GOE 282 (DAIMLER XIII) AIRFOIL (goe282-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 282 (DAIMLER XIII) AIRFOIL (goe282-il) Reynolds number: 1,000,000 Max Cl/Cd: 118.34 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe282-il-1000000.txt Download as CSV file: xf-goe282-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3311 0.11336 0.11171 -0.0298 1.0000 0.0130
-10.000 -0.3284 0.11079 0.10916 -0.0299 1.0000 0.0134
-9.750 -0.5568 0.02248 0.01956 -0.1042 0.9872 0.0113
-9.500 -0.5260 0.02025 0.01704 -0.1066 0.9861 0.0117
-9.250 -0.4940 0.01888 0.01547 -0.1085 0.9852 0.0119
-9.000 -0.4633 0.01640 0.01265 -0.1108 0.9845 0.0129
-8.750 -0.4295 0.01584 0.01204 -0.1123 0.9839 0.0135
-8.500 -0.3977 0.01537 0.01151 -0.1134 0.9824 0.0141
-8.250 -0.3684 0.01481 0.01084 -0.1139 0.9795 0.0148
-8.000 -0.3372 0.01430 0.01022 -0.1147 0.9772 0.0154
-7.750 -0.3062 0.01324 0.00902 -0.1158 0.9751 0.0165
-7.500 -0.2739 0.01315 0.00894 -0.1167 0.9729 0.0174
-7.250 -0.2420 0.01310 0.00889 -0.1174 0.9707 0.0184
-7.000 -0.2151 0.01288 0.00860 -0.1171 0.9658 0.0193
-6.750 -0.1862 0.01274 0.00840 -0.1172 0.9616 0.0199
-6.500 -0.1580 0.01174 0.00728 -0.1175 0.9581 0.0214
-6.250 -0.1302 0.01165 0.00719 -0.1174 0.9533 0.0223
-6.000 -0.1024 0.01151 0.00702 -0.1172 0.9481 0.0235
-5.750 -0.0740 0.01142 0.00688 -0.1171 0.9436 0.0246
-5.500 -0.0461 0.01138 0.00680 -0.1169 0.9376 0.0254
-5.250 -0.0192 0.01033 0.00559 -0.1168 0.9316 0.0270
-5.000 0.0088 0.01008 0.00532 -0.1168 0.9256 0.0281
-4.750 0.0366 0.00994 0.00515 -0.1166 0.9186 0.0294
-4.500 0.0647 0.00970 0.00485 -0.1165 0.9118 0.0306
-4.250 0.0926 0.00947 0.00456 -0.1163 0.9034 0.0317
-4.000 0.1207 0.00939 0.00443 -0.1161 0.8940 0.0325
-3.750 0.1483 0.00891 0.00383 -0.1159 0.8827 0.0334
-3.500 0.1760 0.00840 0.00323 -0.1158 0.8695 0.0351
-3.250 0.2039 0.00819 0.00296 -0.1156 0.8543 0.0366
-3.000 0.2319 0.00801 0.00271 -0.1155 0.8356 0.0378
-2.750 0.2594 0.00789 0.00248 -0.1152 0.8113 0.0392
-2.500 0.2865 0.00785 0.00227 -0.1148 0.7787 0.0405
-2.250 0.3134 0.00789 0.00214 -0.1145 0.7455 0.0416
-2.000 0.3406 0.00789 0.00197 -0.1142 0.7162 0.0432
-1.750 0.3681 0.00783 0.00178 -0.1140 0.6910 0.0471
-1.500 0.3961 0.00780 0.00168 -0.1139 0.6694 0.0512
-1.250 0.4239 0.00777 0.00157 -0.1138 0.6477 0.0622
-1.000 0.4517 0.00766 0.00157 -0.1139 0.6242 0.1199
-0.750 0.4793 0.00776 0.00160 -0.1138 0.5999 0.1339
-0.500 0.5070 0.00785 0.00163 -0.1137 0.5783 0.1440
-0.250 0.5348 0.00796 0.00165 -0.1136 0.5609 0.1494
0.000 0.5627 0.00801 0.00167 -0.1136 0.5467 0.1570
0.250 0.5907 0.00809 0.00170 -0.1136 0.5343 0.1628
0.500 0.6187 0.00815 0.00173 -0.1136 0.5232 0.1706
1.000 0.6749 0.00825 0.00182 -0.1136 0.5041 0.1905
1.250 0.7029 0.00830 0.00187 -0.1136 0.4953 0.2026
1.500 0.7311 0.00833 0.00191 -0.1137 0.4863 0.2165
1.750 0.7592 0.00836 0.00197 -0.1137 0.4775 0.2383
2.000 0.7871 0.00834 0.00205 -0.1138 0.4676 0.2921
2.250 0.8084 0.00694 0.00222 -0.1127 0.4557 1.0000
2.500 0.8357 0.00712 0.00229 -0.1126 0.4362 1.0000
2.750 0.8630 0.00730 0.00236 -0.1125 0.4131 1.0000
3.000 0.8899 0.00752 0.00247 -0.1123 0.3914 1.0000
3.250 0.9164 0.00779 0.00259 -0.1121 0.3647 1.0000
3.500 0.9425 0.00810 0.00275 -0.1118 0.3360 1.0000
3.750 0.9679 0.00848 0.00295 -0.1115 0.3046 1.0000
4.000 0.9933 0.00885 0.00317 -0.1111 0.2760 1.0000
4.250 1.0192 0.00917 0.00337 -0.1108 0.2555 1.0000
4.500 1.0454 0.00943 0.00356 -0.1106 0.2420 1.0000
4.750 1.0715 0.00970 0.00375 -0.1104 0.2302 1.0000
5.000 1.0976 0.00996 0.00395 -0.1101 0.2184 1.0000
5.250 1.1238 0.01020 0.00414 -0.1099 0.2070 1.0000
5.500 1.1496 0.01047 0.00434 -0.1096 0.1939 1.0000
5.750 1.1744 0.01084 0.00460 -0.1092 0.1732 1.0000
6.000 1.1893 0.01225 0.00544 -0.1073 0.0825 1.0000
6.250 1.2114 0.01287 0.00591 -0.1064 0.0594 1.0000
6.500 1.2307 0.01376 0.00655 -0.1051 0.0229 1.0000
6.750 1.2537 0.01426 0.00705 -0.1043 0.0148 1.0000
7.000 1.2773 0.01467 0.00750 -0.1036 0.0132 1.0000
7.250 1.3008 0.01506 0.00795 -0.1028 0.0122 1.0000
7.500 1.3239 0.01547 0.00840 -0.1021 0.0115 1.0000
7.750 1.3461 0.01594 0.00892 -0.1012 0.0109 1.0000
8.000 1.3672 0.01649 0.00953 -0.1001 0.0103 1.0000
8.250 1.3865 0.01719 0.01029 -0.0987 0.0097 1.0000
8.500 1.4021 0.01817 0.01138 -0.0967 0.0092 1.0000
8.750 1.4225 0.01866 0.01191 -0.0955 0.0090 1.0000
9.000 1.4416 0.01922 0.01252 -0.0942 0.0086 1.0000
9.250 1.4592 0.01983 0.01318 -0.0926 0.0082 1.0000
9.500 1.4750 0.02052 0.01393 -0.0907 0.0078 1.0000
9.750 1.4879 0.02129 0.01475 -0.0883 0.0075 1.0000
10.000 1.4974 0.02213 0.01565 -0.0853 0.0073 1.0000
10.250 1.5048 0.02314 0.01674 -0.0822 0.0071 1.0000
10.500 1.5083 0.02445 0.01813 -0.0787 0.0069 1.0000
10.750 1.5046 0.02629 0.02008 -0.0745 0.0067 1.0000
11.000 1.4942 0.02874 0.02264 -0.0700 0.0066 1.0000
11.250 1.5036 0.02991 0.02388 -0.0681 0.0065 1.0000
11.500 1.5107 0.03130 0.02535 -0.0662 0.0064 1.0000
11.750 1.5160 0.03291 0.02704 -0.0642 0.0063 1.0000
12.000 1.5191 0.03481 0.02902 -0.0623 0.0062 1.0000
12.250 1.5211 0.03690 0.03120 -0.0606 0.0061 1.0000
12.500 1.5216 0.03927 0.03367 -0.0592 0.0060 1.0000
12.750 1.5213 0.04187 0.03636 -0.0580 0.0059 1.0000
13.000 1.5200 0.04470 0.03929 -0.0570 0.0058 1.0000
13.250 1.5181 0.04773 0.04241 -0.0563 0.0057 1.0000
13.500 1.5162 0.05089 0.04566 -0.0559 0.0056 1.0000
13.750 1.5148 0.05409 0.04895 -0.0557 0.0054 1.0000
14.000 1.5123 0.05752 0.05247 -0.0558 0.0053 1.0000
14.250 1.5093 0.06113 0.05617 -0.0560 0.0052 1.0000
14.500 1.5061 0.06490 0.06002 -0.0564 0.0051 1.0000
14.750 1.5017 0.06887 0.06408 -0.0570 0.0051 1.0000
15.000 1.4970 0.07297 0.06827 -0.0577 0.0050 1.0000
15.250 1.4916 0.07722 0.07261 -0.0585 0.0049 1.0000
15.500 1.4857 0.08155 0.07702 -0.0594 0.0049 1.0000
15.750 1.4798 0.08582 0.08138 -0.0601 0.0048 1.0000
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