GOE 118 (MVA MK.7) AIRFOIL (goe118-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 118 (MVA MK.7) AIRFOIL (goe118-il) Reynolds number: 200,000 Max Cl/Cd: 82.7 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe118-il-200000-n5.txt Download as CSV file: xf-goe118-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 118 (MVA MK.7) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2592 0.11050 0.10723 -0.0395 1.0000 0.0136
-9.000 -0.2551 0.10778 0.10456 -0.0401 1.0000 0.0139
-8.750 -0.2523 0.10521 0.10203 -0.0404 0.9998 0.0143
-8.500 -0.2371 0.10134 0.09817 -0.0444 0.9887 0.0148
-8.250 -0.2223 0.09755 0.09439 -0.0482 0.9748 0.0153
-8.000 -0.2075 0.09380 0.09059 -0.0521 0.9588 0.0159
-7.500 -0.1799 0.08659 0.08335 -0.0592 0.9224 0.0173
-7.250 -0.1688 0.08328 0.08001 -0.0621 0.9031 0.0180
-7.000 -0.1587 0.08019 0.07688 -0.0652 0.8844 0.0189
-6.750 -0.1424 0.07687 0.07350 -0.0714 0.8667 0.0198
-6.500 -0.1235 0.07327 0.06984 -0.0771 0.8515 0.0202
-6.250 -0.1040 0.06954 0.06604 -0.0820 0.8381 0.0203
-6.000 -0.0829 0.06560 0.06201 -0.0870 0.8257 0.0204
-5.750 -0.0601 0.06149 0.05780 -0.0920 0.8145 0.0205
-5.500 -0.0355 0.05721 0.05340 -0.0972 0.8042 0.0205
-5.250 -0.0091 0.05278 0.04885 -0.1022 0.7940 0.0205
-5.000 0.0160 0.02896 0.02514 -0.0964 0.7602 0.0151
-4.750 0.0522 0.02226 0.01822 -0.1046 0.7546 0.0112
-3.750 0.1731 0.02215 0.01584 -0.1252 0.7474 0.0115
-3.500 0.2026 0.01995 0.01310 -0.1259 0.7397 0.0114
-3.250 0.2316 0.01803 0.01066 -0.1262 0.7330 0.0115
-3.000 0.2602 0.01634 0.00861 -0.1264 0.7255 0.0118
-2.500 0.3163 0.01426 0.00611 -0.1266 0.7119 0.0151
-2.250 0.3446 0.01367 0.00532 -0.1265 0.7055 0.0175
-2.000 0.3730 0.01320 0.00465 -0.1265 0.6982 0.0197
-1.750 0.4011 0.01267 0.00391 -0.1265 0.6918 0.0274
-1.500 0.4290 0.01229 0.00364 -0.1266 0.6848 0.0903
-1.250 0.4565 0.01241 0.00366 -0.1266 0.6781 0.1126
-1.000 0.4841 0.01246 0.00363 -0.1267 0.6711 0.1270
-0.750 0.5116 0.01237 0.00342 -0.1267 0.6642 0.1294
-0.500 0.5391 0.01230 0.00327 -0.1268 0.6570 0.1325
-0.250 0.5664 0.01225 0.00314 -0.1268 0.6496 0.1370
0.000 0.5938 0.01218 0.00304 -0.1269 0.6416 0.1434
0.250 0.6211 0.01216 0.00295 -0.1269 0.6344 0.1517
0.500 0.6485 0.01210 0.00292 -0.1270 0.6267 0.1657
0.750 0.6757 0.01199 0.00292 -0.1271 0.6202 0.2074
1.000 0.6970 0.01074 0.00311 -0.1262 0.6134 0.7387
1.250 0.7259 0.01049 0.00304 -0.1262 0.6069 1.0000
1.500 0.7532 0.01061 0.00310 -0.1262 0.6002 1.0000
1.750 0.7803 0.01074 0.00318 -0.1262 0.5936 1.0000
2.000 0.8073 0.01087 0.00326 -0.1262 0.5858 1.0000
2.250 0.8340 0.01102 0.00334 -0.1261 0.5775 1.0000
2.500 0.8607 0.01115 0.00347 -0.1260 0.5684 1.0000
2.750 0.8873 0.01131 0.00363 -0.1259 0.5602 1.0000
3.000 0.9140 0.01146 0.00381 -0.1259 0.5525 1.0000
3.250 0.9406 0.01164 0.00400 -0.1258 0.5460 1.0000
3.500 0.9670 0.01181 0.00425 -0.1257 0.5374 1.0000
3.750 0.9921 0.01200 0.00443 -0.1252 0.5208 1.0000
4.000 1.0147 0.01227 0.00460 -0.1243 0.4837 1.0000
4.250 1.0325 0.01291 0.00487 -0.1227 0.4083 1.0000
4.500 1.0285 0.01590 0.00634 -0.1184 0.1620 1.0000
4.750 1.0364 0.01795 0.00794 -0.1155 0.0236 1.0000
5.000 1.0570 0.01864 0.00883 -0.1144 0.0177 1.0000
5.250 1.0752 0.01952 0.00990 -0.1128 0.0144 1.0000
5.500 1.0924 0.02041 0.01098 -0.1112 0.0124 1.0000
5.750 1.1056 0.02157 0.01232 -0.1090 0.0114 1.0000
6.000 1.1151 0.02290 0.01379 -0.1063 0.0106 1.0000
6.250 1.1200 0.02436 0.01536 -0.1031 0.0094 1.0000
6.500 1.1135 0.02655 0.01762 -0.0984 0.0085 1.0000
6.750 1.1197 0.02807 0.01922 -0.0955 0.0081 1.0000
7.000 1.1268 0.02972 0.02094 -0.0929 0.0079 1.0000
7.250 1.1370 0.03142 0.02270 -0.0905 0.0077 1.0000
7.500 1.1529 0.03314 0.02448 -0.0885 0.0076 1.0000
7.750 1.1787 0.03502 0.02643 -0.0874 0.0075 1.0000
8.000 1.2191 0.03755 0.02907 -0.0882 0.0075 1.0000
8.250 1.2432 0.03919 0.03091 -0.0874 0.0066 1.0000
8.500 1.2618 0.04097 0.03286 -0.0865 0.0057 1.0000
8.750 1.2945 0.04422 0.03639 -0.0868 0.0057 1.0000
9.000 1.3205 0.04813 0.04068 -0.0856 0.0064 1.0000
9.250 1.3352 0.05214 0.04500 -0.0838 0.0070 1.0000
9.500 1.3588 0.05606 0.04939 -0.0812 0.0117 1.0000
9.750 1.3626 0.05934 0.05297 -0.0783 0.0120 1.0000
10.000 1.3620 0.06245 0.05635 -0.0751 0.0120 1.0000
10.250 1.3554 0.06530 0.05945 -0.0714 0.0118 1.0000
10.500 1.3459 0.06817 0.06255 -0.0678 0.0117 1.0000
10.750 1.3342 0.07122 0.06581 -0.0646 0.0116 1.0000
11.000 1.3209 0.07446 0.06927 -0.0619 0.0115 1.0000
11.250 1.3063 0.07798 0.07299 -0.0598 0.0114 1.0000
11.500 1.2905 0.08176 0.07698 -0.0582 0.0114 1.0000
11.750 1.2737 0.08586 0.08126 -0.0573 0.0113 1.0000
12.000 1.2562 0.09028 0.08587 -0.0570 0.0113 1.0000
12.250 1.2380 0.09505 0.09082 -0.0572 0.0113 1.0000
12.500 1.2195 0.10016 0.09611 -0.0581 0.0113 1.0000
12.750 1.2006 0.10564 0.10175 -0.0597 0.0114 1.0000
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Polar data table (+)
Polar graphs
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