GOE 147 (MVA H.6) AIRFOIL (goe147-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 147 (MVA H.6) AIRFOIL (goe147-il) Reynolds number: 1,000,000 Max Cl/Cd: 102.76 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe147-il-1000000.txt Download as CSV file: xf-goe147-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 147 (MVA H.6) 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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.5758 0.15053 0.14890 0.0382 1.0000 0.0086
-11.750 -0.5696 0.14710 0.14549 0.0369 1.0000 0.0088
-7.750 -0.5611 0.02463 0.02184 -0.0485 1.0000 0.0087
-7.500 -0.5365 0.02174 0.01863 -0.0496 1.0000 0.0089
-7.250 -0.5111 0.01964 0.01626 -0.0502 1.0000 0.0091
-7.000 -0.4851 0.01778 0.01415 -0.0505 1.0000 0.0093
-6.750 -0.4585 0.01627 0.01241 -0.0507 1.0000 0.0096
-6.500 -0.4314 0.01500 0.01094 -0.0507 1.0000 0.0099
-6.250 -0.4039 0.01418 0.00998 -0.0507 1.0000 0.0104
-6.000 -0.3761 0.01361 0.00931 -0.0506 1.0000 0.0107
-5.750 -0.3487 0.01206 0.00753 -0.0507 1.0000 0.0114
-5.500 -0.3210 0.01118 0.00656 -0.0507 1.0000 0.0120
-5.250 -0.2931 0.01071 0.00604 -0.0506 1.0000 0.0127
-5.000 -0.2652 0.01021 0.00549 -0.0505 1.0000 0.0133
-4.750 -0.2361 0.00977 0.00499 -0.0506 0.9973 0.0140
-4.500 -0.1969 0.00941 0.00455 -0.0528 0.9530 0.0148
-4.250 -0.1729 0.00893 0.00377 -0.0514 0.8837 0.0162
-4.000 -0.1475 0.00882 0.00345 -0.0505 0.8315 0.0177
-3.750 -0.1204 0.00871 0.00315 -0.0501 0.7904 0.0192
-3.500 -0.0926 0.00856 0.00283 -0.0498 0.7550 0.0205
-3.250 -0.0645 0.00827 0.00237 -0.0496 0.7211 0.0246
-3.000 -0.0363 0.00814 0.00208 -0.0494 0.6877 0.0294
-2.750 -0.0083 0.00778 0.00183 -0.0494 0.6565 0.0794
-2.500 0.0201 0.00805 0.00202 -0.0492 0.6303 0.0907
-2.250 0.0485 0.00811 0.00200 -0.0491 0.6072 0.0952
-2.000 0.0769 0.00823 0.00204 -0.0490 0.5860 0.0991
-1.750 0.1054 0.00833 0.00207 -0.0489 0.5685 0.1022
-1.500 0.1340 0.00843 0.00209 -0.0488 0.5546 0.1042
-1.250 0.1625 0.00845 0.00205 -0.0488 0.5411 0.1056
-0.750 0.2194 0.00821 0.00172 -0.0488 0.5142 0.1112
-0.500 0.2479 0.00818 0.00164 -0.0487 0.4993 0.1124
-0.250 0.2765 0.00816 0.00156 -0.0487 0.4817 0.1135
0.000 0.3050 0.00815 0.00148 -0.0487 0.4637 0.1145
0.250 0.3335 0.00817 0.00143 -0.0486 0.4426 0.1159
0.500 0.3618 0.00824 0.00139 -0.0486 0.4139 0.1169
0.750 0.3900 0.00837 0.00137 -0.0486 0.3761 0.1176
1.000 0.4181 0.00853 0.00139 -0.0486 0.3434 0.1182
1.250 0.4463 0.00865 0.00142 -0.0486 0.3223 0.1187
1.500 0.4747 0.00872 0.00143 -0.0486 0.3068 0.1199
1.750 0.5030 0.00879 0.00145 -0.0486 0.2940 0.1218
2.000 0.5314 0.00884 0.00149 -0.0485 0.2837 0.1241
2.250 0.5597 0.00890 0.00154 -0.0485 0.2744 0.1269
2.500 0.5880 0.00899 0.00160 -0.0485 0.2651 0.1302
2.750 0.6164 0.00903 0.00167 -0.0485 0.2575 0.1394
3.000 0.6447 0.00904 0.00179 -0.0486 0.2496 0.1928
3.250 0.6730 0.00907 0.00190 -0.0486 0.2426 0.2290
3.500 0.7013 0.00907 0.00203 -0.0487 0.2353 0.2912
3.750 0.7233 0.00761 0.00219 -0.0477 0.2293 1.0000
4.000 0.7514 0.00778 0.00230 -0.0477 0.2216 1.0000
4.250 0.7795 0.00791 0.00241 -0.0476 0.2148 1.0000
4.500 0.8075 0.00808 0.00255 -0.0476 0.2067 1.0000
4.750 0.8355 0.00825 0.00269 -0.0476 0.1977 1.0000
5.000 0.8633 0.00843 0.00284 -0.0475 0.1874 1.0000
5.250 0.8909 0.00867 0.00301 -0.0475 0.1723 1.0000
5.500 0.9181 0.00898 0.00322 -0.0474 0.1547 1.0000
5.750 0.9452 0.00931 0.00346 -0.0473 0.1405 1.0000
6.000 0.9726 0.00955 0.00368 -0.0473 0.1335 1.0000
6.250 0.9997 0.00984 0.00394 -0.0472 0.1264 1.0000
6.500 1.0272 0.01003 0.00415 -0.0471 0.1231 1.0000
6.750 1.0542 0.01031 0.00441 -0.0470 0.1173 1.0000
7.000 1.0813 0.01055 0.00466 -0.0469 0.1117 1.0000
7.250 1.1080 0.01085 0.00494 -0.0468 0.1036 1.0000
7.500 1.1338 0.01134 0.00529 -0.0466 0.0767 1.0000
7.750 1.1546 0.01294 0.00656 -0.0460 0.0206 1.0000
8.000 1.1802 0.01344 0.00709 -0.0457 0.0169 1.0000
8.250 1.2049 0.01412 0.00781 -0.0453 0.0139 1.0000
8.500 1.2305 0.01455 0.00831 -0.0451 0.0130 1.0000
8.750 1.2555 0.01507 0.00888 -0.0447 0.0120 1.0000
9.000 1.2795 0.01575 0.00961 -0.0443 0.0109 1.0000
9.250 1.3012 0.01686 0.01087 -0.0436 0.0099 1.0000
9.500 1.3253 0.01741 0.01147 -0.0432 0.0096 1.0000
9.750 1.3489 0.01802 0.01216 -0.0428 0.0090 1.0000
10.000 1.3719 0.01867 0.01287 -0.0423 0.0085 1.0000
10.250 1.3942 0.01940 0.01365 -0.0417 0.0080 1.0000
10.500 1.4146 0.02035 0.01468 -0.0410 0.0076 1.0000
10.750 1.4268 0.02233 0.01685 -0.0396 0.0071 1.0000
11.000 1.4435 0.02356 0.01819 -0.0385 0.0069 1.0000
11.250 1.4618 0.02451 0.01922 -0.0376 0.0067 1.0000
11.500 1.4778 0.02562 0.02045 -0.0366 0.0065 1.0000
11.750 1.4913 0.02691 0.02184 -0.0353 0.0063 1.0000
12.000 1.5024 0.02830 0.02334 -0.0339 0.0061 1.0000
12.250 1.5101 0.02983 0.02498 -0.0322 0.0059 1.0000
12.500 1.5101 0.03153 0.02679 -0.0298 0.0058 1.0000
12.750 1.5091 0.03370 0.02907 -0.0285 0.0057 1.0000
13.000 1.5063 0.03667 0.03217 -0.0287 0.0056 1.0000
13.250 1.5035 0.04030 0.03593 -0.0301 0.0055 1.0000
13.500 1.5004 0.04446 0.04022 -0.0322 0.0054 1.0000
13.750 1.4949 0.04922 0.04511 -0.0348 0.0054 1.0000
14.000 1.4865 0.05447 0.05047 -0.0375 0.0053 1.0000
14.250 1.4744 0.06017 0.05630 -0.0401 0.0053 1.0000
14.500 1.4602 0.06621 0.06245 -0.0428 0.0052 1.0000
14.750 1.4445 0.07245 0.06880 -0.0455 0.0052 1.0000
15.000 1.4282 0.07885 0.07532 -0.0481 0.0052 1.0000
15.250 1.4121 0.08522 0.08179 -0.0507 0.0052 1.0000
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Polar data table (+)
Polar graphs
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