S6062 8% (s6062-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: S6062 8% (s6062-il) Reynolds number: 50,000 Max Cl/Cd: 34.59 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s6062-il-50000.txt Download as CSV file: xf-s6062-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: S6062 8%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4007 0.09865 0.09235 -0.0028 1.0000 0.2438
-8.500 -0.4035 0.09515 0.08892 -0.0035 1.0000 0.2526
-8.250 -0.5171 0.10300 0.09647 -0.0003 1.0000 0.2495
-8.000 -0.4995 0.09830 0.09174 0.0008 1.0000 0.2621
-7.750 -0.4888 0.09432 0.08778 0.0012 1.0000 0.2736
-7.500 -0.4840 0.09092 0.08445 0.0013 1.0000 0.2862
-7.250 -0.4807 0.08768 0.08128 0.0014 1.0000 0.3000
-7.000 -0.4790 0.08469 0.07837 0.0018 1.0000 0.3159
-6.750 -0.4934 0.08295 0.07678 0.0016 1.0000 0.3340
-6.500 -0.4692 0.07846 0.07228 0.0042 1.0000 0.3552
-5.750 -0.4754 0.05169 0.04427 -0.0367 1.0000 0.1236
-5.500 -0.4586 0.04641 0.03848 -0.0370 1.0000 0.1095
-5.250 -0.4416 0.04239 0.03431 -0.0364 1.0000 0.1047
-5.000 -0.4238 0.03853 0.02992 -0.0359 1.0000 0.1016
-4.750 -0.4045 0.03542 0.02635 -0.0350 1.0000 0.1020
-4.500 -0.3835 0.03261 0.02309 -0.0339 1.0000 0.1033
-4.250 -0.3610 0.02996 0.01998 -0.0327 1.0000 0.1045
-4.000 -0.3372 0.02758 0.01713 -0.0314 1.0000 0.1076
-3.750 -0.3138 0.02545 0.01483 -0.0300 1.0000 0.1156
-3.500 -0.2907 0.02372 0.01293 -0.0286 1.0000 0.1364
-3.250 -0.2678 0.02163 0.01117 -0.0271 1.0000 0.1849
-3.000 -0.2504 0.01845 0.00944 -0.0249 1.0000 0.3836
-2.750 -0.1212 0.01632 0.00846 -0.0338 1.0000 1.0000
-2.500 -0.1225 0.01602 0.00790 -0.0304 1.0000 1.0000
-2.250 -0.1201 0.01585 0.00749 -0.0272 1.0000 1.0000
-2.000 -0.1140 0.01577 0.00715 -0.0243 1.0000 1.0000
-1.750 -0.1040 0.01577 0.00686 -0.0220 1.0000 1.0000
-1.500 -0.0908 0.01582 0.00665 -0.0202 1.0000 1.0000
-1.250 -0.0757 0.01591 0.00649 -0.0187 1.0000 1.0000
-1.000 -0.0592 0.01604 0.00636 -0.0175 1.0000 1.0000
-0.750 -0.0420 0.01622 0.00633 -0.0164 1.0000 1.0000
-0.500 -0.0243 0.01643 0.00636 -0.0155 1.0000 1.0000
-0.250 -0.0062 0.01668 0.00645 -0.0147 1.0000 1.0000
0.000 0.0120 0.01697 0.00659 -0.0140 1.0000 1.0000
0.250 0.0303 0.01730 0.00678 -0.0134 1.0000 1.0000
0.500 0.0485 0.01768 0.00706 -0.0128 1.0000 1.0000
0.750 0.0666 0.01811 0.00740 -0.0124 1.0000 1.0000
1.000 0.0846 0.01858 0.00781 -0.0121 1.0000 1.0000
1.250 0.1024 0.01911 0.00828 -0.0118 1.0000 1.0000
1.500 0.1199 0.01969 0.00883 -0.0116 1.0000 1.0000
1.750 0.1372 0.02034 0.00945 -0.0115 1.0000 1.0000
2.000 0.1677 0.02127 0.01039 -0.0140 0.9940 1.0000
2.250 0.2259 0.02257 0.01177 -0.0215 0.9734 1.0000
2.500 0.2806 0.02370 0.01304 -0.0280 0.9518 1.0000
2.750 0.3397 0.02473 0.01423 -0.0348 0.9295 1.0000
3.000 0.3881 0.02548 0.01517 -0.0392 0.9049 1.0000
3.250 0.4392 0.02608 0.01604 -0.0436 0.8794 1.0000
3.500 0.4945 0.02640 0.01666 -0.0480 0.8529 1.0000
3.750 0.5465 0.02642 0.01700 -0.0509 0.8258 1.0000
4.000 0.5913 0.02621 0.01716 -0.0519 0.7971 1.0000
4.250 0.6305 0.02578 0.01704 -0.0512 0.7667 1.0000
4.500 0.6664 0.02509 0.01662 -0.0492 0.7349 1.0000
4.750 0.6946 0.02450 0.01631 -0.0460 0.6990 1.0000
5.000 0.7216 0.02376 0.01574 -0.0421 0.6594 1.0000
5.250 0.7447 0.02322 0.01531 -0.0380 0.6122 1.0000
5.500 0.7659 0.02282 0.01489 -0.0337 0.5554 1.0000
5.750 0.7832 0.02264 0.01454 -0.0291 0.4817 1.0000
6.000 0.7929 0.02306 0.01442 -0.0244 0.3798 1.0000
6.250 0.7942 0.02489 0.01519 -0.0201 0.2449 1.0000
6.500 0.8054 0.02837 0.01773 -0.0174 0.1503 1.0000
6.750 0.8281 0.03100 0.02007 -0.0161 0.1193 1.0000
7.000 0.8563 0.03383 0.02292 -0.0153 0.1064 1.0000
7.250 0.8830 0.03679 0.02632 -0.0142 0.1002 1.0000
7.500 0.9076 0.04003 0.02986 -0.0134 0.0964 1.0000
7.750 0.9276 0.04386 0.03402 -0.0124 0.0936 1.0000
8.000 0.9415 0.04747 0.03832 -0.0109 0.0917 1.0000
8.250 0.9518 0.05148 0.04291 -0.0096 0.0904 1.0000
8.500 0.9587 0.05594 0.04786 -0.0084 0.0908 1.0000
8.750 0.9630 0.06078 0.05308 -0.0074 0.0923 1.0000
9.000 0.9698 0.06592 0.05842 -0.0068 0.0939 1.0000
9.250 0.9434 0.07120 0.06441 -0.0063 0.0979 1.0000
9.500 0.9163 0.07707 0.07054 -0.0071 0.1010 1.0000
9.750 0.8949 0.08239 0.07593 -0.0081 0.1034 1.0000
10.000 0.8907 0.08794 0.08151 -0.0091 0.1063 1.0000
|
Polar data table (+)
Polar graphs
<< Back to S6062 8% (s6062-il)