GOE 282 (DAIMLER XIII) AIRFOIL (goe282-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 282 (DAIMLER XIII) AIRFOIL (goe282-il) Reynolds number: 500,000 Max Cl/Cd: 94.77 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe282-il-500000-n5.txt Download as CSV file: xf-goe282-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 282 (DAIMLER XIII) 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3345 0.11822 0.11588 -0.0303 1.0000 0.0074
-10.500 -0.3337 0.11470 0.11238 -0.0309 1.0000 0.0074
-9.000 -0.4390 0.02273 0.01899 -0.1115 0.9752 0.0090
-8.750 -0.4133 0.02008 0.01601 -0.1131 0.9710 0.0096
-8.500 -0.3839 0.01865 0.01438 -0.1144 0.9682 0.0104
-8.250 -0.3533 0.01748 0.01300 -0.1156 0.9660 0.0112
-8.000 -0.3234 0.01642 0.01173 -0.1166 0.9631 0.0120
-7.750 -0.2959 0.01548 0.01059 -0.1169 0.9582 0.0128
-7.500 -0.2660 0.01485 0.00989 -0.1175 0.9547 0.0142
-7.250 -0.2348 0.01444 0.00941 -0.1183 0.9516 0.0157
-7.000 -0.2072 0.01400 0.00885 -0.1183 0.9456 0.0173
-6.750 -0.1776 0.01371 0.00852 -0.1186 0.9403 0.0189
-6.500 -0.1476 0.01361 0.00839 -0.1190 0.9357 0.0205
-6.250 -0.1196 0.01334 0.00803 -0.1190 0.9296 0.0223
-6.000 -0.0904 0.01310 0.00769 -0.1191 0.9242 0.0237
-5.750 -0.0621 0.01268 0.00716 -0.1192 0.9183 0.0251
-5.500 -0.0338 0.01237 0.00680 -0.1193 0.9116 0.0266
-5.250 -0.0052 0.01220 0.00658 -0.1194 0.9056 0.0281
-5.000 0.0229 0.01196 0.00627 -0.1193 0.8979 0.0296
-4.750 0.0513 0.01172 0.00593 -0.1193 0.8902 0.0311
-4.500 0.0794 0.01148 0.00560 -0.1192 0.8808 0.0321
-4.250 0.1075 0.01129 0.00531 -0.1191 0.8712 0.0328
-4.000 0.1355 0.01074 0.00465 -0.1191 0.8604 0.0340
-3.750 0.1634 0.01032 0.00413 -0.1190 0.8472 0.0349
-3.500 0.1913 0.01003 0.00375 -0.1189 0.8312 0.0358
-3.250 0.2189 0.00981 0.00342 -0.1186 0.8088 0.0367
-3.000 0.2459 0.00969 0.00314 -0.1182 0.7795 0.0379
-2.750 0.2726 0.00965 0.00291 -0.1178 0.7491 0.0394
-2.500 0.2996 0.00962 0.00272 -0.1175 0.7234 0.0409
-2.250 0.3268 0.00961 0.00255 -0.1172 0.7013 0.0422
-2.000 0.3543 0.00960 0.00241 -0.1170 0.6806 0.0436
-1.750 0.3818 0.00958 0.00228 -0.1168 0.6582 0.0461
-1.500 0.4090 0.00957 0.00215 -0.1166 0.6322 0.0514
-1.250 0.4356 0.00964 0.00207 -0.1163 0.5994 0.0585
-1.000 0.4622 0.00961 0.00206 -0.1161 0.5707 0.1013
-0.750 0.4894 0.00969 0.00209 -0.1160 0.5520 0.1206
-0.500 0.5171 0.00975 0.00210 -0.1159 0.5396 0.1315
-0.250 0.5448 0.00982 0.00213 -0.1159 0.5290 0.1415
0.250 0.6004 0.00993 0.00220 -0.1158 0.5101 0.1587
0.500 0.6281 0.00999 0.00224 -0.1158 0.5016 0.1678
0.750 0.6559 0.01003 0.00230 -0.1157 0.4927 0.1791
1.000 0.6837 0.01010 0.00234 -0.1157 0.4840 0.1870
1.250 0.7112 0.01017 0.00240 -0.1156 0.4740 0.1951
1.500 0.7389 0.01022 0.00246 -0.1156 0.4635 0.2048
2.000 0.7938 0.01036 0.00261 -0.1155 0.4418 0.2358
2.250 0.8212 0.01040 0.00271 -0.1155 0.4293 0.2693
2.500 0.8413 0.00918 0.00296 -0.1142 0.4166 0.8720
3.000 0.8946 0.00944 0.00311 -0.1137 0.3778 1.0000
3.250 0.9198 0.00980 0.00329 -0.1132 0.3448 1.0000
3.500 0.9445 0.01021 0.00350 -0.1128 0.3129 1.0000
3.750 0.9698 0.01056 0.00372 -0.1124 0.2903 1.0000
4.000 0.9954 0.01087 0.00394 -0.1121 0.2729 1.0000
4.250 1.0210 0.01117 0.00416 -0.1117 0.2592 1.0000
4.500 1.0462 0.01150 0.00440 -0.1114 0.2440 1.0000
4.750 1.0711 0.01185 0.00467 -0.1109 0.2277 1.0000
5.000 1.0962 0.01217 0.00492 -0.1106 0.2155 1.0000
5.250 1.1212 0.01250 0.00518 -0.1102 0.2034 1.0000
5.500 1.1459 0.01283 0.00545 -0.1097 0.1894 1.0000
5.750 1.1698 0.01324 0.00575 -0.1092 0.1651 1.0000
6.000 1.1833 0.01470 0.00665 -0.1071 0.0794 1.0000
6.250 1.2048 0.01532 0.00716 -0.1062 0.0609 1.0000
6.500 1.2224 0.01630 0.00789 -0.1046 0.0211 1.0000
6.750 1.2438 0.01687 0.00849 -0.1036 0.0141 1.0000
7.000 1.2658 0.01737 0.00905 -0.1026 0.0122 1.0000
7.250 1.2878 0.01782 0.00957 -0.1017 0.0111 1.0000
7.500 1.3092 0.01831 0.01011 -0.1007 0.0101 1.0000
7.750 1.3296 0.01885 0.01073 -0.0995 0.0092 1.0000
8.000 1.3480 0.01954 0.01153 -0.0980 0.0085 1.0000
8.250 1.3668 0.02014 0.01220 -0.0966 0.0081 1.0000
8.500 1.3849 0.02074 0.01288 -0.0951 0.0077 1.0000
8.750 1.4019 0.02138 0.01359 -0.0934 0.0072 1.0000
9.000 1.4172 0.02204 0.01432 -0.0915 0.0067 1.0000
9.250 1.4296 0.02279 0.01513 -0.0891 0.0063 1.0000
9.500 1.4388 0.02379 0.01622 -0.0862 0.0060 1.0000
9.750 1.4481 0.02480 0.01733 -0.0836 0.0059 1.0000
10.000 1.4579 0.02581 0.01843 -0.0811 0.0057 1.0000
10.250 1.4661 0.02696 0.01968 -0.0785 0.0055 1.0000
10.500 1.4730 0.02823 0.02105 -0.0760 0.0053 1.0000
10.750 1.4785 0.02966 0.02258 -0.0735 0.0051 1.0000
11.000 1.4828 0.03124 0.02427 -0.0711 0.0050 1.0000
11.250 1.4862 0.03297 0.02610 -0.0689 0.0048 1.0000
11.500 1.4891 0.03484 0.02807 -0.0669 0.0047 1.0000
11.750 1.4912 0.03688 0.03020 -0.0651 0.0046 1.0000
12.000 1.4928 0.03909 0.03250 -0.0636 0.0044 1.0000
12.250 1.4930 0.04157 0.03511 -0.0623 0.0043 1.0000
12.500 1.4890 0.04466 0.03831 -0.0613 0.0042 1.0000
12.750 1.4801 0.04852 0.04229 -0.0606 0.0041 1.0000
13.000 1.4794 0.05161 0.04551 -0.0603 0.0040 1.0000
13.250 1.4753 0.05523 0.04925 -0.0602 0.0040 1.0000
13.500 1.4694 0.05923 0.05339 -0.0603 0.0039 1.0000
13.750 1.4623 0.06355 0.05783 -0.0608 0.0038 1.0000
14.000 1.4549 0.06801 0.06241 -0.0614 0.0038 1.0000
14.250 1.4470 0.07264 0.06717 -0.0622 0.0037 1.0000
14.500 1.4390 0.07736 0.07200 -0.0631 0.0037 1.0000
14.750 1.4310 0.08213 0.07688 -0.0640 0.0036 1.0000
15.000 1.4230 0.08690 0.08176 -0.0650 0.0036 1.0000
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Polar data table (+)
Polar graphs
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