SG6050 (sg6050-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: SG6050 (sg6050-il) Reynolds number: 1,000,000 Max Cl/Cd: 126.51 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sg6050-il-1000000.txt Download as CSV file: xf-sg6050-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: SG6050
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
------ -------- --------- --------- -------- -------- --------
-16.500 -0.9166 0.08443 0.08127 -0.0469 1.0000 0.0070
-16.250 -0.9364 0.07751 0.07424 -0.0506 1.0000 0.0070
-16.000 -0.9579 0.07071 0.06734 -0.0542 1.0000 0.0069
-15.750 -0.9785 0.06419 0.06070 -0.0578 1.0000 0.0069
-15.500 -0.9971 0.05801 0.05441 -0.0613 1.0000 0.0069
-15.250 -1.0138 0.05202 0.04831 -0.0649 1.0000 0.0069
-15.000 -1.0252 0.04647 0.04264 -0.0685 1.0000 0.0069
-14.750 -1.0319 0.04130 0.03734 -0.0725 1.0000 0.0070
-14.500 -1.0388 0.03608 0.03197 -0.0768 1.0000 0.0070
-14.250 -1.0458 0.03177 0.02750 -0.0799 1.0000 0.0070
-14.000 -1.0522 0.02874 0.02434 -0.0803 1.0000 0.0071
-13.750 -1.0580 0.02668 0.02216 -0.0786 1.0000 0.0072
-13.500 -1.0637 0.02525 0.02064 -0.0752 1.0000 0.0072
-13.000 -1.0297 0.02253 0.01773 -0.0756 0.9933 0.0075
-12.750 -1.0070 0.02145 0.01658 -0.0761 0.9830 0.0077
-12.500 -0.9879 0.02057 0.01561 -0.0755 0.9655 0.0079
-12.250 -0.9710 0.01982 0.01476 -0.0742 0.9447 0.0080
-12.000 -0.9539 0.01916 0.01396 -0.0727 0.9255 0.0082
-11.750 -0.9343 0.01853 0.01321 -0.0717 0.9093 0.0084
-11.500 -0.9128 0.01793 0.01250 -0.0711 0.8956 0.0087
-11.250 -0.8899 0.01739 0.01185 -0.0706 0.8842 0.0089
-11.000 -0.8675 0.01673 0.01108 -0.0701 0.8740 0.0092
-10.750 -0.8444 0.01607 0.01032 -0.0698 0.8644 0.0098
-10.500 -0.8198 0.01556 0.00973 -0.0696 0.8560 0.0104
-10.250 -0.7943 0.01511 0.00921 -0.0695 0.8479 0.0110
-10.000 -0.7692 0.01457 0.00860 -0.0694 0.8410 0.0122
-9.750 -0.7435 0.01404 0.00802 -0.0693 0.8341 0.0142
-9.500 -0.7190 0.01336 0.00732 -0.0692 0.8276 0.0210
-9.250 -0.6932 0.01275 0.00681 -0.0693 0.8216 0.0338
-9.000 -0.6656 0.01247 0.00654 -0.0695 0.8156 0.0404
-8.750 -0.6378 0.01226 0.00631 -0.0697 0.8099 0.0449
-8.500 -0.6091 0.01207 0.00609 -0.0700 0.8049 0.0476
-8.250 -0.5808 0.01184 0.00586 -0.0703 0.7996 0.0509
-8.000 -0.5522 0.01170 0.00567 -0.0706 0.7946 0.0534
-7.750 -0.5231 0.01159 0.00551 -0.0710 0.7900 0.0548
-7.500 -0.4947 0.01129 0.00520 -0.0713 0.7853 0.0583
-7.250 -0.4659 0.01112 0.00503 -0.0717 0.7806 0.0614
-7.000 -0.4368 0.01103 0.00488 -0.0720 0.7760 0.0637
-6.750 -0.4077 0.01082 0.00464 -0.0724 0.7718 0.0662
-6.500 -0.3788 0.01057 0.00439 -0.0728 0.7675 0.0697
-6.250 -0.3497 0.01041 0.00420 -0.0732 0.7632 0.0727
-6.000 -0.3204 0.01031 0.00405 -0.0736 0.7588 0.0750
-5.750 -0.2911 0.01006 0.00381 -0.0740 0.7548 0.0799
-5.500 -0.2617 0.00986 0.00362 -0.0745 0.7505 0.0847
-5.250 -0.2323 0.00974 0.00344 -0.0749 0.7460 0.0884
-5.000 -0.2030 0.00952 0.00325 -0.0753 0.7415 0.0976
-4.750 -0.1735 0.00928 0.00306 -0.0758 0.7370 0.1109
-4.500 -0.1443 0.00901 0.00287 -0.0763 0.7324 0.1347
-4.250 -0.1154 0.00868 0.00267 -0.0768 0.7279 0.1747
-4.000 -0.0865 0.00823 0.00247 -0.0773 0.7239 0.2374
-3.750 -0.0570 0.00794 0.00236 -0.0779 0.7195 0.2859
-3.500 -0.0273 0.00782 0.00230 -0.0784 0.7150 0.3153
-3.250 0.0024 0.00779 0.00226 -0.0789 0.7103 0.3334
-3.000 0.0327 0.00772 0.00224 -0.0794 0.7062 0.3476
-2.750 0.0628 0.00767 0.00220 -0.0799 0.7014 0.3578
-2.500 0.0928 0.00768 0.00216 -0.0804 0.6967 0.3653
-2.250 0.1228 0.00765 0.00213 -0.0809 0.6921 0.3726
-2.000 0.1530 0.00763 0.00211 -0.0814 0.6870 0.3792
-1.750 0.1830 0.00761 0.00207 -0.0819 0.6817 0.3855
-1.500 0.2129 0.00761 0.00205 -0.0824 0.6765 0.3916
-1.250 0.2431 0.00760 0.00203 -0.0829 0.6710 0.3976
-1.000 0.2730 0.00757 0.00203 -0.0834 0.6654 0.4091
-0.750 0.3029 0.00758 0.00202 -0.0839 0.6602 0.4182
-0.500 0.3329 0.00754 0.00201 -0.0844 0.6546 0.4246
-0.250 0.3628 0.00755 0.00199 -0.0849 0.6486 0.4292
0.000 0.3927 0.00756 0.00198 -0.0854 0.6430 0.4331
0.250 0.4227 0.00752 0.00197 -0.0859 0.6368 0.4388
0.750 0.4823 0.00753 0.00198 -0.0869 0.6238 0.4505
1.000 0.5119 0.00753 0.00199 -0.0874 0.6165 0.4586
1.250 0.5417 0.00753 0.00201 -0.0879 0.6097 0.4681
1.500 0.5713 0.00752 0.00204 -0.0884 0.6023 0.4817
1.750 0.6008 0.00750 0.00208 -0.0889 0.5952 0.5032
2.000 0.6304 0.00742 0.00212 -0.0894 0.5875 0.5441
2.250 0.6597 0.00729 0.00219 -0.0900 0.5799 0.6167
2.500 0.6888 0.00710 0.00227 -0.0905 0.5715 0.7078
2.750 0.7158 0.00689 0.00241 -0.0903 0.5636 0.8233
3.000 0.7418 0.00687 0.00252 -0.0898 0.5548 0.8812
3.500 0.7927 0.00699 0.00269 -0.0887 0.5366 0.9290
3.750 0.8164 0.00705 0.00277 -0.0877 0.5265 0.9484
4.000 0.8401 0.00714 0.00283 -0.0867 0.5160 0.9683
4.250 0.8679 0.00724 0.00290 -0.0868 0.5049 0.9856
4.500 0.9008 0.00733 0.00297 -0.0881 0.4937 0.9976
4.750 0.9297 0.00748 0.00308 -0.0885 0.4827 1.0000
5.000 0.9576 0.00767 0.00322 -0.0888 0.4704 1.0000
5.250 0.9858 0.00784 0.00335 -0.0891 0.4576 1.0000
5.500 1.0137 0.00803 0.00350 -0.0893 0.4453 1.0000
5.750 1.0412 0.00823 0.00367 -0.0895 0.4332 1.0000
6.000 1.0684 0.00846 0.00385 -0.0896 0.4208 1.0000
6.500 1.1220 0.00895 0.00424 -0.0897 0.3929 1.0000
6.750 1.1483 0.00921 0.00445 -0.0897 0.3784 1.0000
7.000 1.1744 0.00948 0.00468 -0.0897 0.3640 1.0000
7.250 1.1999 0.00977 0.00493 -0.0895 0.3492 1.0000
7.500 1.2242 0.01013 0.00521 -0.0891 0.3310 1.0000
7.750 1.2472 0.01057 0.00554 -0.0886 0.3085 1.0000
8.000 1.2693 0.01103 0.00589 -0.0879 0.2855 1.0000
8.250 1.2908 0.01151 0.00627 -0.0871 0.2653 1.0000
8.500 1.3119 0.01197 0.00666 -0.0862 0.2458 1.0000
8.750 1.3310 0.01252 0.00711 -0.0850 0.2243 1.0000
9.000 1.3483 0.01313 0.00760 -0.0835 0.2029 1.0000
9.250 1.3633 0.01380 0.00815 -0.0816 0.1806 1.0000
9.500 1.3741 0.01453 0.00877 -0.0789 0.1603 1.0000
9.750 1.3842 0.01527 0.00944 -0.0762 0.1429 1.0000
10.000 1.3946 0.01609 0.01018 -0.0737 0.1267 1.0000
10.250 1.4052 0.01697 0.01099 -0.0714 0.1122 1.0000
10.500 1.4163 0.01787 0.01184 -0.0693 0.0999 1.0000
10.750 1.4272 0.01885 0.01277 -0.0674 0.0885 1.0000
11.000 1.4379 0.01989 0.01378 -0.0656 0.0782 1.0000
11.250 1.4479 0.02102 0.01487 -0.0638 0.0690 1.0000
11.500 1.4575 0.02224 0.01606 -0.0622 0.0606 1.0000
11.750 1.4669 0.02352 0.01732 -0.0606 0.0533 1.0000
12.000 1.4768 0.02479 0.01858 -0.0592 0.0472 1.0000
12.250 1.4857 0.02618 0.01997 -0.0578 0.0414 1.0000
12.500 1.4932 0.02771 0.02150 -0.0564 0.0360 1.0000
12.750 1.4996 0.02936 0.02314 -0.0549 0.0309 1.0000
13.000 1.5057 0.03107 0.02485 -0.0536 0.0265 1.0000
13.250 1.5110 0.03288 0.02668 -0.0523 0.0225 1.0000
13.500 1.5154 0.03481 0.02862 -0.0510 0.0190 1.0000
13.750 1.5187 0.03685 0.03069 -0.0498 0.0160 1.0000
14.000 1.5218 0.03897 0.03285 -0.0486 0.0139 1.0000
14.250 1.5251 0.04115 0.03507 -0.0476 0.0125 1.0000
14.500 1.5283 0.04340 0.03737 -0.0467 0.0115 1.0000
14.750 1.5325 0.04559 0.03962 -0.0459 0.0109 1.0000
15.000 1.5350 0.04802 0.04211 -0.0452 0.0103 1.0000
15.250 1.5356 0.05072 0.04487 -0.0446 0.0099 1.0000
15.500 1.5357 0.05354 0.04776 -0.0440 0.0095 1.0000
15.750 1.5381 0.05614 0.05044 -0.0437 0.0092 1.0000
16.000 1.5394 0.05892 0.05331 -0.0434 0.0090 1.0000
16.250 1.5397 0.06188 0.05635 -0.0432 0.0088 1.0000
16.500 1.5393 0.06499 0.05954 -0.0431 0.0086 1.0000
16.750 1.5374 0.06833 0.06296 -0.0431 0.0084 1.0000
17.000 1.5342 0.07185 0.06656 -0.0432 0.0082 1.0000
17.250 1.5294 0.07567 0.07046 -0.0434 0.0080 1.0000
17.500 1.5224 0.07986 0.07474 -0.0438 0.0078 1.0000
17.750 1.5131 0.08443 0.07942 -0.0443 0.0077 1.0000
|
Polar data table (+)
Polar graphs
<< Back to SG6050 (sg6050-il)