S2062 8% (s2062-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: S2062 8% (s2062-il) Reynolds number: 1,000,000 Max Cl/Cd: 78.87 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s2062-il-1000000-n5.txt Download as CSV file: xf-s2062-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S2062 8%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.5328 0.10876 0.10704 -0.0123 1.0000 0.0028
-10.750 -0.5405 0.10215 0.10046 -0.0148 1.0000 0.0026
-10.250 -0.8084 0.03443 0.03221 -0.0537 1.0000 0.0023
-10.000 -0.8098 0.03064 0.02813 -0.0530 1.0000 0.0023
-9.750 -0.8013 0.02840 0.02569 -0.0520 1.0000 0.0024
-9.500 -0.7930 0.02600 0.02304 -0.0506 1.0000 0.0024
-9.250 -0.7807 0.02427 0.02111 -0.0491 1.0000 0.0025
-9.000 -0.7587 0.02244 0.01906 -0.0496 0.9989 0.0026
-8.750 -0.7312 0.02097 0.01740 -0.0508 0.9970 0.0027
-8.500 -0.7030 0.01955 0.01579 -0.0521 0.9952 0.0028
-8.250 -0.6754 0.01819 0.01422 -0.0530 0.9932 0.0029
-8.000 -0.6477 0.01709 0.01295 -0.0537 0.9908 0.0031
-7.750 -0.6191 0.01586 0.01152 -0.0545 0.9885 0.0032
-7.500 -0.5892 0.01485 0.01034 -0.0555 0.9865 0.0033
-7.250 -0.5585 0.01396 0.00931 -0.0565 0.9849 0.0034
-7.000 -0.5272 0.01309 0.00831 -0.0576 0.9834 0.0036
-6.750 -0.4999 0.01245 0.00756 -0.0578 0.9794 0.0037
-6.500 -0.4711 0.01180 0.00681 -0.0582 0.9755 0.0038
-6.250 -0.4408 0.01128 0.00620 -0.0589 0.9722 0.0039
-6.000 -0.4105 0.01095 0.00582 -0.0596 0.9688 0.0040
-5.750 -0.3844 0.01004 0.00476 -0.0594 0.9624 0.0044
-5.500 -0.3554 0.00952 0.00416 -0.0598 0.9574 0.0047
-5.250 -0.3279 0.00910 0.00368 -0.0597 0.9508 0.0050
-5.000 -0.2999 0.00876 0.00328 -0.0597 0.9440 0.0055
-4.750 -0.2726 0.00848 0.00293 -0.0596 0.9364 0.0060
-4.250 -0.2180 0.00805 0.00237 -0.0592 0.9192 0.0070
-4.000 -0.1909 0.00783 0.00211 -0.0590 0.9100 0.0091
-3.500 -0.1374 0.00727 0.00165 -0.0585 0.8903 0.0419
-3.250 -0.1103 0.00711 0.00150 -0.0584 0.8806 0.0550
-3.000 -0.0834 0.00692 0.00136 -0.0582 0.8703 0.0769
-2.750 -0.0564 0.00678 0.00123 -0.0580 0.8589 0.0955
-2.500 -0.0294 0.00660 0.00111 -0.0578 0.8466 0.1237
-2.250 -0.0024 0.00643 0.00101 -0.0577 0.8340 0.1567
-2.000 0.0248 0.00632 0.00092 -0.0575 0.8212 0.1811
-1.750 0.0518 0.00618 0.00085 -0.0573 0.8073 0.2144
-1.500 0.0789 0.00609 0.00078 -0.0572 0.7914 0.2441
-1.250 0.1057 0.00598 0.00072 -0.0570 0.7735 0.2845
-1.000 0.1326 0.00588 0.00068 -0.0568 0.7539 0.3237
-0.500 0.1859 0.00570 0.00062 -0.0564 0.7098 0.4219
-0.250 0.2124 0.00561 0.00061 -0.0562 0.6863 0.4784
0.000 0.2388 0.00552 0.00062 -0.0559 0.6613 0.5390
0.250 0.2650 0.00544 0.00064 -0.0557 0.6348 0.6052
0.500 0.2911 0.00537 0.00068 -0.0553 0.6076 0.6744
0.750 0.3171 0.00538 0.00074 -0.0549 0.5789 0.7256
1.000 0.3433 0.00546 0.00080 -0.0545 0.5486 0.7613
1.250 0.3693 0.00556 0.00088 -0.0541 0.5162 0.7902
1.500 0.3951 0.00569 0.00096 -0.0537 0.4819 0.8170
1.750 0.4207 0.00582 0.00105 -0.0532 0.4488 0.8420
2.000 0.4461 0.00598 0.00115 -0.0527 0.4132 0.8634
2.250 0.4712 0.00614 0.00125 -0.0520 0.3822 0.8858
2.500 0.4953 0.00628 0.00136 -0.0512 0.3520 0.9123
3.000 0.5445 0.00723 0.00172 -0.0501 0.1947 0.9731
3.250 0.5771 0.00759 0.00190 -0.0515 0.1509 1.0000
3.500 0.6027 0.00793 0.00209 -0.0511 0.1186 1.0000
3.750 0.6282 0.00827 0.00229 -0.0508 0.0876 1.0000
4.000 0.6536 0.00865 0.00254 -0.0505 0.0586 1.0000
4.250 0.6787 0.00907 0.00282 -0.0501 0.0292 1.0000
4.500 0.7042 0.00946 0.00311 -0.0497 0.0142 1.0000
4.750 0.7305 0.00972 0.00336 -0.0494 0.0119 1.0000
5.000 0.7567 0.00999 0.00367 -0.0491 0.0107 1.0000
5.250 0.7829 0.01026 0.00397 -0.0488 0.0102 1.0000
5.500 0.8089 0.01053 0.00428 -0.0485 0.0100 1.0000
5.750 0.8348 0.01084 0.00462 -0.0482 0.0098 1.0000
6.000 0.8604 0.01117 0.00498 -0.0478 0.0095 1.0000
6.250 0.8859 0.01152 0.00537 -0.0475 0.0093 1.0000
6.500 0.9110 0.01191 0.00581 -0.0470 0.0090 1.0000
6.750 0.9359 0.01232 0.00629 -0.0466 0.0088 1.0000
7.000 0.9606 0.01276 0.00678 -0.0461 0.0085 1.0000
7.250 0.9849 0.01323 0.00730 -0.0456 0.0081 1.0000
7.500 1.0089 0.01373 0.00786 -0.0450 0.0079 1.0000
7.750 1.0329 0.01421 0.00838 -0.0445 0.0075 1.0000
8.000 1.0561 0.01477 0.00899 -0.0438 0.0071 1.0000
8.250 1.0777 0.01556 0.00986 -0.0429 0.0068 1.0000
8.500 1.0960 0.01680 0.01125 -0.0416 0.0064 1.0000
8.750 1.1154 0.01788 0.01244 -0.0404 0.0063 1.0000
9.000 1.1383 0.01839 0.01302 -0.0397 0.0062 1.0000
9.250 1.1610 0.01890 0.01359 -0.0391 0.0060 1.0000
9.500 1.1834 0.01942 0.01418 -0.0384 0.0058 1.0000
9.750 1.2045 0.02009 0.01494 -0.0376 0.0057 1.0000
10.000 1.2247 0.02085 0.01581 -0.0366 0.0054 1.0000
10.250 1.2440 0.02168 0.01673 -0.0356 0.0052 1.0000
10.500 1.2629 0.02248 0.01764 -0.0345 0.0050 1.0000
10.750 1.2819 0.02321 0.01845 -0.0335 0.0048 1.0000
11.000 1.3013 0.02381 0.01912 -0.0325 0.0046 1.0000
11.250 1.3214 0.02425 0.01960 -0.0317 0.0044 1.0000
11.500 1.3405 0.02476 0.02015 -0.0307 0.0042 1.0000
11.750 1.3591 0.02528 0.02070 -0.0297 0.0040 1.0000
12.000 1.3738 0.02612 0.02161 -0.0282 0.0039 1.0000
12.250 1.3788 0.02747 0.02311 -0.0254 0.0037 1.0000
12.500 1.3845 0.02861 0.02436 -0.0226 0.0036 1.0000
12.750 1.3901 0.02977 0.02565 -0.0201 0.0036 1.0000
13.000 1.3955 0.03100 0.02699 -0.0179 0.0035 1.0000
13.250 1.3989 0.03243 0.02855 -0.0157 0.0034 1.0000
13.500 1.3992 0.03423 0.03048 -0.0137 0.0034 1.0000
13.750 1.4015 0.03596 0.03233 -0.0122 0.0033 1.0000
14.000 1.4010 0.03808 0.03458 -0.0109 0.0032 1.0000
14.250 1.3986 0.04057 0.03720 -0.0101 0.0031 1.0000
14.500 1.3900 0.04399 0.04078 -0.0098 0.0030 1.0000
14.750 1.3889 0.04684 0.04373 -0.0101 0.0030 1.0000
15.000 1.3792 0.05111 0.04815 -0.0112 0.0029 1.0000
15.250 1.3627 0.05687 0.05410 -0.0137 0.0029 1.0000
15.500 1.3486 0.06294 0.06032 -0.0169 0.0029 1.0000
15.750 1.3317 0.07009 0.06762 -0.0211 0.0028 1.0000
16.000 1.3110 0.07858 0.07627 -0.0264 0.0028 1.0000
16.250 1.2634 0.09341 0.09135 -0.0356 0.0030 1.0000
16.500 1.2179 0.10864 0.10677 -0.0447 0.0030 1.0000
16.750 1.1585 0.12810 0.12642 -0.0562 0.0033 1.0000
17.000 1.0945 0.15048 0.14895 -0.0691 0.0034 1.0000
|
Polar data table (+)
Polar graphs
<< Back to S2062 8% (s2062-il)