1103 0.8140 0.0059
-7.250 -0.3037 0.01137 0.00616 -0.1100 0.8071 0.0062
-7.000 -0.2782 0.01090 0.00557 -0.1097 0.7989 0.0067
-6.750 -0.2525 0.01048 0.00505 -0.1094 0.7903 0.0076
-6.500 -0.2266 0.01018 0.00466 -0.1092 0.7806 0.0085
-6.250 -0.2005 0.00990 0.00427 -0.1089 0.7694 0.0092
-6.000 -0.1744 0.00960 0.00388 -0.1086 0.7569 0.0109
-5.750 -0.1482 0.00942 0.00366 -0.1083 0.7414 0.0129
-5.500 -0.1223 0.00928 0.00344 -0.1080 0.7207 0.0150
-5.250 -0.0966 0.00932 0.00342 -0.1075 0.6912 0.0182
-5.000 -0.0709 0.00939 0.00336 -0.1071 0.6624 0.0205
-4.750 -0.0449 0.00943 0.00327 -0.1068 0.6404 0.0218
-4.500 -0.0184 0.00948 0.00323 -0.1065 0.6242 0.0225
-4.250 0.0086 0.00954 0.00323 -0.1064 0.6116 0.0229
-4.000 0.0349 0.00928 0.00286 -0.1062 0.6019 0.0238
-3.750 0.0612 0.00902 0.00249 -0.1059 0.5939 0.0252
-3.500 0.0881 0.00885 0.00225 -0.1058 0.5868 0.0261
-3.250 0.1150 0.00872 0.00206 -0.1056 0.5804 0.0269
-3.000 0.1422 0.00859 0.00188 -0.1055 0.5746 0.0276
-2.750 0.1693 0.00849 0.00170 -0.1053 0.5686 0.0280
-2.500 0.1964 0.00839 0.00155 -0.1052 0.5634 0.0284
-2.250 0.2237 0.00830 0.00142 -0.1051 0.5583 0.0293
-2.000 0.2509 0.00824 0.00131 -0.1050 0.5536 0.0307
-1.750 0.2782 0.00818 0.00122 -0.1049 0.5498 0.0325
-1.500 0.3057 0.00813 0.00115 -0.1048 0.5458 0.0341
-1.250 0.3330 0.00808 0.00109 -0.1047 0.5416 0.0411
-0.750 0.3864 0.00775 0.00101 -0.1045 0.5343 0.1318
-0.500 0.4139 0.00773 0.00100 -0.1044 0.5308 0.1415
-0.250 0.4411 0.00771 0.00100 -0.1043 0.5271 0.1494
0.000 0.4683 0.00772 0.00100 -0.1042 0.5236 0.1555
0.250 0.4956 0.00770 0.00101 -0.1042 0.5200 0.1653
0.500 0.5228 0.00766 0.00102 -0.1041 0.5151 0.1820
0.750 0.5494 0.00759 0.00107 -0.1040 0.5103 0.2275
1.000 0.5764 0.00757 0.00114 -0.1039 0.5066 0.2609
1.250 0.6037 0.00757 0.00118 -0.1038 0.5035 0.2772
1.500 0.6311 0.00759 0.00123 -0.1038 0.5002 0.2847
1.750 0.6581 0.00762 0.00128 -0.1037 0.4962 0.2933
2.000 0.6851 0.00766 0.00134 -0.1035 0.4898 0.3006
2.250 0.7120 0.00770 0.00139 -0.1034 0.4825 0.3091
2.500 0.7389 0.00773 0.00147 -0.1033 0.4780 0.3213
2.750 0.7656 0.00776 0.00154 -0.1031 0.4688 0.3357
3.000 0.7920 0.00779 0.00163 -0.1030 0.4595 0.3594
3.250 0.8167 0.00762 0.00178 -0.1026 0.4461 0.5102
3.750 0.8719 0.00746 0.00227 -0.1033 0.3472 1.0000
4.000 0.8896 0.00825 0.00269 -0.1016 0.2728 1.0000
4.250 0.8959 0.01004 0.00365 -0.0981 0.0865 1.0000
4.500 0.9174 0.01052 0.00397 -0.0971 0.0473 1.0000
4.750 0.9410 0.01082 0.00422 -0.0964 0.0355 1.0000
5.000 0.9647 0.01110 0.00447 -0.0957 0.0294 1.0000
5.250 0.9887 0.01135 0.00474 -0.0951 0.0245 1.0000
5.500 1.0117 0.01168 0.00503 -0.0944 0.0162 1.0000
5.750 1.0348 0.01199 0.00532 -0.0936 0.0132 1.0000
6.000 1.0571 0.01236 0.00569 -0.0927 0.0101 1.0000
6.250 1.0799 0.01266 0.00602 -0.0919 0.0092 1.0000
6.500 1.1021 0.01300 0.00640 -0.0910 0.0081 1.0000
6.750 1.1230 0.01343 0.00683 -0.0899 0.0071 1.0000
7.000 1.1433 0.01388 0.00733 -0.0887 0.0064 1.0000
7.250 1.1638 0.01428 0.00777 -0.0875 0.0060 1.0000
7.500 1.1834 0.01473 0.00827 -0.0862 0.0056 1.0000
7.750 1.2025 0.01518 0.00874 -0.0849 0.0052 1.0000
8.000 1.2205 0.01567 0.00926 -0.0833 0.0048 1.0000
8.250 1.2353 0.01630 0.00995 -0.0813 0.0043 1.0000
8.500 1.2492 0.01684 0.01055 -0.0790 0.0041 1.0000
8.750 1.2612 0.01742 0.01119 -0.0763 0.0040 1.0000
9.000 1.2725 0.01805 0.01188 -0.0737 0.0038 1.0000
9.250 1.2837 0.01871 0.01261 -0.0711 0.0037 1.0000
9.500 1.2934 0.01947 0.01344 -0.0685 0.0035 1.0000
9.750 1.3036 0.02026 0.01428 -0.0661 0.0034 1.0000
10.000 1.3122 0.02117 0.01526 -0.0636 0.0033 1.0000
10.250 1.3213 0.02210 0.01626 -0.0614 0.0032 1.0000
10.500 1.3292 0.02317 0.01740 -0.0592 0.0031 1.0000
10.750 1.3384 0.02422 0.01850 -0.0573 0.0029 1.0000
11.000 1.3447 0.02554 0.01989 -0.0552 0.0028 1.0000
11.250 1.3475 0.02721 0.02168 -0.0529 0.0027 1.0000
11.500 1.3484 0.02915 0.02374 -0.0507 0.0026 1.0000
11.750 1.3567 0.03053 0.02521 -0.0492 0.0026 1.0000
12.000 1.3623 0.03221 0.02700 -0.0477 0.0026 1.0000
12.250 1.3679 0.03396 0.02885 -0.0462 0.0025 1.0000
12.500 1.3761 0.03547 0.03046 -0.0452 0.0024 1.0000
12.750 1.3794 0.03758 0.03270 -0.0438 0.0024 1.0000
13.000 1.3867 0.03927 0.03448 -0.0429 0.0023 1.0000
13.250 1.3900 0.04147 0.03680 -0.0419 0.0022 1.0000
13.500 1.3950 0.04354 0.03898 -0.0411 0.0021 1.0000
13.750 1.3992 0.04571 0.04126 -0.0404 0.0021 1.0000
14.000 1.3995 0.04846 0.04416 -0.0396 0.0020 1.0000
14.250 1.4027 0.05090 0.04671 -0.0392 0.0020 1.0000
14.500 1.4020 0.05388 0.04984 -0.0388 0.0020 1.0000
14.750 1.4009 0.05702 0.05315 -0.0386 0.0020 1.0000
15.000 1.4005 0.06015 0.05641 -0.0387 0.0019 1.0000
15.250 1.3966 0.06387 0.06028 -0.0389 0.0019 1.0000
15.500 1.3979 0.06688 0.06338 -0.0393 0.0018 1.0000
15.750 1.3892 0.07151 0.06820 -0.0400 0.0018 1.0000
16.000 1.3832 0.07588 0.07271 -0.0409 0.0018 1.0000
16.250 1.3783 0.08013 0.07710 -0.0420 0.0018 1.0000
16.500 1.3623 0.08643 0.08360 -0.0438 0.0018 1.0000
16.750 1.3513 0.09209 0.08942 -0.0458 0.0017 1.0000
17.000 1.3386 0.09826 0.09576 -0.0482 0.0017 1.0000
17.250 1.3233 0.10516 0.10281 -0.0512 0.0017 1.0000
17.500 1.3057 0.11286 0.11069 -0.0548 0.0017 1.0000
17.750 1.2591 0.12751 0.12567 -0.0624 0.0018 1.0000
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Polar data table (+)
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