GOE 274 (DAIMLER V) AIRFOIL (goe274-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 274 (DAIMLER V) AIRFOIL (goe274-il) Reynolds number: 1,000,000 Max Cl/Cd: 105.53 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe274-il-1000000-n5.txt Download as CSV file: xf-goe274-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 274 (DAIMLER V) 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 -0.2785 0.08971 0.08805 -0.0465 0.9885 0.0089
-8.500 -0.2656 0.08606 0.08440 -0.0502 0.9855 0.0092
-8.000 -0.2512 0.07658 0.07491 -0.0591 0.9722 0.0106
-7.750 -0.2355 0.07382 0.07214 -0.0626 0.9657 0.0107
-7.500 -0.2187 0.07083 0.06914 -0.0666 0.9598 0.0109
-7.250 -0.2016 0.06761 0.06589 -0.0707 0.9525 0.0112
-7.000 -0.1828 0.06402 0.06226 -0.0754 0.9454 0.0116
-6.750 -0.1599 0.05547 0.05360 -0.0865 0.9364 0.0131
-6.500 -0.1372 0.05291 0.05099 -0.0897 0.9296 0.0133
-6.250 -0.1137 0.05040 0.04842 -0.0925 0.9210 0.0135
-6.000 -0.0889 0.04768 0.04562 -0.0956 0.9122 0.0137
-5.750 -0.0629 0.04466 0.04250 -0.0988 0.9026 0.0141
-5.500 -0.0353 0.04119 0.03889 -0.1023 0.8913 0.0148
-5.250 0.0004 0.03356 0.03090 -0.1085 0.8803 0.0164
-5.000 0.0264 0.03193 0.02914 -0.1096 0.8661 0.0165
-4.750 0.0527 0.03040 0.02747 -0.1105 0.8493 0.0168
-4.500 0.0797 0.02875 0.02563 -0.1114 0.8307 0.0171
-4.250 0.1074 0.02706 0.02375 -0.1123 0.8113 0.0176
-4.000 0.1364 0.02486 0.02129 -0.1132 0.7882 0.0183
-3.750 0.1663 0.02236 0.01844 -0.1141 0.7608 0.0188
-3.500 0.1975 0.01924 0.01484 -0.1148 0.7278 0.0194
-3.250 0.2270 0.01700 0.01213 -0.1154 0.6891 0.0202
-3.000 0.2538 0.01642 0.01122 -0.1155 0.6343 0.0204
-2.750 0.2800 0.01610 0.01054 -0.1155 0.5666 0.0206
-2.500 0.3074 0.01567 0.00983 -0.1157 0.5260 0.0209
-2.250 0.3359 0.01504 0.00899 -0.1160 0.5028 0.0211
-2.000 0.3646 0.01440 0.00816 -0.1162 0.4843 0.0214
-1.750 0.3935 0.01376 0.00732 -0.1165 0.4683 0.0216
-1.500 0.4223 0.01315 0.00654 -0.1167 0.4534 0.0217
-1.250 0.4509 0.01272 0.00597 -0.1169 0.4389 0.0221
-1.000 0.4796 0.01220 0.00530 -0.1170 0.4257 0.0223
-0.750 0.5082 0.01172 0.00468 -0.1171 0.4133 0.0225
-0.500 0.5368 0.01133 0.00420 -0.1173 0.4032 0.0228
-0.250 0.5652 0.01105 0.00384 -0.1174 0.3931 0.0233
0.000 0.5933 0.01090 0.00361 -0.1175 0.3802 0.0238
0.250 0.6213 0.01083 0.00345 -0.1176 0.3651 0.0241
0.500 0.6491 0.01079 0.00333 -0.1176 0.3487 0.0243
0.750 0.6772 0.01075 0.00323 -0.1177 0.3367 0.0245
1.000 0.7057 0.01054 0.00298 -0.1179 0.3281 0.0248
1.250 0.7340 0.01043 0.00282 -0.1181 0.3183 0.0253
1.500 0.7621 0.01040 0.00278 -0.1183 0.3090 0.0260
1.750 0.7902 0.01042 0.00276 -0.1184 0.2995 0.0264
2.000 0.8180 0.01046 0.00274 -0.1184 0.2886 0.0267
2.250 0.8458 0.01051 0.00275 -0.1185 0.2775 0.0273
2.500 0.8734 0.01059 0.00279 -0.1185 0.2649 0.0281
2.750 0.9007 0.01073 0.00286 -0.1185 0.2497 0.0290
3.000 0.9275 0.01091 0.00295 -0.1184 0.2325 0.0298
3.250 0.9543 0.01111 0.00307 -0.1183 0.2152 0.0304
3.500 0.9809 0.01131 0.00321 -0.1182 0.2002 0.0308
3.750 1.0078 0.01149 0.00332 -0.1181 0.1891 0.0329
4.000 1.0348 0.01163 0.00345 -0.1180 0.1827 0.0354
4.250 1.0617 0.01179 0.00360 -0.1179 0.1766 0.0387
4.750 1.1103 0.01064 0.00416 -0.1171 0.1645 1.0000
5.250 1.1636 0.01106 0.00453 -0.1169 0.1547 1.0000
5.500 1.1899 0.01128 0.00472 -0.1167 0.1493 1.0000
5.750 1.2159 0.01154 0.00494 -0.1165 0.1424 1.0000
6.000 1.2421 0.01177 0.00515 -0.1163 0.1353 1.0000
6.250 1.2675 0.01208 0.00539 -0.1160 0.1246 1.0000
6.750 1.3125 0.01333 0.00632 -0.1146 0.0741 1.0000
7.000 1.3372 0.01366 0.00665 -0.1142 0.0677 1.0000
7.250 1.3541 0.01489 0.00761 -0.1125 0.0193 1.0000
7.500 1.3776 0.01531 0.00803 -0.1119 0.0148 1.0000
7.750 1.4013 0.01569 0.00844 -0.1113 0.0132 1.0000
8.000 1.4243 0.01612 0.00888 -0.1106 0.0117 1.0000
8.250 1.4471 0.01655 0.00934 -0.1099 0.0107 1.0000
8.500 1.4699 0.01694 0.00976 -0.1091 0.0101 1.0000
8.750 1.4922 0.01737 0.01023 -0.1083 0.0094 1.0000
9.000 1.5136 0.01784 0.01072 -0.1074 0.0087 1.0000
9.250 1.5337 0.01842 0.01133 -0.1063 0.0079 1.0000
9.500 1.5544 0.01889 0.01185 -0.1053 0.0076 1.0000
9.750 1.5745 0.01939 0.01240 -0.1041 0.0072 1.0000
10.000 1.5935 0.01992 0.01297 -0.1028 0.0069 1.0000
10.250 1.6116 0.02047 0.01357 -0.1014 0.0066 1.0000
10.500 1.6285 0.02106 0.01420 -0.0997 0.0063 1.0000
10.750 1.6438 0.02171 0.01489 -0.0978 0.0060 1.0000
11.000 1.6553 0.02248 0.01574 -0.0952 0.0056 1.0000
11.250 1.6659 0.02326 0.01658 -0.0925 0.0054 1.0000
11.500 1.6778 0.02398 0.01737 -0.0902 0.0053 1.0000
11.750 1.6891 0.02478 0.01823 -0.0879 0.0051 1.0000
12.000 1.6994 0.02567 0.01920 -0.0855 0.0049 1.0000
12.250 1.7088 0.02665 0.02026 -0.0831 0.0048 1.0000
12.500 1.7174 0.02771 0.02139 -0.0808 0.0046 1.0000
12.750 1.7254 0.02886 0.02262 -0.0785 0.0045 1.0000
13.000 1.7323 0.03013 0.02396 -0.0763 0.0044 1.0000
13.250 1.7383 0.03152 0.02543 -0.0741 0.0042 1.0000
13.500 1.7429 0.03309 0.02709 -0.0720 0.0041 1.0000
13.750 1.7453 0.03491 0.02899 -0.0700 0.0040 1.0000
14.000 1.7454 0.03707 0.03126 -0.0680 0.0039 1.0000
14.250 1.7421 0.03968 0.03399 -0.0662 0.0038 1.0000
14.500 1.7354 0.04284 0.03727 -0.0647 0.0037 1.0000
14.750 1.7325 0.04581 0.04036 -0.0638 0.0037 1.0000
15.000 1.7279 0.04919 0.04387 -0.0632 0.0037 1.0000
15.250 1.7209 0.05308 0.04788 -0.0631 0.0036 1.0000
15.500 1.7116 0.05761 0.05255 -0.0636 0.0036 1.0000
15.750 1.7011 0.06264 0.05772 -0.0646 0.0036 1.0000
16.000 1.6868 0.06855 0.06378 -0.0663 0.0036 1.0000
16.250 1.6701 0.07500 0.07038 -0.0683 0.0036 1.0000
16.500 1.6515 0.08184 0.07737 -0.0704 0.0035 1.0000
16.750 1.6293 0.08925 0.08492 -0.0728 0.0035 1.0000
17.000 1.6074 0.09662 0.09243 -0.0752 0.0035 1.0000
17.250 1.5842 0.10433 0.10027 -0.0779 0.0035 1.0000
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Polar data table (+)
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