GOE 277 (DAIMLER VIII) AIRFOIL (goe277-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 277 (DAIMLER VIII) AIRFOIL (goe277-il) Reynolds number: 200,000 Max Cl/Cd: 73.5 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe277-il-200000.txt Download as CSV file: xf-goe277-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3377 0.09090 0.08752 -0.0246 1.0000 0.0368
-7.500 -0.3429 0.08888 0.08558 -0.0254 1.0000 0.0377
-7.250 -0.3450 0.08678 0.08354 -0.0299 1.0000 0.0384
-7.000 -0.3428 0.08432 0.08110 -0.0342 1.0000 0.0388
-6.750 -0.3386 0.08143 0.07819 -0.0371 1.0000 0.0390
-6.500 -0.3326 0.07840 0.07512 -0.0387 1.0000 0.0391
-6.250 -0.3385 0.07291 0.06974 -0.0360 1.0000 0.0398
-6.000 -0.3376 0.07026 0.06713 -0.0331 1.0000 0.0404
-5.750 -0.3346 0.06787 0.06477 -0.0315 1.0000 0.0412
-5.500 -0.3299 0.06547 0.06238 -0.0308 1.0000 0.0422
-5.250 -0.3007 0.06160 0.05844 -0.0360 0.9968 0.0450
-5.000 -0.2245 0.05674 0.05291 -0.0529 0.9902 0.0505
-4.750 -0.2021 0.04944 0.04577 -0.0567 0.9859 0.0525
-4.500 -0.0893 0.03047 0.02640 -0.0711 0.9608 0.0640
-4.250 -0.0647 0.02371 0.01985 -0.0746 0.9578 0.0670
-4.000 -0.0312 0.02086 0.01691 -0.0775 0.9507 0.0719
-3.750 0.0081 0.01724 0.01286 -0.0818 0.9450 0.0811
-3.500 0.0398 0.01514 0.01073 -0.0837 0.9377 0.0879
-3.250 0.0725 0.01280 0.00817 -0.0858 0.9294 0.0989
-3.000 0.1023 0.01107 0.00620 -0.0869 0.9185 0.1120
-2.750 0.1313 0.00960 0.00455 -0.0876 0.9077 0.1268
-2.500 0.1585 0.00833 0.00319 -0.0879 0.8959 0.1429
-2.250 0.1836 0.00746 0.00224 -0.0876 0.8813 0.1643
-2.000 0.2070 0.00656 0.00130 -0.0872 0.8651 0.1921
-1.750 0.2613 0.01776 0.01079 -0.0907 0.8870 0.0772
-1.500 0.2899 0.01604 0.00889 -0.0903 0.8711 0.0724
-1.250 0.3183 0.01503 0.00764 -0.0895 0.8539 0.0701
-1.000 0.3453 0.01436 0.00685 -0.0887 0.8339 0.0716
-0.750 0.3722 0.01367 0.00601 -0.0879 0.8127 0.0709
-0.500 0.3989 0.01310 0.00531 -0.0870 0.7907 0.0707
-0.250 0.4253 0.01267 0.00477 -0.0862 0.7679 0.0716
0.000 0.4516 0.01236 0.00434 -0.0855 0.7453 0.0733
0.250 0.4780 0.01215 0.00402 -0.0848 0.7231 0.0758
0.500 0.5043 0.01197 0.00375 -0.0843 0.7008 0.0812
0.750 0.5308 0.01187 0.00355 -0.0837 0.6778 0.0892
1.000 0.5574 0.01175 0.00338 -0.0832 0.6536 0.1090
1.250 0.5807 0.00970 0.00331 -0.0820 0.6304 1.0000
1.500 0.6068 0.00990 0.00326 -0.0814 0.6038 1.0000
1.750 0.6327 0.01013 0.00328 -0.0809 0.5780 1.0000
2.000 0.6584 0.01041 0.00333 -0.0804 0.5538 1.0000
2.250 0.6843 0.01072 0.00344 -0.0799 0.5307 1.0000
2.500 0.7102 0.01106 0.00358 -0.0795 0.5107 1.0000
2.750 0.7364 0.01136 0.00377 -0.0792 0.4921 1.0000
3.000 0.7627 0.01168 0.00396 -0.0789 0.4766 1.0000
3.250 0.7891 0.01200 0.00417 -0.0786 0.4638 1.0000
3.500 0.8156 0.01233 0.00440 -0.0784 0.4527 1.0000
3.750 0.8423 0.01261 0.00465 -0.0782 0.4421 1.0000
4.000 0.8689 0.01293 0.00491 -0.0780 0.4330 1.0000
4.250 0.8955 0.01324 0.00516 -0.0778 0.4243 1.0000
4.500 0.9221 0.01354 0.00548 -0.0777 0.4157 1.0000
4.750 0.9485 0.01389 0.00575 -0.0775 0.4082 1.0000
5.000 0.9749 0.01416 0.00608 -0.0773 0.4001 1.0000
5.250 1.0014 0.01453 0.00640 -0.0771 0.3935 1.0000
5.500 1.0278 0.01482 0.00679 -0.0769 0.3866 1.0000
5.750 1.0539 0.01517 0.00710 -0.0767 0.3796 1.0000
6.000 1.0798 0.01547 0.00749 -0.0764 0.3719 1.0000
6.250 1.1057 0.01582 0.00784 -0.0761 0.3647 1.0000
6.500 1.1308 0.01607 0.00821 -0.0757 0.3556 1.0000
6.750 1.1556 0.01638 0.00852 -0.0753 0.3459 1.0000
7.000 1.1798 0.01664 0.00878 -0.0747 0.3345 1.0000
7.250 1.2037 0.01682 0.00913 -0.0741 0.3232 1.0000
7.500 1.2279 0.01709 0.00950 -0.0736 0.3132 1.0000
7.750 1.2509 0.01728 0.00977 -0.0729 0.2992 1.0000
8.000 1.2739 0.01747 0.01007 -0.0721 0.2840 1.0000
8.250 1.2963 0.01766 0.01037 -0.0713 0.2639 1.0000
8.500 1.3179 0.01793 0.01066 -0.0704 0.2281 1.0000
8.750 1.3276 0.01951 0.01160 -0.0683 0.1340 1.0000
9.000 1.3335 0.02173 0.01336 -0.0656 0.0725 1.0000
9.250 1.3420 0.02352 0.01489 -0.0631 0.0412 1.0000
9.500 1.3526 0.02495 0.01638 -0.0608 0.0354 1.0000
9.750 1.3620 0.02634 0.01791 -0.0584 0.0324 1.0000
10.000 1.3697 0.02769 0.01939 -0.0558 0.0302 1.0000
10.250 1.3720 0.02919 0.02102 -0.0526 0.0289 1.0000
10.500 1.3712 0.03101 0.02296 -0.0494 0.0279 1.0000
10.750 1.3673 0.03323 0.02528 -0.0464 0.0272 1.0000
11.000 1.3615 0.03583 0.02799 -0.0437 0.0265 1.0000
11.250 1.3605 0.03823 0.03050 -0.0418 0.0262 1.0000
11.500 1.3623 0.04054 0.03293 -0.0402 0.0258 1.0000
11.750 1.3644 0.04293 0.03547 -0.0389 0.0254 1.0000
12.000 1.3672 0.04536 0.03802 -0.0377 0.0248 1.0000
12.250 1.3701 0.04784 0.04062 -0.0367 0.0241 1.0000
12.500 1.3732 0.05037 0.04326 -0.0358 0.0233 1.0000
12.750 1.3765 0.05294 0.04594 -0.0348 0.0228 1.0000
13.000 1.3811 0.05548 0.04859 -0.0337 0.0225 1.0000
13.250 1.3854 0.05814 0.05138 -0.0327 0.0222 1.0000
13.500 1.3889 0.06099 0.05438 -0.0317 0.0220 1.0000
13.750 1.3906 0.06412 0.05770 -0.0310 0.0218 1.0000
14.000 1.3903 0.06758 0.06136 -0.0305 0.0218 1.0000
14.250 1.3868 0.07144 0.06545 -0.0304 0.0218 1.0000
14.500 1.3803 0.07579 0.07004 -0.0307 0.0220 1.0000
14.750 1.3695 0.08077 0.07529 -0.0316 0.0222 1.0000
15.000 1.3546 0.08644 0.08124 -0.0332 0.0224 1.0000
15.250 1.3374 0.09274 0.08781 -0.0356 0.0227 1.0000
15.500 1.3184 0.09961 0.09494 -0.0387 0.0230 1.0000
15.750 1.2985 0.10700 0.10257 -0.0425 0.0232 1.0000
16.000 1.2778 0.11497 0.11077 -0.0469 0.0235 1.0000
16.250 1.2566 0.12350 0.11951 -0.0521 0.0238 1.0000
16.500 1.2346 0.13268 0.12889 -0.0579 0.0242 1.0000
16.750 1.2119 0.14265 0.13903 -0.0645 0.0245 1.0000
17.000 1.1881 0.15360 0.15012 -0.0718 0.0248 1.0000
17.250 1.1624 0.16602 0.16266 -0.0802 0.0253 1.0000
17.500 1.1398 0.17827 0.17497 -0.0878 0.0261 1.0000
17.750 0.8938 0.15530 0.15218 -0.0553 0.0260 1.0000
18.000 0.8079 0.18330 0.18020 -0.0681 0.0334 1.0000
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