S9027 (8%) (s9027-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: S9027 (8%) (s9027-il) Reynolds number: 50,000 Max Cl/Cd: 22.63 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s9027-il-50000.txt Download as CSV file: xf-s9027-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: S9027 (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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.6100 0.09640 0.08923 0.0299 1.0000 0.3511
-8.000 -0.6238 0.09414 0.08707 0.0293 1.0000 0.3629
-7.750 -0.7430 0.06178 0.05440 -0.0110 1.0000 0.1476
-7.500 -0.7378 0.05628 0.04866 -0.0117 1.0000 0.1457
-7.250 -0.7335 0.05089 0.04281 -0.0123 1.0000 0.1462
-7.000 -0.7279 0.04583 0.03696 -0.0124 1.0000 0.1488
-6.750 -0.7078 0.04310 0.03433 -0.0115 1.0000 0.1561
-6.500 -0.6926 0.03899 0.02954 -0.0109 1.0000 0.1603
-6.250 -0.6729 0.03636 0.02672 -0.0101 1.0000 0.1709
-6.000 -0.6526 0.03385 0.02392 -0.0091 1.0000 0.1836
-5.750 -0.6308 0.03142 0.02120 -0.0082 1.0000 0.1971
-5.500 -0.6087 0.02957 0.01914 -0.0072 1.0000 0.2167
-5.250 -0.5853 0.02757 0.01696 -0.0062 1.0000 0.2359
-5.000 -0.5624 0.02609 0.01537 -0.0051 1.0000 0.2627
-4.750 -0.5386 0.02452 0.01382 -0.0040 1.0000 0.2908
-4.500 -0.5159 0.02325 0.01280 -0.0027 1.0000 0.3264
-4.250 -0.4931 0.02201 0.01171 -0.0013 1.0000 0.3686
-4.000 -0.4711 0.02091 0.01078 0.0003 1.0000 0.4205
-3.750 -0.4498 0.01989 0.01006 0.0023 1.0000 0.4793
-3.500 -0.4298 0.01898 0.00952 0.0049 1.0000 0.5455
-3.250 -0.4113 0.01819 0.00911 0.0082 1.0000 0.6197
-3.000 -0.3943 0.01760 0.00888 0.0125 1.0000 0.6984
-2.750 -0.3765 0.01725 0.00876 0.0172 1.0000 0.7814
-2.500 -0.3343 0.01740 0.00892 0.0185 1.0000 0.8711
-2.250 -0.1922 0.01786 0.00865 0.0000 1.0000 0.9627
-2.000 -0.1124 0.01684 0.00727 -0.0122 1.0000 1.0000
-1.750 -0.1026 0.01622 0.00658 -0.0112 1.0000 1.0000
-1.500 -0.0908 0.01578 0.00605 -0.0098 1.0000 1.0000
-1.250 -0.0775 0.01545 0.00566 -0.0083 1.0000 1.0000
-1.000 -0.0630 0.01522 0.00537 -0.0068 1.0000 1.0000
-0.750 -0.0478 0.01506 0.00516 -0.0051 1.0000 1.0000
-0.500 -0.0320 0.01495 0.00502 -0.0034 1.0000 1.0000
-0.250 -0.0160 0.01489 0.00493 -0.0017 1.0000 1.0000
0.000 0.0000 0.01487 0.00490 0.0000 1.0000 1.0000
0.250 0.0160 0.01489 0.00493 0.0017 1.0000 1.0000
0.500 0.0320 0.01495 0.00502 0.0034 1.0000 1.0000
0.750 0.0478 0.01506 0.00516 0.0051 1.0000 1.0000
1.000 0.0630 0.01522 0.00537 0.0068 1.0000 1.0000
1.250 0.0775 0.01545 0.00566 0.0083 1.0000 1.0000
1.500 0.0909 0.01577 0.00605 0.0098 1.0000 1.0000
1.750 0.1027 0.01622 0.00658 0.0112 1.0000 1.0000
2.000 0.1126 0.01684 0.00726 0.0122 1.0000 1.0000
2.250 0.1923 0.01785 0.00864 0.0000 0.9628 1.0000
2.500 0.3341 0.01740 0.00891 -0.0185 0.8712 1.0000
2.750 0.3764 0.01725 0.00878 -0.0172 0.7816 1.0000
3.000 0.3942 0.01760 0.00888 -0.0124 0.6986 1.0000
3.250 0.4111 0.01819 0.00910 -0.0082 0.6200 1.0000
3.500 0.4296 0.01898 0.00952 -0.0049 0.5457 1.0000
3.750 0.4496 0.01988 0.01006 -0.0023 0.4794 1.0000
4.000 0.4710 0.02091 0.01079 -0.0003 0.4207 1.0000
4.250 0.4930 0.02201 0.01171 0.0013 0.3688 1.0000
4.500 0.5157 0.02325 0.01279 0.0027 0.3265 1.0000
4.750 0.5384 0.02452 0.01382 0.0041 0.2909 1.0000
5.000 0.5623 0.02608 0.01537 0.0051 0.2628 1.0000
5.250 0.5852 0.02757 0.01696 0.0062 0.2359 1.0000
5.500 0.6087 0.02956 0.01913 0.0072 0.2167 1.0000
5.750 0.6308 0.03142 0.02120 0.0082 0.1972 1.0000
6.000 0.6526 0.03386 0.02392 0.0091 0.1835 1.0000
6.250 0.6729 0.03636 0.02671 0.0100 0.1707 1.0000
6.500 0.6927 0.03901 0.02955 0.0109 0.1603 1.0000
6.750 0.7079 0.04311 0.03434 0.0115 0.1560 1.0000
7.000 0.7280 0.04585 0.03700 0.0123 0.1487 1.0000
7.250 0.7338 0.05092 0.04284 0.0122 0.1462 1.0000
7.500 0.7382 0.05633 0.04871 0.0116 0.1457 1.0000
7.750 0.7436 0.06180 0.05442 0.0109 0.1476 1.0000
8.000 0.6612 0.08493 0.07798 -0.0135 0.2384 1.0000
8.250 0.7126 0.08019 0.07334 0.0001 0.1782 1.0000
8.500 0.6069 0.09975 0.09252 -0.0307 0.3405 1.0000
8.750 0.6115 0.10350 0.09625 -0.0308 0.3296 1.0000
|
Polar data table (+)
Polar graphs
<< Back to S9027 (8%) (s9027-il)