GOE 281 (DAIMLER XII) AIRFOIL (goe281-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 281 (DAIMLER XII) AIRFOIL (goe281-il) Reynolds number: 500,000 Max Cl/Cd: 95.33 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe281-il-500000-n5.txt Download as CSV file: xf-goe281-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 281 (DAIMLER XII) 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3297 0.09592 0.09375 -0.0265 1.0000 0.0075
-8.250 -0.3283 0.09287 0.09073 -0.0272 1.0000 0.0075
-8.000 -0.3244 0.08951 0.08740 -0.0289 0.9974 0.0076
-7.750 -0.3121 0.08515 0.08304 -0.0336 0.9901 0.0078
-7.500 -0.2973 0.08038 0.07827 -0.0395 0.9824 0.0080
-7.250 -0.2796 0.07410 0.07198 -0.0480 0.9747 0.0084
-7.000 -0.2604 0.07024 0.06810 -0.0534 0.9666 0.0089
-6.750 -0.2407 0.06734 0.06518 -0.0572 0.9583 0.0093
-6.500 -0.2202 0.06324 0.06103 -0.0624 0.9493 0.0096
-6.250 -0.1991 0.05872 0.05645 -0.0676 0.9387 0.0100
-6.000 -0.1756 0.05380 0.05142 -0.0731 0.9279 0.0105
-5.750 -0.1454 0.04501 0.04240 -0.0817 0.9169 0.0118
-5.500 -0.1228 0.04365 0.04097 -0.0827 0.9056 0.0122
-5.250 -0.0983 0.04124 0.03844 -0.0845 0.8926 0.0128
-4.750 -0.0382 0.02982 0.02627 -0.0904 0.8653 0.0158
-4.500 -0.0142 0.02924 0.02560 -0.0905 0.8497 0.0163
-4.250 0.0117 0.02760 0.02375 -0.0910 0.8331 0.0171
-4.000 0.0393 0.02502 0.02084 -0.0915 0.8163 0.0181
-3.750 0.0703 0.02088 0.01601 -0.0916 0.8014 0.0209
-3.500 0.0964 0.01990 0.01489 -0.0919 0.7864 0.0213
-3.250 0.1232 0.01898 0.01379 -0.0921 0.7718 0.0219
-3.000 0.1505 0.01804 0.01263 -0.0922 0.7557 0.0227
-2.750 0.1783 0.01710 0.01143 -0.0922 0.7386 0.0241
-2.500 0.2065 0.01595 0.00998 -0.0921 0.7215 0.0246
-2.250 0.2345 0.01507 0.00883 -0.0920 0.7055 0.0251
-2.000 0.2627 0.01432 0.00785 -0.0920 0.6927 0.0254
-1.750 0.2909 0.01387 0.00721 -0.0920 0.6807 0.0260
-1.500 0.3189 0.01355 0.00672 -0.0920 0.6681 0.0264
-1.250 0.3468 0.01287 0.00587 -0.0920 0.6557 0.0263
-1.000 0.3747 0.01239 0.00524 -0.0919 0.6435 0.0264
-0.750 0.4026 0.01206 0.00479 -0.0919 0.6317 0.0266
-0.500 0.4307 0.01172 0.00436 -0.0919 0.6221 0.0270
-0.250 0.4584 0.01104 0.00363 -0.0920 0.6132 0.0277
0.000 0.4861 0.01069 0.00324 -0.0920 0.6015 0.0282
0.250 0.5138 0.01046 0.00298 -0.0920 0.5884 0.0286
0.500 0.5415 0.01030 0.00277 -0.0920 0.5730 0.0290
0.750 0.5692 0.01019 0.00262 -0.0921 0.5566 0.0300
1.000 0.5969 0.01011 0.00250 -0.0921 0.5391 0.0309
1.250 0.6242 0.01008 0.00237 -0.0921 0.5114 0.0308
1.500 0.6506 0.01021 0.00230 -0.0919 0.4709 0.0307
1.750 0.6772 0.01035 0.00229 -0.0918 0.4430 0.0307
2.000 0.7042 0.01045 0.00230 -0.0917 0.4259 0.0309
2.250 0.7315 0.01052 0.00232 -0.0917 0.4141 0.0312
2.500 0.7590 0.01059 0.00235 -0.0917 0.4048 0.0316
2.750 0.7862 0.01070 0.00241 -0.0917 0.3944 0.0325
3.000 0.8136 0.01079 0.00248 -0.0917 0.3836 0.0338
3.250 0.8408 0.01090 0.00256 -0.0916 0.3733 0.0352
3.500 0.8679 0.01103 0.00267 -0.0916 0.3603 0.0377
3.750 0.8948 0.01117 0.00280 -0.0915 0.3456 0.0458
4.000 0.9171 0.00962 0.00311 -0.0909 0.3299 1.0000
4.250 0.9429 0.00996 0.00330 -0.0907 0.2982 1.0000
4.500 0.9668 0.01052 0.00358 -0.0903 0.2515 1.0000
4.750 0.9914 0.01098 0.00388 -0.0900 0.2235 1.0000
5.000 1.0164 0.01139 0.00417 -0.0897 0.2033 1.0000
5.250 1.0414 0.01178 0.00446 -0.0894 0.1806 1.0000
5.500 1.0642 0.01243 0.00486 -0.0888 0.1372 1.0000
5.750 1.0872 0.01305 0.00530 -0.0883 0.1094 1.0000
6.000 1.1094 0.01375 0.00580 -0.0876 0.0776 1.0000
6.250 1.1272 0.01499 0.00674 -0.0862 0.0177 1.0000
6.500 1.1513 0.01541 0.00723 -0.0857 0.0140 1.0000
6.750 1.1754 0.01580 0.00769 -0.0851 0.0125 1.0000
7.000 1.1989 0.01625 0.00821 -0.0846 0.0112 1.0000
7.250 1.2217 0.01675 0.00881 -0.0839 0.0102 1.0000
7.500 1.2433 0.01739 0.00954 -0.0830 0.0093 1.0000
7.750 1.2632 0.01819 0.01045 -0.0818 0.0085 1.0000
8.000 1.2849 0.01872 0.01105 -0.0810 0.0078 1.0000
8.250 1.3051 0.01938 0.01178 -0.0800 0.0072 1.0000
8.500 1.3242 0.02013 0.01262 -0.0787 0.0068 1.0000
8.750 1.3422 0.02091 0.01348 -0.0774 0.0064 1.0000
9.000 1.3582 0.02182 0.01445 -0.0758 0.0061 1.0000
9.250 1.3691 0.02308 0.01582 -0.0734 0.0058 1.0000
9.500 1.3788 0.02428 0.01713 -0.0709 0.0056 1.0000
9.750 1.3877 0.02529 0.01824 -0.0681 0.0055 1.0000
10.000 1.3956 0.02636 0.01944 -0.0654 0.0052 1.0000
10.250 1.4029 0.02754 0.02072 -0.0628 0.0050 1.0000
10.500 1.4103 0.02878 0.02206 -0.0605 0.0047 1.0000
10.750 1.4159 0.03021 0.02359 -0.0581 0.0045 1.0000
11.000 1.4200 0.03184 0.02532 -0.0559 0.0044 1.0000
11.250 1.4236 0.03362 0.02721 -0.0540 0.0042 1.0000
11.500 1.4264 0.03556 0.02925 -0.0522 0.0041 1.0000
11.750 1.4283 0.03772 0.03151 -0.0508 0.0041 1.0000
12.000 1.4288 0.04013 0.03403 -0.0495 0.0040 1.0000
12.250 1.4277 0.04284 0.03687 -0.0485 0.0039 1.0000
12.500 1.4242 0.04595 0.04009 -0.0476 0.0038 1.0000
12.750 1.4172 0.04959 0.04385 -0.0468 0.0037 1.0000
13.000 1.4143 0.05291 0.04730 -0.0464 0.0037 1.0000
13.250 1.4113 0.05631 0.05084 -0.0461 0.0036 1.0000
13.500 1.4075 0.05990 0.05459 -0.0460 0.0036 1.0000
13.750 1.4026 0.06371 0.05854 -0.0460 0.0035 1.0000
14.000 1.3968 0.06770 0.06269 -0.0461 0.0035 1.0000
14.250 1.3904 0.07191 0.06706 -0.0465 0.0034 1.0000
14.500 1.3831 0.07640 0.07170 -0.0470 0.0034 1.0000
14.750 1.3750 0.08110 0.07657 -0.0478 0.0033 1.0000
15.000 1.3659 0.08613 0.08176 -0.0489 0.0033 1.0000
15.250 1.3561 0.09149 0.08729 -0.0504 0.0033 1.0000
15.500 1.3455 0.09716 0.09312 -0.0523 0.0032 1.0000
15.750 1.3340 0.10314 0.09927 -0.0545 0.0032 1.0000
16.000 1.3221 0.10943 0.10572 -0.0572 0.0032 1.0000
16.250 1.3101 0.11594 0.11239 -0.0602 0.0032 1.0000
16.500 1.2974 0.12279 0.11940 -0.0635 0.0031 1.0000
16.750 1.2848 0.12982 0.12658 -0.0672 0.0031 1.0000
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Polar data table (+)
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