GOE 276 (DAIMLER VII) AIRFOIL (goe276-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 276 (DAIMLER VII) AIRFOIL (goe276-il) Reynolds number: 500,000 Max Cl/Cd: 97.57 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe276-il-500000.txt Download as CSV file: xf-goe276-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 276 (DAIMLER VII) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3913 0.09996 0.09769 -0.0204 1.0000 0.0176
-8.250 -0.3940 0.09715 0.09492 -0.0214 1.0000 0.0176
-8.000 -0.3953 0.09416 0.09197 -0.0225 1.0000 0.0176
-7.750 -0.3908 0.09061 0.08844 -0.0251 1.0000 0.0177
-7.500 -0.3897 0.08628 0.08414 -0.0242 1.0000 0.0179
-7.250 -0.3846 0.08345 0.08133 -0.0229 1.0000 0.0181
-7.000 -0.3795 0.08071 0.07862 -0.0231 1.0000 0.0183
-6.750 -0.3746 0.07798 0.07591 -0.0239 1.0000 0.0186
-6.500 -0.3718 0.07547 0.07343 -0.0242 1.0000 0.0190
-6.250 -0.3562 0.07203 0.06998 -0.0280 0.9987 0.0199
-6.000 -0.3096 0.06589 0.06372 -0.0413 0.9957 0.0220
-5.750 -0.2600 0.05919 0.05683 -0.0537 0.9929 0.0224
-5.500 -0.2227 0.05364 0.05111 -0.0604 0.9896 0.0225
-5.250 -0.2011 0.04776 0.04520 -0.0646 0.9869 0.0232
-5.000 -0.1710 0.04509 0.04249 -0.0679 0.9847 0.0240
-4.750 -0.1368 0.04181 0.03910 -0.0720 0.9801 0.0256
-4.500 -0.0850 0.03839 0.03526 -0.0771 0.9760 0.0288
-4.250 -0.0460 0.03491 0.03148 -0.0806 0.9731 0.0289
-4.000 -0.0180 0.02904 0.02549 -0.0845 0.9682 0.0304
-3.750 0.0135 0.02711 0.02348 -0.0865 0.9620 0.0315
-3.500 0.0481 0.02509 0.02128 -0.0886 0.9559 0.0336
-3.250 0.0873 0.02507 0.02091 -0.0893 0.9477 0.0375
-3.000 0.1215 0.02047 0.01593 -0.0920 0.9393 0.0392
-2.750 0.1534 0.01893 0.01433 -0.0935 0.9299 0.0407
-2.500 0.1840 0.01781 0.01306 -0.0942 0.9188 0.0430
-2.250 0.2142 0.01728 0.01230 -0.0942 0.9068 0.0471
-2.000 0.2440 0.01597 0.01062 -0.0943 0.8953 0.0508
-1.750 0.2711 0.01486 0.00948 -0.0945 0.8831 0.0532
-1.500 0.2984 0.01431 0.00881 -0.0942 0.8682 0.0574
-1.250 0.3261 0.01552 0.00980 -0.0932 0.8503 0.0623
-1.000 0.3532 0.01293 0.00713 -0.0937 0.8337 0.0689
-0.500 0.4107 0.01156 0.00527 -0.0922 0.7964 0.0501
-0.250 0.4377 0.01083 0.00446 -0.0917 0.7665 0.0471
0.000 0.4633 0.01046 0.00385 -0.0909 0.7050 0.0463
0.250 0.4864 0.01052 0.00339 -0.0898 0.6006 0.0450
0.500 0.5114 0.01060 0.00312 -0.0892 0.5271 0.0447
0.750 0.5380 0.01062 0.00293 -0.0890 0.4889 0.0452
1.000 0.5654 0.01060 0.00279 -0.0889 0.4683 0.0463
1.250 0.5930 0.01060 0.00270 -0.0888 0.4538 0.0473
1.500 0.6207 0.01062 0.00266 -0.0888 0.4427 0.0485
1.750 0.6485 0.01061 0.00259 -0.0888 0.4331 0.0514
2.000 0.6764 0.01063 0.00258 -0.0888 0.4243 0.0556
2.250 0.7040 0.01071 0.00261 -0.0887 0.4163 0.0670
2.500 0.7256 0.00879 0.00276 -0.0878 0.4099 1.0000
2.750 0.7531 0.00897 0.00285 -0.0877 0.4026 1.0000
3.000 0.7809 0.00910 0.00296 -0.0877 0.3952 1.0000
3.250 0.8082 0.00929 0.00307 -0.0876 0.3865 1.0000
3.500 0.8360 0.00939 0.00318 -0.0876 0.3785 1.0000
3.750 0.8632 0.00957 0.00331 -0.0875 0.3704 1.0000
4.000 0.8909 0.00968 0.00344 -0.0874 0.3615 1.0000
4.250 0.9183 0.00984 0.00358 -0.0874 0.3528 1.0000
4.500 0.9455 0.01000 0.00372 -0.0873 0.3429 1.0000
4.750 0.9729 0.01014 0.00388 -0.0872 0.3320 1.0000
5.000 0.9999 0.01031 0.00403 -0.0871 0.3173 1.0000
5.500 1.0528 0.01079 0.00439 -0.0867 0.2806 1.0000
5.750 1.0786 0.01111 0.00464 -0.0865 0.2589 1.0000
6.000 1.1039 0.01150 0.00492 -0.0862 0.2351 1.0000
6.250 1.1291 0.01190 0.00523 -0.0858 0.2148 1.0000
6.500 1.1543 0.01229 0.00556 -0.0855 0.1939 1.0000
6.750 1.1787 0.01279 0.00595 -0.0851 0.1648 1.0000
7.000 1.2015 0.01352 0.00645 -0.0845 0.1299 1.0000
7.250 1.2242 0.01426 0.00704 -0.0838 0.1016 1.0000
7.500 1.2399 0.01601 0.00827 -0.0822 0.0266 1.0000
7.750 1.2620 0.01683 0.00913 -0.0813 0.0209 1.0000
8.000 1.2849 0.01746 0.00985 -0.0805 0.0191 1.0000
8.250 1.3065 0.01822 0.01070 -0.0795 0.0175 1.0000
8.500 1.3259 0.01924 0.01182 -0.0782 0.0162 1.0000
8.750 1.3420 0.02057 0.01331 -0.0764 0.0153 1.0000
9.000 1.3611 0.02145 0.01430 -0.0751 0.0148 1.0000
9.250 1.3783 0.02247 0.01543 -0.0735 0.0143 1.0000
9.500 1.3943 0.02353 0.01660 -0.0717 0.0137 1.0000
9.750 1.4093 0.02463 0.01778 -0.0699 0.0130 1.0000
10.000 1.4221 0.02583 0.01906 -0.0678 0.0124 1.0000
10.250 1.4309 0.02731 0.02063 -0.0651 0.0120 1.0000
10.500 1.4349 0.02908 0.02250 -0.0618 0.0117 1.0000
10.750 1.4328 0.03128 0.02480 -0.0576 0.0114 1.0000
11.000 1.4310 0.03395 0.02760 -0.0537 0.0112 1.0000
11.250 1.4369 0.03534 0.02912 -0.0510 0.0110 1.0000
11.500 1.4419 0.03691 0.03084 -0.0485 0.0109 1.0000
11.750 1.4456 0.03877 0.03285 -0.0460 0.0108 1.0000
12.000 1.4479 0.04089 0.03513 -0.0438 0.0106 1.0000
12.250 1.4487 0.04327 0.03767 -0.0417 0.0105 1.0000
12.500 1.4479 0.04594 0.04053 -0.0399 0.0104 1.0000
12.750 1.4454 0.04886 0.04362 -0.0383 0.0103 1.0000
13.000 1.4412 0.05202 0.04698 -0.0371 0.0102 1.0000
13.250 1.4355 0.05549 0.05063 -0.0364 0.0101 1.0000
13.500 1.4282 0.05925 0.05457 -0.0361 0.0099 1.0000
13.750 1.4190 0.06356 0.05907 -0.0364 0.0098 1.0000
14.000 1.4090 0.06817 0.06386 -0.0374 0.0097 1.0000
14.250 1.3983 0.07318 0.06904 -0.0390 0.0096 1.0000
14.500 1.3842 0.07908 0.07514 -0.0412 0.0096 1.0000
14.750 1.3695 0.08531 0.08155 -0.0440 0.0096 1.0000
15.000 1.3539 0.09204 0.08846 -0.0473 0.0096 1.0000
15.250 1.3369 0.09936 0.09597 -0.0512 0.0097 1.0000
15.500 1.3188 0.10706 0.10384 -0.0553 0.0097 1.0000
15.750 1.3004 0.11509 0.11203 -0.0598 0.0098 1.0000
16.000 1.2820 0.12346 0.12057 -0.0647 0.0099 1.0000
16.250 1.2632 0.13228 0.12953 -0.0701 0.0100 1.0000
16.500 1.2448 0.14146 0.13885 -0.0758 0.0101 1.0000
16.750 1.2261 0.15135 0.14888 -0.0821 0.0103 1.0000
17.000 1.2074 0.16183 0.15949 -0.0888 0.0105 1.0000
17.250 1.1868 0.17340 0.17116 -0.0962 0.0107 1.0000
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