GOE 277 (DAIMLER VIII) AIRFOIL (goe277-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 277 (DAIMLER VIII) AIRFOIL (goe277-il) Reynolds number: 500,000 Max Cl/Cd: 98.73 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe277-il-500000-n5.txt Download as CSV file: xf-goe277-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 277 (DAIMLER VIII) 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 -0.3531 0.09123 0.08904 -0.0248 1.0000 0.0092
-8.250 -0.3531 0.08769 0.08553 -0.0260 1.0000 0.0094
-8.000 -0.3590 0.08460 0.08249 -0.0260 1.0000 0.0096
-7.750 -0.3534 0.07924 0.07715 -0.0315 0.9950 0.0099
-7.500 -0.3351 0.07188 0.06978 -0.0420 0.9873 0.0104
-7.250 -0.3115 0.06878 0.06665 -0.0474 0.9806 0.0108
-7.000 -0.2862 0.06527 0.06310 -0.0532 0.9735 0.0113
-6.750 -0.2604 0.05997 0.05774 -0.0610 0.9644 0.0121
-6.500 -0.2325 0.04624 0.04374 -0.0765 0.9526 0.0137
-6.250 -0.2073 0.04427 0.04168 -0.0786 0.9421 0.0141
-6.000 -0.1823 0.04246 0.03978 -0.0803 0.9311 0.0147
-5.750 -0.1534 0.02807 0.02461 -0.0879 0.9210 0.0182
-5.500 -0.1288 0.02732 0.02375 -0.0881 0.9080 0.0186
-5.250 -0.1039 0.02684 0.02317 -0.0880 0.8929 0.0191
-5.000 -0.0790 0.02596 0.02215 -0.0880 0.8751 0.0199
-4.750 -0.0535 0.02338 0.01922 -0.0882 0.8535 0.0211
-4.500 -0.0273 0.01990 0.01518 -0.0881 0.8290 0.0233
-4.250 -0.0012 0.01863 0.01351 -0.0877 0.7990 0.0241
-4.000 0.0239 0.01628 0.01066 -0.0877 0.7720 0.0251
-3.750 0.0501 0.01576 0.00994 -0.0875 0.7490 0.0259
-3.250 0.1040 0.01461 0.00838 -0.0873 0.7149 0.0272
-3.000 0.1314 0.01394 0.00751 -0.0872 0.6993 0.0277
-2.750 0.1589 0.01333 0.00671 -0.0871 0.6835 0.0281
-2.500 0.1865 0.01277 0.00597 -0.0869 0.6675 0.0285
-2.250 0.2141 0.01238 0.00544 -0.0868 0.6513 0.0293
-2.000 0.2417 0.01196 0.00489 -0.0867 0.6335 0.0299
-1.750 0.2691 0.01155 0.00433 -0.0866 0.6137 0.0302
-1.500 0.2964 0.01123 0.00387 -0.0864 0.5916 0.0307
-1.250 0.3235 0.01100 0.00349 -0.0862 0.5681 0.0312
-1.000 0.3508 0.01083 0.00319 -0.0861 0.5464 0.0318
-0.750 0.3781 0.01070 0.00296 -0.0860 0.5271 0.0323
-0.500 0.4055 0.01060 0.00276 -0.0859 0.5105 0.0327
-0.250 0.4330 0.01051 0.00259 -0.0858 0.4949 0.0330
0.000 0.4606 0.01045 0.00245 -0.0857 0.4794 0.0332
0.250 0.4881 0.01035 0.00229 -0.0857 0.4639 0.0339
0.750 0.5432 0.01025 0.00202 -0.0856 0.4305 0.0361
1.000 0.5707 0.01028 0.00196 -0.0855 0.4134 0.0371
1.250 0.5981 0.01033 0.00194 -0.0855 0.3981 0.0386
1.500 0.6256 0.01040 0.00195 -0.0854 0.3853 0.0411
2.000 0.6803 0.00974 0.00217 -0.0859 0.3649 0.4505
2.500 0.7303 0.00877 0.00236 -0.0846 0.3500 1.0000
2.750 0.7575 0.00895 0.00247 -0.0845 0.3429 1.0000
3.000 0.7848 0.00910 0.00257 -0.0845 0.3352 1.0000
3.250 0.8119 0.00930 0.00270 -0.0843 0.3278 1.0000
3.500 0.8392 0.00944 0.00282 -0.0843 0.3219 1.0000
3.750 0.8662 0.00962 0.00296 -0.0842 0.3163 1.0000
4.000 0.8933 0.00979 0.00312 -0.0841 0.3119 1.0000
4.250 0.9206 0.00994 0.00327 -0.0840 0.3076 1.0000
4.500 0.9476 0.01010 0.00343 -0.0839 0.3035 1.0000
5.000 1.0013 0.01045 0.00380 -0.0837 0.2945 1.0000
5.250 1.0282 0.01062 0.00398 -0.0836 0.2902 1.0000
5.500 1.0546 0.01084 0.00419 -0.0834 0.2847 1.0000
5.750 1.0813 0.01101 0.00438 -0.0833 0.2758 1.0000
6.000 1.1076 0.01123 0.00459 -0.0831 0.2658 1.0000
6.250 1.1334 0.01148 0.00480 -0.0829 0.2488 1.0000
6.500 1.1587 0.01179 0.00505 -0.0827 0.2290 1.0000
6.750 1.1819 0.01235 0.00541 -0.0821 0.1888 1.0000
7.000 1.1997 0.01357 0.00620 -0.0810 0.1202 1.0000
7.250 1.2203 0.01443 0.00689 -0.0801 0.0890 1.0000
7.500 1.2426 0.01505 0.00745 -0.0794 0.0717 1.0000
7.750 1.2580 0.01645 0.00852 -0.0779 0.0206 1.0000
8.000 1.2795 0.01710 0.00918 -0.0770 0.0153 1.0000
8.250 1.3019 0.01761 0.00977 -0.0763 0.0135 1.0000
8.500 1.3232 0.01820 0.01042 -0.0754 0.0119 1.0000
8.750 1.3431 0.01891 0.01123 -0.0743 0.0107 1.0000
9.000 1.3627 0.01961 0.01202 -0.0732 0.0099 1.0000
9.250 1.3823 0.02026 0.01275 -0.0722 0.0093 1.0000
9.500 1.4009 0.02096 0.01354 -0.0710 0.0087 1.0000
9.750 1.4183 0.02171 0.01435 -0.0696 0.0081 1.0000
10.000 1.4333 0.02260 0.01530 -0.0680 0.0075 1.0000
10.250 1.4429 0.02382 0.01665 -0.0656 0.0071 1.0000
10.500 1.4536 0.02470 0.01762 -0.0633 0.0069 1.0000
10.750 1.4622 0.02571 0.01874 -0.0607 0.0067 1.0000
11.000 1.4690 0.02689 0.02003 -0.0582 0.0064 1.0000
11.250 1.4745 0.02823 0.02148 -0.0558 0.0062 1.0000
11.500 1.4789 0.02974 0.02309 -0.0536 0.0060 1.0000
11.750 1.4820 0.03146 0.02492 -0.0516 0.0059 1.0000
12.000 1.4848 0.03334 0.02690 -0.0500 0.0057 1.0000
12.250 1.4868 0.03544 0.02911 -0.0487 0.0055 1.0000
12.500 1.4880 0.03779 0.03156 -0.0478 0.0054 1.0000
12.750 1.4875 0.04053 0.03443 -0.0472 0.0052 1.0000
13.000 1.4839 0.04383 0.03785 -0.0470 0.0051 1.0000
13.250 1.4764 0.04782 0.04196 -0.0473 0.0050 1.0000
13.500 1.4679 0.05209 0.04636 -0.0478 0.0049 1.0000
13.750 1.4640 0.05591 0.05032 -0.0484 0.0048 1.0000
14.000 1.4588 0.06003 0.05457 -0.0492 0.0047 1.0000
14.250 1.4516 0.06446 0.05913 -0.0502 0.0047 1.0000
14.500 1.4431 0.06917 0.06397 -0.0513 0.0046 1.0000
14.750 1.4347 0.07394 0.06887 -0.0525 0.0045 1.0000
15.000 1.4255 0.07885 0.07390 -0.0538 0.0045 1.0000
15.250 1.4168 0.08380 0.07897 -0.0552 0.0044 1.0000
15.500 1.4083 0.08878 0.08406 -0.0566 0.0044 1.0000
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Polar data table (+)
Polar graphs
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