GOE 124 (MVA H.4) AIRFOIL (goe124-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 124 (MVA H.4) AIRFOIL (goe124-il) Reynolds number: 1,000,000 Max Cl/Cd: 126.4 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe124-il-1000000-n5.txt Download as CSV file: xf-goe124-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 124 (MVA H.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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3322 0.09570 0.09364 -0.0209 0.8390 0.0095
-8.500 -0.3333 0.09020 0.08809 -0.0239 0.8247 0.0105
-8.250 -0.3232 0.08793 0.08577 -0.0254 0.8103 0.0107
-8.000 -0.3135 0.08552 0.08331 -0.0271 0.7963 0.0108
-7.750 -0.3029 0.08299 0.08074 -0.0293 0.7833 0.0110
-7.500 -0.2890 0.07998 0.07769 -0.0327 0.7716 0.0113
-7.250 -0.2737 0.07662 0.07426 -0.0368 0.7603 0.0116
-7.000 -0.2574 0.06879 0.06637 -0.0471 0.7504 0.0131
-6.750 -0.2365 0.06627 0.06380 -0.0508 0.7402 0.0133
-6.500 -0.2143 0.06367 0.06114 -0.0546 0.7302 0.0135
-6.250 -0.1907 0.06082 0.05824 -0.0587 0.7210 0.0137
-6.000 -0.1653 0.05761 0.05495 -0.0634 0.7112 0.0141
-5.750 -0.1374 0.05383 0.05108 -0.0689 0.7009 0.0147
-5.500 -0.0965 0.04498 0.04202 -0.0812 0.6930 0.0163
-5.000 -0.0396 0.04049 0.03733 -0.0870 0.6727 0.0168
-4.750 -0.0092 0.03794 0.03465 -0.0901 0.6640 0.0171
-4.500 0.0224 0.03518 0.03177 -0.0932 0.6553 0.0177
-4.250 0.0580 0.03104 0.02740 -0.0973 0.6475 0.0185
-4.000 0.1038 0.02145 0.01712 -0.1039 0.6405 0.0201
-3.750 0.1337 0.01998 0.01546 -0.1051 0.6321 0.0203
-3.500 0.1634 0.01874 0.01404 -0.1060 0.6228 0.0206
-3.250 0.1932 0.01767 0.01281 -0.1067 0.6142 0.0209
-3.000 0.2235 0.01640 0.01133 -0.1075 0.6062 0.0211
-2.750 0.2541 0.01512 0.00983 -0.1083 0.5997 0.0214
-2.500 0.2849 0.01384 0.00831 -0.1090 0.5926 0.0217
-2.250 0.3152 0.01283 0.00709 -0.1096 0.5868 0.0220
-2.000 0.3453 0.01199 0.00608 -0.1100 0.5805 0.0224
-1.750 0.3752 0.01120 0.00511 -0.1105 0.5741 0.0227
-1.500 0.4048 0.01065 0.00445 -0.1108 0.5678 0.0232
-1.250 0.4341 0.01029 0.00399 -0.1110 0.5602 0.0236
-1.000 0.4633 0.01002 0.00365 -0.1113 0.5526 0.0239
-0.750 0.4923 0.00983 0.00339 -0.1115 0.5442 0.0241
-0.500 0.5213 0.00966 0.00317 -0.1117 0.5368 0.0243
-0.250 0.5503 0.00948 0.00295 -0.1119 0.5285 0.0244
0.000 0.5798 0.00908 0.00250 -0.1122 0.5205 0.0248
0.250 0.6089 0.00891 0.00228 -0.1125 0.5114 0.0252
0.500 0.6379 0.00881 0.00216 -0.1127 0.5012 0.0257
0.750 0.6666 0.00879 0.00210 -0.1129 0.4863 0.0263
1.000 0.6952 0.00880 0.00204 -0.1131 0.4690 0.0268
1.250 0.7239 0.00881 0.00199 -0.1133 0.4531 0.0273
1.500 0.7524 0.00885 0.00197 -0.1134 0.4368 0.0279
1.750 0.7808 0.00893 0.00197 -0.1136 0.4193 0.0287
2.000 0.8089 0.00906 0.00201 -0.1137 0.3956 0.0294
2.250 0.8368 0.00923 0.00207 -0.1138 0.3743 0.0299
2.500 0.8650 0.00933 0.00213 -0.1139 0.3615 0.0304
2.750 0.8933 0.00940 0.00218 -0.1140 0.3519 0.0310
3.000 0.9214 0.00949 0.00224 -0.1141 0.3432 0.0331
3.250 0.9497 0.00957 0.00232 -0.1142 0.3360 0.0359
3.750 1.0066 0.00959 0.00260 -0.1147 0.3208 0.2223
4.250 1.0576 0.00853 0.00302 -0.1143 0.3073 1.0000
4.500 1.0853 0.00871 0.00316 -0.1143 0.3008 1.0000
4.750 1.1130 0.00887 0.00330 -0.1143 0.2941 1.0000
5.000 1.1405 0.00904 0.00345 -0.1144 0.2867 1.0000
5.250 1.1679 0.00924 0.00362 -0.1144 0.2779 1.0000
5.500 1.1949 0.00947 0.00380 -0.1143 0.2662 1.0000
5.750 1.2217 0.00974 0.00400 -0.1143 0.2507 1.0000
6.000 1.2431 0.01078 0.00459 -0.1137 0.1712 1.0000
6.250 1.2654 0.01165 0.00519 -0.1131 0.1262 1.0000
6.500 1.2908 0.01203 0.00552 -0.1129 0.1152 1.0000
6.750 1.3167 0.01233 0.00581 -0.1127 0.1086 1.0000
7.000 1.3420 0.01269 0.00613 -0.1124 0.1010 1.0000
7.250 1.3675 0.01299 0.00643 -0.1122 0.0951 1.0000
7.500 1.3926 0.01334 0.00675 -0.1119 0.0881 1.0000
7.750 1.4171 0.01373 0.00711 -0.1116 0.0788 1.0000
8.000 1.4408 0.01420 0.00751 -0.1111 0.0673 1.0000
8.250 1.4637 0.01473 0.00797 -0.1106 0.0552 1.0000
8.500 1.4850 0.01542 0.00856 -0.1098 0.0410 1.0000
8.750 1.5026 0.01645 0.00944 -0.1085 0.0193 1.0000
9.000 1.5235 0.01707 0.01006 -0.1077 0.0148 1.0000
9.250 1.5444 0.01765 0.01065 -0.1068 0.0127 1.0000
9.500 1.5658 0.01814 0.01118 -0.1060 0.0118 1.0000
9.750 1.5862 0.01870 0.01177 -0.1051 0.0109 1.0000
10.000 1.6052 0.01933 0.01243 -0.1039 0.0100 1.0000
10.250 1.6235 0.01997 0.01312 -0.1027 0.0092 1.0000
10.500 1.6417 0.02056 0.01375 -0.1015 0.0088 1.0000
10.750 1.6583 0.02120 0.01445 -0.1000 0.0082 1.0000
11.000 1.6726 0.02191 0.01520 -0.0982 0.0078 1.0000
11.250 1.6828 0.02271 0.01604 -0.0957 0.0074 1.0000
11.500 1.6911 0.02367 0.01707 -0.0932 0.0070 1.0000
11.750 1.6999 0.02471 0.01817 -0.0909 0.0068 1.0000
12.000 1.7096 0.02577 0.01930 -0.0891 0.0066 1.0000
12.250 1.7187 0.02695 0.02057 -0.0873 0.0064 1.0000
12.500 1.7272 0.02827 0.02196 -0.0857 0.0062 1.0000
12.750 1.7348 0.02973 0.02349 -0.0842 0.0060 1.0000
13.000 1.7417 0.03133 0.02517 -0.0829 0.0058 1.0000
13.250 1.7478 0.03307 0.02698 -0.0817 0.0056 1.0000
13.500 1.7527 0.03501 0.02899 -0.0806 0.0054 1.0000
13.750 1.7564 0.03715 0.03121 -0.0796 0.0052 1.0000
14.000 1.7578 0.03959 0.03374 -0.0786 0.0050 1.0000
14.250 1.7563 0.04244 0.03668 -0.0778 0.0049 1.0000
14.500 1.7584 0.04496 0.03930 -0.0772 0.0048 1.0000
14.750 1.7587 0.04772 0.04216 -0.0767 0.0047 1.0000
15.000 1.7576 0.05069 0.04523 -0.0763 0.0047 1.0000
15.250 1.7552 0.05388 0.04852 -0.0760 0.0046 1.0000
15.500 1.7517 0.05728 0.05203 -0.0758 0.0045 1.0000
15.750 1.7473 0.06090 0.05575 -0.0758 0.0044 1.0000
16.000 1.7422 0.06471 0.05967 -0.0760 0.0044 1.0000
16.250 1.7364 0.06873 0.06379 -0.0763 0.0043 1.0000
16.500 1.7292 0.07300 0.06817 -0.0768 0.0042 1.0000
16.750 1.7218 0.07741 0.07268 -0.0774 0.0042 1.0000
17.000 1.7134 0.08208 0.07747 -0.0783 0.0041 1.0000
17.250 1.7046 0.08688 0.08238 -0.0793 0.0041 1.0000
17.500 1.6944 0.09194 0.08755 -0.0804 0.0040 1.0000
17.750 1.6840 0.09717 0.09288 -0.0818 0.0040 1.0000
18.000 1.6730 0.10257 0.09839 -0.0833 0.0039 1.0000
18.250 1.6616 0.10809 0.10403 -0.0850 0.0039 1.0000
18.500 1.6495 0.11378 0.10983 -0.0868 0.0038 1.0000
18.750 1.6376 0.11954 0.11569 -0.0889 0.0038 1.0000
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Polar data table (+)
Polar graphs
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