S4095 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4095-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: S4095 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4095-il) Reynolds number: 100,000 Max Cl/Cd: 41.09 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4095-il-100000.txt Download as CSV file: xf-s4095-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: S4095 (designed for the E-flite UMX ASK-21 scale
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5982 0.11993 0.11522 0.0243 1.0007 0.0884
-8.500 -0.6084 0.11587 0.11123 0.0197 1.0007 0.0910
-8.250 -0.6134 0.11133 0.10675 0.0171 1.0007 0.0921
-8.000 -0.5986 0.10760 0.10301 0.0190 1.0007 0.0949
-7.750 -0.6011 0.10327 0.09871 0.0145 1.0007 0.0984
-7.500 -0.5999 0.09755 0.09300 0.0073 1.0007 0.1007
-7.250 -0.5873 0.09405 0.08952 0.0088 1.0007 0.1039
-7.000 -0.5791 0.08722 0.08258 -0.0033 1.0007 0.1096
-6.750 -0.5652 0.08403 0.07945 -0.0004 1.0007 0.1126
-6.500 -0.5480 0.07781 0.07307 -0.0094 1.0007 0.1202
-6.250 -0.5311 0.07445 0.06973 -0.0088 1.0007 0.1249
-6.000 -0.4999 0.06893 0.06365 -0.0218 1.0007 0.1420
-5.750 -0.4858 0.06478 0.05978 -0.0182 1.0007 0.1448
-5.500 -0.4615 0.06092 0.05582 -0.0210 1.0007 0.1584
-5.250 -0.4352 0.05716 0.05193 -0.0238 1.0007 0.1731
-5.000 -0.3608 0.03844 0.03109 -0.0387 1.0007 0.0782
-4.750 -0.3232 0.03323 0.02502 -0.0406 1.0007 0.0692
-4.500 -0.2893 0.02993 0.02119 -0.0416 1.0007 0.0673
-4.250 -0.2565 0.02746 0.01827 -0.0423 1.0007 0.0680
-4.000 -0.2248 0.02559 0.01609 -0.0429 1.0007 0.0719
-3.750 -0.1937 0.02392 0.01425 -0.0432 1.0007 0.0757
-3.500 -0.1633 0.02233 0.01265 -0.0435 1.0007 0.0808
-3.250 -0.1328 0.02105 0.01133 -0.0437 1.0007 0.0916
-3.000 -0.1030 0.01970 0.01027 -0.0442 1.0007 0.1148
-2.750 -0.0729 0.01832 0.00930 -0.0448 1.0007 0.1824
-2.500 -0.0441 0.01713 0.00881 -0.0455 1.0007 0.3007
-2.250 -0.0206 0.01529 0.00855 -0.0446 1.0007 0.6178
-2.000 -0.0017 0.01343 0.00745 -0.0409 1.0007 0.9993
-1.750 0.0285 0.01353 0.00724 -0.0417 1.0007 0.9993
-1.500 0.0584 0.01370 0.00719 -0.0425 1.0007 0.9993
-1.250 0.0876 0.01395 0.00729 -0.0434 1.0007 0.9993
-1.000 0.1156 0.01440 0.00760 -0.0442 1.0007 0.9993
-0.750 0.1404 0.01524 0.00834 -0.0449 1.0007 0.9993
-0.500 0.1822 0.01557 0.00853 -0.0488 0.9925 0.9993
-0.250 0.2351 0.01530 0.00810 -0.0544 0.9699 0.9993
0.000 0.2810 0.01522 0.00788 -0.0581 0.9414 0.9993
0.250 0.3144 0.01541 0.00792 -0.0587 0.9089 0.9993
0.500 0.3397 0.01571 0.00809 -0.0574 0.8769 0.9993
0.750 0.3637 0.01603 0.00827 -0.0559 0.8484 0.9993
1.000 0.3881 0.01634 0.00843 -0.0546 0.8224 0.9993
1.250 0.4133 0.01663 0.00860 -0.0535 0.7974 0.9993
1.500 0.4389 0.01692 0.00877 -0.0526 0.7739 0.9993
1.750 0.4651 0.01721 0.00893 -0.0518 0.7512 0.9993
2.000 0.4917 0.01750 0.00912 -0.0512 0.7291 0.9993
2.250 0.5187 0.01779 0.00930 -0.0507 0.7073 0.9993
2.500 0.5459 0.01809 0.00949 -0.0502 0.6857 0.9993
2.750 0.5733 0.01838 0.00968 -0.0499 0.6643 0.9993
3.000 0.6009 0.01868 0.00989 -0.0496 0.6429 0.9993
3.250 0.6286 0.01898 0.01013 -0.0493 0.6215 0.9993
3.500 0.6564 0.01928 0.01036 -0.0491 0.6000 0.9993
3.750 0.6842 0.01959 0.01060 -0.0490 0.5785 0.9993
4.000 0.7121 0.01990 0.01084 -0.0489 0.5570 0.9993
4.250 0.7401 0.02022 0.01113 -0.0487 0.5353 0.9993
4.500 0.7680 0.02054 0.01139 -0.0487 0.5135 0.9993
4.750 0.7959 0.02087 0.01166 -0.0486 0.4918 0.9993
5.000 0.8238 0.02123 0.01195 -0.0486 0.4701 0.9993
5.250 0.8516 0.02163 0.01230 -0.0485 0.4486 0.9993
5.500 0.8796 0.02205 0.01272 -0.0486 0.4260 0.9993
5.750 0.9075 0.02250 0.01317 -0.0487 0.4034 0.9993
6.000 0.9353 0.02300 0.01367 -0.0488 0.3812 0.9993
6.250 0.9628 0.02354 0.01418 -0.0489 0.3596 0.9993
6.500 0.9902 0.02412 0.01472 -0.0490 0.3386 0.9993
6.750 1.0175 0.02476 0.01533 -0.0490 0.3182 0.9993
7.000 1.0445 0.02546 0.01599 -0.0491 0.2985 0.9993
7.250 1.0714 0.02622 0.01674 -0.0492 0.2791 0.9993
7.500 1.0982 0.02699 0.01759 -0.0494 0.2597 0.9993
7.750 1.1247 0.02783 0.01848 -0.0494 0.2412 0.9993
8.000 1.1509 0.02872 0.01941 -0.0495 0.2237 0.9993
8.250 1.1767 0.02967 0.02041 -0.0495 0.2070 0.9993
8.500 1.2021 0.03069 0.02147 -0.0495 0.1915 0.9993
8.750 1.2272 0.03180 0.02260 -0.0494 0.1770 0.9993
9.000 1.2519 0.03299 0.02385 -0.0494 0.1636 0.9993
9.250 1.2762 0.03428 0.02520 -0.0492 0.1512 0.9993
9.500 1.3001 0.03568 0.02667 -0.0490 0.1398 0.9993
9.750 1.3234 0.03717 0.02824 -0.0488 0.1292 0.9993
10.000 1.3461 0.03873 0.02989 -0.0485 0.1193 0.9993
10.250 1.3675 0.04026 0.03148 -0.0481 0.1091 0.9993
10.500 1.3843 0.04137 0.03290 -0.0474 0.0972 0.9993
10.750 1.4016 0.04224 0.03366 -0.0469 0.0864 0.9993
11.000 1.4141 0.04400 0.03579 -0.0457 0.0760 0.9993
11.250 1.4254 0.04592 0.03779 -0.0444 0.0664 0.9993
11.500 1.4334 0.04806 0.04003 -0.0428 0.0580 0.9993
11.750 1.4402 0.05083 0.04292 -0.0411 0.0519 0.9993
12.000 1.4468 0.05378 0.04601 -0.0393 0.0477 0.9993
12.250 1.4452 0.05728 0.04991 -0.0368 0.0450 0.9993
12.500 1.4449 0.06067 0.05350 -0.0347 0.0431 0.9993
12.750 1.4291 0.06456 0.05777 -0.0315 0.0421 0.9993
13.000 1.4178 0.06826 0.06168 -0.0295 0.0410 0.9993
13.250 1.4152 0.07162 0.06509 -0.0286 0.0396 0.9993
13.500 1.3931 0.07713 0.07096 -0.0286 0.0393 0.9993
13.750 1.3709 0.08333 0.07749 -0.0300 0.0392 0.9993
14.000 1.3488 0.09011 0.08457 -0.0325 0.0392 0.9993
14.250 1.3260 0.09753 0.09225 -0.0360 0.0392 0.9993
14.500 1.3036 0.10540 0.10035 -0.0402 0.0394 0.9993
14.750 1.2821 0.11358 0.10872 -0.0449 0.0397 0.9993
|
Polar data table (+)
Polar graphs
<< Back to S4095 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4095-il)