GOE 255 (MVA CA.6) AIRFOIL (goe255-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 255 (MVA CA.6) AIRFOIL (goe255-il) Reynolds number: 500,000 Max Cl/Cd: 105.07 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe255-il-500000.txt Download as CSV file: xf-goe255-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 255 (MVA CA.6) 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
------ -------- --------- --------- -------- -------- --------
-17.250 -0.5776 0.11408 0.11120 -0.0649 1.0000 0.0155
-17.000 -0.6293 0.09985 0.09666 -0.0731 1.0000 0.0152
-16.750 -0.6522 0.09179 0.08842 -0.0778 1.0000 0.0152
-16.500 -0.6684 0.08525 0.08175 -0.0817 1.0000 0.0151
-16.250 -0.6805 0.07975 0.07613 -0.0848 1.0000 0.0152
-16.000 -0.6904 0.07487 0.07115 -0.0875 1.0000 0.0152
-15.750 -0.6994 0.07045 0.06664 -0.0898 1.0000 0.0153
-15.500 -0.7088 0.06648 0.06259 -0.0915 1.0000 0.0154
-15.250 -0.7191 0.06289 0.05892 -0.0925 1.0000 0.0154
-15.000 -0.7303 0.05962 0.05558 -0.0930 1.0000 0.0155
-14.750 -0.7421 0.05656 0.05245 -0.0930 1.0000 0.0156
-14.500 -0.7545 0.05369 0.04952 -0.0925 1.0000 0.0156
-14.250 -0.7633 0.05075 0.04651 -0.0928 0.9996 0.0157
-14.000 -0.7513 0.04698 0.04263 -0.0977 0.9967 0.0160
-13.750 -0.7359 0.04338 0.03891 -0.1029 0.9940 0.0162
-13.500 -0.7197 0.04008 0.03551 -0.1076 0.9901 0.0165
-13.250 -0.7006 0.03696 0.03226 -0.1125 0.9861 0.0168
-13.000 -0.6805 0.03409 0.02926 -0.1172 0.9813 0.0172
-12.750 -0.6648 0.03164 0.02667 -0.1204 0.9721 0.0175
-12.500 -0.6541 0.02956 0.02446 -0.1220 0.9593 0.0178
-12.250 -0.6559 0.02721 0.02201 -0.1212 0.9427 0.0181
-12.000 -0.6559 0.02554 0.02026 -0.1195 0.9222 0.0184
-11.750 -0.6523 0.02433 0.01895 -0.1172 0.8971 0.0188
-11.500 -0.6416 0.02324 0.01773 -0.1157 0.8726 0.0191
-11.250 -0.6278 0.02230 0.01661 -0.1145 0.8526 0.0196
-11.000 -0.6113 0.02146 0.01560 -0.1136 0.8375 0.0201
-10.750 -0.5930 0.02069 0.01468 -0.1129 0.8260 0.0207
-10.250 -0.5552 0.01903 0.01277 -0.1117 0.8086 0.0219
-10.000 -0.5357 0.01819 0.01183 -0.1111 0.8016 0.0228
-9.750 -0.5130 0.01758 0.01115 -0.1108 0.7953 0.0239
-9.500 -0.4893 0.01706 0.01053 -0.1106 0.7891 0.0251
-9.250 -0.4667 0.01640 0.00977 -0.1102 0.7836 0.0265
-9.000 -0.4427 0.01580 0.00913 -0.1100 0.7782 0.0285
-8.750 -0.4174 0.01535 0.00859 -0.1099 0.7728 0.0305
-8.500 -0.3933 0.01473 0.00792 -0.1096 0.7677 0.0345
-8.250 -0.3684 0.01414 0.00734 -0.1095 0.7629 0.0425
-8.000 -0.3440 0.01345 0.00679 -0.1094 0.7577 0.0643
-7.750 -0.3177 0.01307 0.00641 -0.1094 0.7526 0.0812
-7.500 -0.2912 0.01270 0.00605 -0.1094 0.7478 0.0951
-7.250 -0.2644 0.01232 0.00573 -0.1095 0.7424 0.1108
-7.000 -0.2372 0.01201 0.00546 -0.1096 0.7372 0.1305
-6.750 -0.2096 0.01178 0.00523 -0.1097 0.7323 0.1501
-6.500 -0.1817 0.01153 0.00504 -0.1099 0.7271 0.1673
-6.250 -0.1535 0.01134 0.00484 -0.1101 0.7217 0.1819
-6.000 -0.1253 0.01120 0.00465 -0.1103 0.7166 0.1962
-5.750 -0.0972 0.01098 0.00447 -0.1105 0.7112 0.2122
-5.500 -0.0692 0.01075 0.00427 -0.1106 0.7054 0.2290
-5.250 -0.0414 0.01055 0.00408 -0.1108 0.7000 0.2484
-5.000 -0.0134 0.01032 0.00393 -0.1110 0.6938 0.2712
-4.750 0.0147 0.01015 0.00384 -0.1111 0.6871 0.2992
-4.500 0.0434 0.01011 0.00379 -0.1113 0.6806 0.3247
-4.250 0.0722 0.01008 0.00376 -0.1115 0.6727 0.3421
-4.000 0.1011 0.01013 0.00371 -0.1116 0.6655 0.3557
-3.750 0.1301 0.01014 0.00371 -0.1118 0.6571 0.3673
-3.500 0.1586 0.01018 0.00367 -0.1120 0.6498 0.3764
-3.250 0.1877 0.01022 0.00366 -0.1122 0.6419 0.3847
-3.000 0.2162 0.01024 0.00363 -0.1123 0.6350 0.3924
-2.750 0.2451 0.01029 0.00364 -0.1126 0.6275 0.4005
-2.500 0.2736 0.01032 0.00358 -0.1127 0.6203 0.4061
-2.250 0.3022 0.01030 0.00355 -0.1129 0.6132 0.4109
-2.000 0.3307 0.01033 0.00352 -0.1131 0.6061 0.4158
-1.750 0.3593 0.01041 0.00350 -0.1133 0.6005 0.4205
-1.500 0.3880 0.01036 0.00347 -0.1135 0.5951 0.4251
-1.250 0.4165 0.01038 0.00346 -0.1137 0.5902 0.4293
-1.000 0.4450 0.01045 0.00346 -0.1139 0.5860 0.4333
-0.750 0.4740 0.01048 0.00347 -0.1142 0.5818 0.4372
-0.500 0.5025 0.01047 0.00346 -0.1144 0.5777 0.4415
-0.250 0.5309 0.01050 0.00348 -0.1147 0.5739 0.4458
0.000 0.5593 0.01058 0.00351 -0.1149 0.5701 0.4505
0.250 0.5881 0.01062 0.00354 -0.1151 0.5662 0.4554
0.500 0.6163 0.01060 0.00357 -0.1153 0.5623 0.4610
0.750 0.6447 0.01065 0.00361 -0.1156 0.5589 0.4665
1.000 0.6732 0.01076 0.00367 -0.1158 0.5559 0.4720
1.250 0.7015 0.01078 0.00373 -0.1161 0.5530 0.4780
1.500 0.7299 0.01080 0.00380 -0.1163 0.5499 0.4839
1.750 0.7582 0.01085 0.00386 -0.1165 0.5467 0.4893
2.000 0.7862 0.01088 0.00393 -0.1167 0.5433 0.4955
2.250 0.8142 0.01097 0.00401 -0.1169 0.5399 0.5030
2.500 0.8424 0.01103 0.00411 -0.1172 0.5370 0.5119
2.750 0.8702 0.01105 0.00421 -0.1174 0.5341 0.5241
3.250 0.9251 0.01106 0.00444 -0.1176 0.5275 0.5709
3.500 0.9519 0.01106 0.00458 -0.1176 0.5235 0.6217
3.750 0.9772 0.01094 0.00475 -0.1173 0.5191 0.7047
4.000 0.9978 0.01065 0.00491 -0.1157 0.5140 0.8315
4.250 1.0304 0.01058 0.00502 -0.1166 0.5083 1.0000
4.500 1.0564 0.01073 0.00515 -0.1164 0.5038 1.0000
4.750 1.0821 0.01082 0.00527 -0.1162 0.4992 1.0000
5.000 1.1076 0.01095 0.00539 -0.1159 0.4942 1.0000
5.250 1.1326 0.01115 0.00554 -0.1156 0.4891 1.0000
5.500 1.1573 0.01122 0.00568 -0.1152 0.4830 1.0000
5.750 1.1808 0.01138 0.00582 -0.1145 0.4757 1.0000
6.000 1.2044 0.01152 0.00598 -0.1139 0.4679 1.0000
6.250 1.2260 0.01170 0.00614 -0.1130 0.4582 1.0000
6.500 1.2472 0.01187 0.00632 -0.1119 0.4451 1.0000
6.750 1.2632 0.01214 0.00654 -0.1099 0.4254 1.0000
7.000 1.2710 0.01264 0.00690 -0.1064 0.3906 1.0000
7.250 1.2738 0.01353 0.00757 -0.1024 0.3598 1.0000
7.500 1.2820 0.01435 0.00827 -0.0994 0.3429 1.0000
7.750 1.2935 0.01509 0.00894 -0.0972 0.3326 1.0000
8.000 1.3075 0.01575 0.00958 -0.0953 0.3245 1.0000
8.250 1.3208 0.01647 0.01027 -0.0935 0.3175 1.0000
8.500 1.3364 0.01710 0.01091 -0.0921 0.3106 1.0000
8.750 1.3475 0.01797 0.01174 -0.0901 0.3037 1.0000
9.000 1.3656 0.01851 0.01234 -0.0891 0.2987 1.0000
9.250 1.3808 0.01922 0.01306 -0.0878 0.2932 1.0000
9.500 1.3916 0.02021 0.01403 -0.0861 0.2873 1.0000
9.750 1.4100 0.02080 0.01468 -0.0853 0.2813 1.0000
10.000 1.4226 0.02175 0.01563 -0.0840 0.2742 1.0000
10.250 1.4368 0.02265 0.01656 -0.0829 0.2663 1.0000
10.500 1.4488 0.02373 0.01764 -0.0817 0.2575 1.0000
10.750 1.4625 0.02474 0.01867 -0.0808 0.2479 1.0000
11.000 1.4718 0.02608 0.02000 -0.0795 0.2354 1.0000
11.250 1.4769 0.02780 0.02164 -0.0780 0.2151 1.0000
11.500 1.4697 0.03051 0.02418 -0.0757 0.1849 1.0000
11.750 1.4576 0.03370 0.02719 -0.0732 0.1604 1.0000
12.000 1.4497 0.03665 0.03005 -0.0711 0.1434 1.0000
12.250 1.4445 0.03944 0.03277 -0.0694 0.1270 1.0000
12.500 1.4354 0.04266 0.03587 -0.0676 0.1034 1.0000
12.750 1.4190 0.04668 0.03971 -0.0656 0.0776 1.0000
13.000 1.4069 0.05045 0.04339 -0.0641 0.0587 1.0000
13.500 1.3756 0.05920 0.05201 -0.0615 0.0200 1.0000
13.750 1.3769 0.06196 0.05484 -0.0610 0.0184 1.0000
14.000 1.3788 0.06469 0.05766 -0.0606 0.0176 1.0000
14.250 1.3798 0.06757 0.06062 -0.0602 0.0169 1.0000
14.500 1.3790 0.07067 0.06382 -0.0599 0.0162 1.0000
14.750 1.3761 0.07407 0.06731 -0.0596 0.0155 1.0000
15.000 1.3770 0.07706 0.07039 -0.0595 0.0152 1.0000
15.250 1.3769 0.08018 0.07361 -0.0594 0.0148 1.0000
15.500 1.3748 0.08363 0.07715 -0.0594 0.0145 1.0000
15.750 1.3716 0.08722 0.08084 -0.0595 0.0142 1.0000
16.000 1.3675 0.09097 0.08469 -0.0596 0.0139 1.0000
16.250 1.3616 0.09503 0.08884 -0.0599 0.0137 1.0000
16.500 1.3543 0.09935 0.09325 -0.0603 0.0135 1.0000
16.750 1.3465 0.10379 0.09780 -0.0609 0.0133 1.0000
17.000 1.3366 0.10860 0.10271 -0.0617 0.0131 1.0000
17.250 1.3247 0.11379 0.10801 -0.0627 0.0129 1.0000
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