GOE 282 (DAIMLER XIII) AIRFOIL (goe282-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 282 (DAIMLER XIII) AIRFOIL (goe282-il) Reynolds number: 1,000,000 Max Cl/Cd: 105.1 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe282-il-1000000-n5.txt Download as CSV file: xf-goe282-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.3617 0.11369 0.11204 -0.0312 1.0000 0.0049
-10.750 -0.3618 0.11011 0.10848 -0.0319 1.0000 0.0050
-10.500 -0.5839 0.02577 0.02288 -0.1119 0.9789 0.0054
-10.250 -0.5606 0.02046 0.01717 -0.1152 0.9763 0.0056
-10.000 -0.5357 0.01869 0.01519 -0.1160 0.9718 0.0058
-9.750 -0.5088 0.01736 0.01366 -0.1167 0.9676 0.0060
-9.500 -0.4807 0.01629 0.01243 -0.1174 0.9640 0.0062
-9.250 -0.4545 0.01544 0.01143 -0.1175 0.9584 0.0064
-9.000 -0.4273 0.01445 0.01029 -0.1178 0.9539 0.0068
-8.750 -0.3999 0.01364 0.00935 -0.1181 0.9498 0.0073
-8.500 -0.3728 0.01300 0.00860 -0.1181 0.9443 0.0078
-8.250 -0.3452 0.01244 0.00793 -0.1182 0.9391 0.0082
-8.000 -0.3175 0.01196 0.00735 -0.1183 0.9339 0.0088
-7.750 -0.2898 0.01151 0.00680 -0.1183 0.9278 0.0094
-7.250 -0.2342 0.01066 0.00580 -0.1183 0.9159 0.0120
-7.000 -0.2063 0.01034 0.00540 -0.1182 0.9088 0.0135
-6.750 -0.1781 0.01009 0.00514 -0.1182 0.9024 0.0157
-6.500 -0.1499 0.00987 0.00487 -0.1182 0.8958 0.0174
-6.250 -0.1215 0.00971 0.00470 -0.1183 0.8899 0.0192
-6.000 -0.0931 0.00963 0.00461 -0.1183 0.8827 0.0211
-5.750 -0.0647 0.00953 0.00447 -0.1183 0.8749 0.0226
-5.500 -0.0364 0.00944 0.00431 -0.1182 0.8652 0.0236
-5.250 -0.0080 0.00937 0.00419 -0.1182 0.8549 0.0241
-5.000 0.0202 0.00913 0.00387 -0.1182 0.8427 0.0251
-4.750 0.0482 0.00890 0.00355 -0.1181 0.8259 0.0265
-4.500 0.0759 0.00882 0.00337 -0.1180 0.8036 0.0277
-4.250 0.1031 0.00882 0.00323 -0.1177 0.7738 0.0288
-4.000 0.1302 0.00883 0.00308 -0.1174 0.7418 0.0297
-3.750 0.1575 0.00881 0.00289 -0.1172 0.7148 0.0304
-3.500 0.1855 0.00873 0.00269 -0.1171 0.6950 0.0308
-3.250 0.2136 0.00866 0.00252 -0.1171 0.6763 0.0313
-3.000 0.2415 0.00862 0.00236 -0.1170 0.6542 0.0317
-2.750 0.2694 0.00860 0.00222 -0.1170 0.6293 0.0322
-2.500 0.2969 0.00866 0.00213 -0.1169 0.5976 0.0327
-2.250 0.3242 0.00872 0.00203 -0.1167 0.5657 0.0334
-2.000 0.3520 0.00871 0.00188 -0.1166 0.5421 0.0357
-1.750 0.3799 0.00872 0.00181 -0.1166 0.5241 0.0381
-1.500 0.4082 0.00872 0.00176 -0.1166 0.5121 0.0406
-1.250 0.4365 0.00872 0.00171 -0.1167 0.5037 0.0430
-1.000 0.4650 0.00870 0.00167 -0.1168 0.4964 0.0476
-0.500 0.5218 0.00854 0.00163 -0.1170 0.4819 0.1022
-0.250 0.5501 0.00856 0.00165 -0.1171 0.4741 0.1159
0.000 0.5785 0.00858 0.00167 -0.1172 0.4661 0.1260
0.250 0.6066 0.00863 0.00170 -0.1172 0.4566 0.1341
0.500 0.6348 0.00868 0.00173 -0.1172 0.4462 0.1407
0.750 0.6629 0.00872 0.00176 -0.1173 0.4365 0.1488
1.000 0.6909 0.00879 0.00181 -0.1173 0.4256 0.1581
1.250 0.7187 0.00886 0.00187 -0.1173 0.4127 0.1698
1.500 0.7463 0.00896 0.00193 -0.1173 0.3979 0.1758
1.750 0.7738 0.00908 0.00201 -0.1172 0.3810 0.1836
2.000 0.8010 0.00923 0.00210 -0.1171 0.3617 0.1922
2.500 0.8530 0.00978 0.00241 -0.1166 0.2991 0.2168
2.750 0.8788 0.01007 0.00259 -0.1164 0.2700 0.2362
3.000 0.9054 0.01024 0.00276 -0.1163 0.2533 0.2723
3.500 0.9532 0.00919 0.00317 -0.1150 0.2347 1.0000
3.750 0.9802 0.00937 0.00331 -0.1149 0.2262 1.0000
4.000 1.0067 0.00961 0.00348 -0.1148 0.2150 1.0000
4.250 1.0329 0.00986 0.00366 -0.1145 0.2039 1.0000
4.500 1.0594 0.01008 0.00383 -0.1144 0.1940 1.0000
4.750 1.0855 0.01033 0.00402 -0.1141 0.1809 1.0000
5.250 1.1265 0.01203 0.00507 -0.1120 0.0727 1.0000
5.500 1.1506 0.01245 0.00540 -0.1114 0.0577 1.0000
5.750 1.1743 0.01290 0.00576 -0.1108 0.0430 1.0000
6.000 1.1952 0.01365 0.00637 -0.1097 0.0136 1.0000
6.250 1.2200 0.01395 0.00669 -0.1092 0.0114 1.0000
6.500 1.2446 0.01426 0.00702 -0.1087 0.0103 1.0000
6.750 1.2685 0.01461 0.00740 -0.1081 0.0090 1.0000
7.000 1.2922 0.01498 0.00780 -0.1075 0.0081 1.0000
7.250 1.3158 0.01533 0.00817 -0.1068 0.0075 1.0000
7.500 1.3389 0.01570 0.00857 -0.1061 0.0069 1.0000
7.750 1.3614 0.01612 0.00901 -0.1053 0.0064 1.0000
8.000 1.3829 0.01659 0.00954 -0.1043 0.0058 1.0000
8.250 1.4048 0.01701 0.00998 -0.1034 0.0055 1.0000
8.500 1.4258 0.01747 0.01048 -0.1024 0.0051 1.0000
8.750 1.4462 0.01795 0.01099 -0.1013 0.0048 1.0000
9.000 1.4658 0.01846 0.01153 -0.1000 0.0046 1.0000
9.250 1.4837 0.01905 0.01218 -0.0985 0.0043 1.0000
9.500 1.4994 0.01975 0.01294 -0.0966 0.0041 1.0000
9.750 1.5155 0.02034 0.01359 -0.0947 0.0040 1.0000
10.000 1.5286 0.02097 0.01428 -0.0923 0.0038 1.0000
10.250 1.5414 0.02165 0.01501 -0.0900 0.0036 1.0000
10.500 1.5542 0.02235 0.01578 -0.0878 0.0035 1.0000
10.750 1.5663 0.02312 0.01660 -0.0855 0.0033 1.0000
11.000 1.5784 0.02391 0.01744 -0.0834 0.0032 1.0000
11.250 1.5896 0.02478 0.01839 -0.0813 0.0031 1.0000
11.500 1.5994 0.02579 0.01945 -0.0790 0.0030 1.0000
11.750 1.6070 0.02697 0.02071 -0.0767 0.0029 1.0000
12.000 1.6108 0.02850 0.02234 -0.0741 0.0028 1.0000
12.250 1.6150 0.03006 0.02400 -0.0717 0.0027 1.0000
12.500 1.6201 0.03164 0.02567 -0.0697 0.0027 1.0000
12.750 1.6238 0.03340 0.02753 -0.0677 0.0026 1.0000
13.000 1.6263 0.03536 0.02959 -0.0660 0.0026 1.0000
13.250 1.6272 0.03758 0.03192 -0.0644 0.0025 1.0000
13.500 1.6267 0.04010 0.03455 -0.0630 0.0025 1.0000
13.750 1.6246 0.04292 0.03748 -0.0620 0.0024 1.0000
14.000 1.6217 0.04602 0.04070 -0.0613 0.0024 1.0000
14.250 1.6172 0.04948 0.04429 -0.0609 0.0023 1.0000
14.500 1.6111 0.05329 0.04822 -0.0608 0.0023 1.0000
14.750 1.6037 0.05746 0.05251 -0.0610 0.0023 1.0000
15.000 1.5951 0.06200 0.05718 -0.0616 0.0022 1.0000
15.250 1.5857 0.06680 0.06210 -0.0625 0.0022 1.0000
15.500 1.5731 0.07220 0.06763 -0.0636 0.0022 1.0000
15.750 1.5615 0.07754 0.07310 -0.0649 0.0022 1.0000
16.000 1.5475 0.08337 0.07905 -0.0664 0.0021 1.0000
16.250 1.5330 0.08931 0.08511 -0.0680 0.0021 1.0000
16.500 1.5175 0.09556 0.09148 -0.0699 0.0021 1.0000
16.750 1.5033 0.10175 0.09779 -0.0719 0.0021 1.0000
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Polar data table (+)
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