SG6051 (sg6051-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: SG6051 (sg6051-il) Reynolds number: 1,000,000 Max Cl/Cd: 133.55 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sg6051-il-1000000.txt Download as CSV file: xf-sg6051-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.7264 0.05777 0.05613 -0.0571 1.0000 0.0061
-11.500 -0.7818 0.03846 0.03628 -0.0770 0.9777 0.0059
-11.250 -0.7965 0.03381 0.03124 -0.0760 0.9527 0.0059
-11.000 -0.7986 0.03031 0.02737 -0.0745 0.9380 0.0058
-10.750 -0.7919 0.02756 0.02427 -0.0733 0.9276 0.0058
-10.500 -0.7786 0.02532 0.02174 -0.0726 0.9191 0.0059
-10.250 -0.7617 0.02363 0.01979 -0.0719 0.9122 0.0060
-10.000 -0.7419 0.02216 0.01812 -0.0715 0.9056 0.0061
-9.750 -0.7213 0.02084 0.01657 -0.0710 0.8998 0.0062
-9.500 -0.6991 0.01956 0.01509 -0.0708 0.8943 0.0063
-9.250 -0.6760 0.01839 0.01372 -0.0705 0.8890 0.0064
-9.000 -0.6526 0.01733 0.01246 -0.0702 0.8842 0.0064
-8.750 -0.6276 0.01637 0.01136 -0.0701 0.8795 0.0065
-8.500 -0.6021 0.01554 0.01038 -0.0701 0.8746 0.0067
-8.250 -0.5763 0.01485 0.00954 -0.0700 0.8701 0.0068
-8.000 -0.5494 0.01426 0.00884 -0.0701 0.8660 0.0069
-7.750 -0.5238 0.01319 0.00762 -0.0701 0.8615 0.0075
-7.500 -0.4968 0.01263 0.00697 -0.0702 0.8572 0.0079
-7.250 -0.4693 0.01221 0.00647 -0.0703 0.8530 0.0084
-7.000 -0.4411 0.01180 0.00599 -0.0706 0.8488 0.0090
-6.750 -0.4129 0.01143 0.00555 -0.0708 0.8445 0.0095
-6.500 -0.3851 0.01097 0.00503 -0.0709 0.8403 0.0113
-6.250 -0.3568 0.01058 0.00463 -0.0712 0.8362 0.0158
-6.000 -0.3281 0.01033 0.00444 -0.0716 0.8319 0.0230
-5.750 -0.2991 0.01028 0.00437 -0.0719 0.8277 0.0261
-5.500 -0.2706 0.01009 0.00416 -0.0722 0.8236 0.0296
-5.250 -0.2414 0.00998 0.00406 -0.0727 0.8197 0.0321
-5.000 -0.2121 0.00990 0.00395 -0.0731 0.8155 0.0335
-4.750 -0.1835 0.00959 0.00360 -0.0734 0.8115 0.0372
-4.500 -0.1545 0.00945 0.00344 -0.0738 0.8075 0.0398
-4.250 -0.1251 0.00933 0.00331 -0.0742 0.8034 0.0421
-4.000 -0.0960 0.00910 0.00305 -0.0746 0.7991 0.0460
-3.750 -0.0670 0.00894 0.00287 -0.0750 0.7951 0.0503
-3.500 -0.0376 0.00882 0.00273 -0.0754 0.7911 0.0533
-3.250 -0.0082 0.00860 0.00251 -0.0758 0.7868 0.0607
-3.000 0.0211 0.00843 0.00235 -0.0762 0.7825 0.0709
-2.750 0.0502 0.00824 0.00221 -0.0767 0.7785 0.0949
-2.500 0.0795 0.00791 0.00209 -0.0772 0.7741 0.1457
-2.250 0.1085 0.00747 0.00194 -0.0778 0.7695 0.2369
-2.000 0.1371 0.00703 0.00186 -0.0784 0.7650 0.3613
-1.750 0.1666 0.00690 0.00183 -0.0789 0.7602 0.4011
-1.500 0.1961 0.00681 0.00179 -0.0794 0.7553 0.4263
-1.250 0.2254 0.00674 0.00174 -0.0798 0.7507 0.4521
-1.000 0.2549 0.00664 0.00172 -0.0803 0.7461 0.4761
-0.750 0.2844 0.00653 0.00169 -0.0808 0.7413 0.5071
-0.500 0.3135 0.00637 0.00168 -0.0813 0.7365 0.5664
-0.250 0.3421 0.00599 0.00171 -0.0817 0.7318 0.6936
0.000 0.3682 0.00560 0.00177 -0.0813 0.7266 0.8329
0.250 0.3881 0.00538 0.00179 -0.0791 0.7213 0.9335
0.500 0.4166 0.00529 0.00173 -0.0790 0.7156 0.9852
1.000 0.4842 0.00531 0.00167 -0.0819 0.7035 1.0000
1.250 0.5130 0.00534 0.00168 -0.0822 0.6968 1.0000
1.500 0.5416 0.00541 0.00169 -0.0825 0.6899 1.0000
1.750 0.5706 0.00544 0.00171 -0.0828 0.6822 1.0000
2.000 0.5994 0.00551 0.00174 -0.0832 0.6749 1.0000
2.250 0.6284 0.00556 0.00178 -0.0836 0.6665 1.0000
2.500 0.6573 0.00563 0.00182 -0.0839 0.6578 1.0000
2.750 0.6861 0.00572 0.00187 -0.0843 0.6484 1.0000
3.000 0.7151 0.00579 0.00193 -0.0846 0.6388 1.0000
3.250 0.7438 0.00589 0.00199 -0.0850 0.6276 1.0000
3.500 0.7724 0.00600 0.00207 -0.0853 0.6153 1.0000
3.750 0.8010 0.00612 0.00216 -0.0856 0.6026 1.0000
4.000 0.8294 0.00625 0.00225 -0.0859 0.5861 1.0000
4.250 0.8574 0.00642 0.00236 -0.0861 0.5654 1.0000
4.500 0.8849 0.00664 0.00250 -0.0863 0.5402 1.0000
4.750 0.9119 0.00693 0.00267 -0.0864 0.5087 1.0000
5.000 0.9379 0.00731 0.00288 -0.0863 0.4689 1.0000
5.250 0.9634 0.00775 0.00315 -0.0862 0.4268 1.0000
5.500 0.9880 0.00827 0.00345 -0.0860 0.3782 1.0000
5.750 1.0112 0.00891 0.00382 -0.0855 0.3237 1.0000
6.000 1.0345 0.00951 0.00420 -0.0851 0.2760 1.0000
6.250 1.0574 0.01011 0.00460 -0.0846 0.2322 1.0000
6.500 1.0797 0.01074 0.00502 -0.0840 0.1910 1.0000
6.750 1.1012 0.01141 0.00547 -0.0833 0.1509 1.0000
7.000 1.1225 0.01206 0.00594 -0.0825 0.1164 1.0000
7.250 1.1439 0.01266 0.00640 -0.0817 0.0901 1.0000
7.500 1.1650 0.01325 0.00687 -0.0809 0.0694 1.0000
7.750 1.1863 0.01379 0.00733 -0.0800 0.0546 1.0000
8.000 1.2074 0.01432 0.00781 -0.0792 0.0440 1.0000
8.250 1.2284 0.01482 0.00829 -0.0783 0.0370 1.0000
8.500 1.2484 0.01536 0.00879 -0.0772 0.0318 1.0000
8.750 1.2693 0.01579 0.00926 -0.0762 0.0291 1.0000
9.000 1.2887 0.01629 0.00976 -0.0751 0.0265 1.0000
9.250 1.3057 0.01690 0.01039 -0.0735 0.0234 1.0000
9.500 1.3245 0.01733 0.01087 -0.0722 0.0218 1.0000
9.750 1.3380 0.01795 0.01148 -0.0700 0.0195 1.0000
10.000 1.3516 0.01862 0.01220 -0.0679 0.0172 1.0000
10.250 1.3665 0.01927 0.01286 -0.0662 0.0152 1.0000
10.500 1.3782 0.02018 0.01380 -0.0641 0.0133 1.0000
10.750 1.3932 0.02090 0.01457 -0.0625 0.0123 1.0000
11.000 1.4065 0.02176 0.01546 -0.0609 0.0113 1.0000
11.250 1.4147 0.02303 0.01680 -0.0586 0.0103 1.0000
11.500 1.4281 0.02395 0.01778 -0.0571 0.0100 1.0000
11.750 1.4409 0.02493 0.01882 -0.0556 0.0095 1.0000
12.000 1.4531 0.02597 0.01992 -0.0542 0.0091 1.0000
12.250 1.4647 0.02709 0.02110 -0.0527 0.0086 1.0000
12.500 1.4740 0.02840 0.02246 -0.0511 0.0082 1.0000
12.750 1.4786 0.03013 0.02429 -0.0492 0.0078 1.0000
13.000 1.4804 0.03216 0.02643 -0.0471 0.0076 1.0000
13.250 1.4892 0.03360 0.02795 -0.0458 0.0074 1.0000
13.500 1.4969 0.03518 0.02962 -0.0445 0.0073 1.0000
13.750 1.5033 0.03690 0.03143 -0.0432 0.0071 1.0000
14.000 1.5091 0.03872 0.03334 -0.0419 0.0069 1.0000
14.250 1.5142 0.04062 0.03532 -0.0408 0.0067 1.0000
14.500 1.5187 0.04262 0.03741 -0.0397 0.0065 1.0000
14.750 1.5229 0.04470 0.03957 -0.0387 0.0063 1.0000
15.000 1.5256 0.04701 0.04196 -0.0379 0.0061 1.0000
15.250 1.5258 0.04965 0.04470 -0.0370 0.0059 1.0000
15.500 1.5221 0.05283 0.04798 -0.0363 0.0058 1.0000
15.750 1.5129 0.05678 0.05207 -0.0356 0.0056 1.0000
16.000 1.4990 0.06145 0.05690 -0.0352 0.0055 1.0000
16.250 1.4941 0.06520 0.06077 -0.0352 0.0054 1.0000
16.500 1.4926 0.06862 0.06431 -0.0354 0.0053 1.0000
16.750 1.4894 0.07238 0.06818 -0.0358 0.0053 1.0000
17.000 1.4841 0.07653 0.07245 -0.0364 0.0052 1.0000
17.250 1.4780 0.08087 0.07692 -0.0373 0.0052 1.0000
17.500 1.4706 0.08553 0.08170 -0.0383 0.0051 1.0000
17.750 1.4614 0.09061 0.08691 -0.0397 0.0050 1.0000
18.000 1.4512 0.09599 0.09241 -0.0414 0.0050 1.0000
18.250 1.4403 0.10158 0.09813 -0.0433 0.0049 1.0000
18.500 1.4275 0.10762 0.10430 -0.0456 0.0049 1.0000
18.750 1.4147 0.11385 0.11066 -0.0481 0.0048 1.0000
19.000 1.4002 0.12052 0.11746 -0.0510 0.0048 1.0000
19.250 1.3863 0.12724 0.12431 -0.0542 0.0048 1.0000
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