SG6051 (sg6051-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: SG6051 (sg6051-il) Reynolds number: 500,000 Max Cl/Cd: 112.95 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sg6051-il-500000.txt Download as CSV file: xf-sg6051-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: SG6051
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3230 0.08031 0.07828 -0.0570 0.9814 0.0166
-10.000 -0.3153 0.07760 0.07557 -0.0585 0.9725 0.0171
-9.750 -0.4941 0.07008 0.06805 -0.0580 0.9949 0.0123
-9.250 -0.6192 0.02658 0.02237 -0.0810 0.9445 0.0103
-9.000 -0.6046 0.02399 0.01938 -0.0799 0.9367 0.0104
-8.750 -0.5868 0.02218 0.01724 -0.0789 0.9302 0.0106
-8.500 -0.5658 0.02067 0.01547 -0.0782 0.9240 0.0109
-8.250 -0.5436 0.01936 0.01393 -0.0776 0.9181 0.0113
-8.000 -0.5210 0.01827 0.01260 -0.0769 0.9131 0.0117
-7.750 -0.4959 0.01731 0.01146 -0.0767 0.9074 0.0122
-7.500 -0.4725 0.01610 0.01008 -0.0762 0.9022 0.0129
-7.250 -0.4474 0.01544 0.00934 -0.0759 0.8978 0.0137
-7.000 -0.4204 0.01487 0.00868 -0.0760 0.8926 0.0150
-6.750 -0.3944 0.01416 0.00785 -0.0758 0.8877 0.0167
-6.250 -0.3389 0.01376 0.00742 -0.0760 0.8786 0.0258
-6.000 -0.3111 0.01355 0.00721 -0.0762 0.8739 0.0309
-5.750 -0.2833 0.01344 0.00699 -0.0762 0.8697 0.0341
-5.500 -0.2558 0.01302 0.00656 -0.0765 0.8651 0.0377
-5.250 -0.2274 0.01287 0.00637 -0.0767 0.8602 0.0409
-5.000 -0.1998 0.01255 0.00598 -0.0768 0.8560 0.0448
-4.750 -0.1718 0.01233 0.00575 -0.0770 0.8519 0.0491
-4.500 -0.1431 0.01210 0.00547 -0.0773 0.8471 0.0523
-4.250 -0.1151 0.01170 0.00500 -0.0775 0.8428 0.0553
-4.000 -0.0873 0.01130 0.00455 -0.0776 0.8390 0.0598
-3.750 -0.0583 0.01106 0.00428 -0.0780 0.8344 0.0642
-3.500 -0.0296 0.01074 0.00394 -0.0783 0.8298 0.0711
-3.250 -0.0010 0.01053 0.00368 -0.0785 0.8258 0.0797
-3.000 0.0276 0.01017 0.00343 -0.0788 0.8217 0.1058
-2.750 0.0559 0.00957 0.00321 -0.0794 0.8170 0.1985
-2.500 0.0835 0.00888 0.00308 -0.0800 0.8127 0.3679
-2.250 0.1121 0.00874 0.00302 -0.0802 0.8089 0.4212
-2.000 0.1412 0.00857 0.00296 -0.0807 0.8041 0.4592
-1.750 0.1700 0.00840 0.00289 -0.0810 0.7994 0.4964
-1.500 0.1986 0.00824 0.00282 -0.0813 0.7952 0.5372
-1.250 0.2272 0.00803 0.00280 -0.0816 0.7905 0.5976
-1.000 0.2548 0.00771 0.00279 -0.0816 0.7853 0.6872
-0.750 0.2785 0.00731 0.00282 -0.0805 0.7809 0.8196
-0.500 0.2974 0.00706 0.00283 -0.0777 0.7761 0.9309
-0.250 0.3403 0.00699 0.00276 -0.0808 0.7713 0.9945
0.000 0.3769 0.00698 0.00268 -0.0829 0.7668 1.0000
0.250 0.4039 0.00701 0.00265 -0.0828 0.7620 1.0000
0.500 0.4315 0.00703 0.00263 -0.0829 0.7563 1.0000
0.750 0.4593 0.00706 0.00259 -0.0830 0.7514 1.0000
1.000 0.4874 0.00710 0.00260 -0.0832 0.7457 1.0000
1.250 0.5157 0.00713 0.00260 -0.0834 0.7395 1.0000
1.500 0.5440 0.00719 0.00260 -0.0835 0.7339 1.0000
1.750 0.5725 0.00722 0.00263 -0.0838 0.7270 1.0000
2.000 0.6009 0.00728 0.00263 -0.0840 0.7208 1.0000
2.250 0.6295 0.00732 0.00268 -0.0843 0.7130 1.0000
2.500 0.6579 0.00739 0.00269 -0.0845 0.7060 1.0000
2.750 0.6865 0.00743 0.00276 -0.0847 0.6975 1.0000
3.000 0.7149 0.00750 0.00280 -0.0849 0.6897 1.0000
3.250 0.7434 0.00755 0.00286 -0.0852 0.6800 1.0000
3.500 0.7718 0.00762 0.00293 -0.0854 0.6707 1.0000
3.750 0.7999 0.00771 0.00299 -0.0856 0.6605 1.0000
4.000 0.8281 0.00779 0.00307 -0.0857 0.6484 1.0000
4.250 0.8561 0.00789 0.00317 -0.0859 0.6360 1.0000
4.500 0.8838 0.00800 0.00328 -0.0860 0.6213 1.0000
4.750 0.9112 0.00815 0.00340 -0.0860 0.6042 1.0000
5.000 0.9384 0.00831 0.00354 -0.0860 0.5850 1.0000
5.250 0.9646 0.00854 0.00370 -0.0859 0.5591 1.0000
5.500 0.9899 0.00885 0.00390 -0.0856 0.5233 1.0000
5.750 1.0143 0.00925 0.00415 -0.0852 0.4862 1.0000
6.000 1.0376 0.00974 0.00448 -0.0846 0.4430 1.0000
6.250 1.0590 0.01040 0.00491 -0.0838 0.3891 1.0000
6.500 1.0785 0.01121 0.00543 -0.0827 0.3291 1.0000
6.750 1.0974 0.01205 0.00598 -0.0816 0.2741 1.0000
7.000 1.1159 0.01288 0.00657 -0.0804 0.2248 1.0000
7.250 1.1338 0.01373 0.00718 -0.0791 0.1805 1.0000
7.500 1.1507 0.01459 0.00783 -0.0776 0.1393 1.0000
7.750 1.1669 0.01547 0.00850 -0.0760 0.1040 1.0000
8.000 1.1825 0.01632 0.00920 -0.0743 0.0773 1.0000
8.250 1.1975 0.01716 0.00992 -0.0725 0.0598 1.0000
8.500 1.2128 0.01792 0.01066 -0.0706 0.0500 1.0000
8.750 1.2285 0.01856 0.01133 -0.0688 0.0444 1.0000
9.000 1.2374 0.01950 0.01225 -0.0659 0.0390 1.0000
9.250 1.2534 0.02009 0.01292 -0.0642 0.0361 1.0000
9.500 1.2658 0.02095 0.01378 -0.0622 0.0326 1.0000
9.750 1.2767 0.02196 0.01487 -0.0600 0.0296 1.0000
10.000 1.2910 0.02278 0.01575 -0.0584 0.0270 1.0000
10.250 1.2978 0.02416 0.01715 -0.0560 0.0241 1.0000
10.500 1.3093 0.02526 0.01835 -0.0542 0.0221 1.0000
10.750 1.3210 0.02637 0.01951 -0.0526 0.0202 1.0000
11.000 1.3263 0.02800 0.02118 -0.0504 0.0186 1.0000
11.250 1.3323 0.02964 0.02292 -0.0484 0.0174 1.0000
11.500 1.3435 0.03087 0.02425 -0.0470 0.0164 1.0000
11.750 1.3532 0.03225 0.02570 -0.0456 0.0155 1.0000
12.000 1.3611 0.03379 0.02731 -0.0441 0.0148 1.0000
12.250 1.3637 0.03584 0.02941 -0.0422 0.0141 1.0000
12.500 1.3608 0.03847 0.03216 -0.0399 0.0136 1.0000
12.750 1.3688 0.04014 0.03395 -0.0387 0.0133 1.0000
13.000 1.3749 0.04200 0.03593 -0.0374 0.0129 1.0000
13.250 1.3803 0.04397 0.03801 -0.0362 0.0124 1.0000
13.500 1.3855 0.04600 0.04014 -0.0352 0.0120 1.0000
13.750 1.3903 0.04807 0.04231 -0.0343 0.0116 1.0000
14.000 1.3941 0.05027 0.04459 -0.0335 0.0112 1.0000
14.250 1.3959 0.05276 0.04716 -0.0327 0.0109 1.0000
14.500 1.3936 0.05578 0.05028 -0.0317 0.0106 1.0000
14.750 1.3852 0.05955 0.05419 -0.0302 0.0103 1.0000
15.000 1.3857 0.06248 0.05728 -0.0299 0.0101 1.0000
15.250 1.3848 0.06567 0.06064 -0.0296 0.0100 1.0000
15.500 1.3823 0.06916 0.06429 -0.0296 0.0098 1.0000
15.750 1.3780 0.07295 0.06825 -0.0297 0.0096 1.0000
16.000 1.3725 0.07703 0.07250 -0.0300 0.0095 1.0000
16.250 1.3657 0.08143 0.07707 -0.0307 0.0093 1.0000
16.500 1.3580 0.08613 0.08193 -0.0317 0.0092 1.0000
16.750 1.3493 0.09110 0.08707 -0.0330 0.0091 1.0000
17.000 1.3392 0.09645 0.09258 -0.0347 0.0089 1.0000
17.250 1.3291 0.10203 0.09831 -0.0368 0.0088 1.0000
17.500 1.3180 0.10798 0.10442 -0.0393 0.0087 1.0000
17.750 1.3055 0.11439 0.11099 -0.0422 0.0086 1.0000
18.000 1.2919 0.12119 0.11795 -0.0456 0.0086 1.0000
18.250 1.2788 0.12816 0.12508 -0.0493 0.0085 1.0000
18.500 1.2620 0.13620 0.13328 -0.0538 0.0085 1.0000
18.750 1.2443 0.14486 0.14212 -0.0590 0.0085 1.0000
19.000 1.2185 0.15598 0.15346 -0.0658 0.0086 1.0000
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