S4095 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4095-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: S4095 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4095-il) Reynolds number: 50,000 Max Cl/Cd: 32.85 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4095-il-50000-n5.txt Download as CSV file: xf-s4095-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.6105 0.10417 0.09746 0.0032 1.0007 0.0554
-8.000 -0.6033 0.09940 0.09269 0.0013 1.0007 0.0551
-7.750 -0.5957 0.09432 0.08760 -0.0015 1.0007 0.0547
-7.500 -0.5867 0.08901 0.08225 -0.0049 1.0007 0.0544
-7.250 -0.5756 0.08357 0.07675 -0.0085 1.0007 0.0538
-7.000 -0.5621 0.07795 0.07103 -0.0124 1.0007 0.0530
-6.750 -0.5455 0.07207 0.06496 -0.0166 1.0007 0.0520
-6.500 -0.5251 0.06587 0.05851 -0.0212 1.0007 0.0509
-6.250 -0.5007 0.05957 0.05185 -0.0260 1.0007 0.0500
-6.000 -0.4726 0.05353 0.04532 -0.0303 1.0007 0.0494
-5.750 -0.4422 0.04824 0.03947 -0.0338 1.0007 0.0492
-5.500 -0.4103 0.04370 0.03434 -0.0366 1.0007 0.0495
-5.250 -0.3781 0.04003 0.03007 -0.0386 1.0007 0.0514
-5.000 -0.3452 0.03686 0.02621 -0.0401 1.0007 0.0543
-4.750 -0.3140 0.03421 0.02314 -0.0412 1.0007 0.0568
-4.500 -0.2838 0.03210 0.02082 -0.0418 1.0007 0.0591
-4.250 -0.2535 0.03019 0.01866 -0.0422 1.0007 0.0623
-4.000 -0.2234 0.02846 0.01662 -0.0423 1.0007 0.0670
-3.750 -0.1946 0.02713 0.01527 -0.0426 1.0007 0.0758
-3.500 -0.1654 0.02584 0.01392 -0.0428 1.0007 0.0890
-3.250 -0.1356 0.02466 0.01276 -0.0432 1.0007 0.1152
-3.000 -0.1059 0.02359 0.01191 -0.0439 1.0007 0.1683
-2.750 -0.0765 0.02244 0.01110 -0.0446 1.0007 0.2389
-2.500 -0.0482 0.02129 0.01055 -0.0451 1.0007 0.3532
-2.250 -0.0253 0.01991 0.01021 -0.0441 1.0007 0.5624
-2.000 -0.0076 0.01774 0.00907 -0.0401 1.0007 0.9993
-1.750 0.0216 0.01783 0.00878 -0.0407 1.0007 0.9993
-1.500 0.0500 0.01799 0.00864 -0.0413 1.0007 0.9993
-1.250 0.0777 0.01821 0.00864 -0.0418 1.0007 0.9993
-1.000 0.1043 0.01855 0.00878 -0.0423 1.0007 0.9993
-0.750 0.1292 0.01905 0.00915 -0.0426 1.0007 0.9993
-0.500 0.1732 0.01926 0.00911 -0.0465 0.9790 0.9993
-0.250 0.2182 0.01935 0.00898 -0.0503 0.9513 0.9993
0.000 0.2609 0.01948 0.00892 -0.0535 0.9228 0.9993
0.250 0.2987 0.01968 0.00894 -0.0554 0.8930 0.9993
0.500 0.3312 0.01994 0.00903 -0.0560 0.8634 0.9993
0.750 0.3601 0.02026 0.00918 -0.0557 0.8353 0.9993
1.000 0.3872 0.02059 0.00936 -0.0550 0.8093 0.9993
1.250 0.4138 0.02093 0.00956 -0.0544 0.7838 0.9993
1.500 0.4403 0.02127 0.00976 -0.0537 0.7599 0.9993
1.750 0.4667 0.02161 0.00998 -0.0530 0.7374 0.9993
2.000 0.4936 0.02194 0.01022 -0.0525 0.7147 0.9993
2.250 0.5203 0.02229 0.01046 -0.0519 0.6933 0.9993
2.500 0.5475 0.02263 0.01073 -0.0515 0.6717 0.9993
2.750 0.5747 0.02298 0.01103 -0.0511 0.6505 0.9993
3.000 0.6019 0.02333 0.01131 -0.0508 0.6299 0.9993
3.250 0.6294 0.02369 0.01164 -0.0505 0.6083 0.9993
3.500 0.6566 0.02405 0.01198 -0.0502 0.5882 0.9993
3.750 0.6843 0.02443 0.01236 -0.0501 0.5666 0.9993
4.000 0.7117 0.02481 0.01272 -0.0499 0.5458 0.9993
4.250 0.7392 0.02521 0.01312 -0.0497 0.5248 0.9993
4.500 0.7666 0.02562 0.01358 -0.0496 0.5035 0.9993
4.750 0.7938 0.02604 0.01399 -0.0494 0.4829 0.9993
5.000 0.8212 0.02650 0.01450 -0.0494 0.4611 0.9993
5.250 0.8483 0.02696 0.01494 -0.0492 0.4409 0.9993
5.500 0.8757 0.02749 0.01558 -0.0493 0.4190 0.9993
5.750 0.9026 0.02803 0.01613 -0.0491 0.3987 0.9993
6.000 0.9295 0.02863 0.01678 -0.0491 0.3779 0.9993
6.250 0.9561 0.02928 0.01747 -0.0491 0.3575 0.9993
6.500 0.9824 0.02995 0.01819 -0.0490 0.3386 0.9993
6.750 1.0088 0.03071 0.01907 -0.0490 0.3181 0.9993
7.000 1.0346 0.03150 0.01994 -0.0490 0.2993 0.9993
7.250 1.0600 0.03232 0.02079 -0.0489 0.2813 0.9993
7.500 1.0854 0.03326 0.02189 -0.0488 0.2633 0.9993
7.750 1.1102 0.03425 0.02301 -0.0488 0.2456 0.9993
8.000 1.1345 0.03530 0.02418 -0.0486 0.2293 0.9993
8.250 1.1582 0.03641 0.02541 -0.0485 0.2136 0.9993
8.500 1.1814 0.03763 0.02679 -0.0483 0.1990 0.9993
8.750 1.2039 0.03892 0.02823 -0.0480 0.1850 0.9993
9.000 1.2256 0.04033 0.02981 -0.0477 0.1719 0.9993
9.250 1.2464 0.04185 0.03152 -0.0473 0.1597 0.9993
9.500 1.2662 0.04345 0.03329 -0.0468 0.1485 0.9993
9.750 1.2853 0.04507 0.03503 -0.0462 0.1389 0.9993
10.000 1.3023 0.04692 0.03715 -0.0455 0.1287 0.9993
10.250 1.3179 0.04914 0.03969 -0.0447 0.1200 0.9993
10.500 1.3330 0.05099 0.04158 -0.0438 0.1126 0.9993
10.750 1.3426 0.05360 0.04463 -0.0426 0.1046 0.9993
11.000 1.3529 0.05598 0.04715 -0.0414 0.0986 0.9993
11.250 1.3553 0.05912 0.05072 -0.0398 0.0925 0.9993
11.500 1.3606 0.06132 0.05291 -0.0383 0.0870 0.9993
11.750 1.3494 0.06553 0.05765 -0.0362 0.0830 0.9993
12.000 1.3369 0.06923 0.06164 -0.0341 0.0798 0.9993
12.250 1.3361 0.07139 0.06365 -0.0327 0.0754 0.9993
12.500 1.3121 0.07731 0.06998 -0.0328 0.0741 0.9993
12.750 1.2875 0.08426 0.07727 -0.0347 0.0732 0.9993
13.000 1.2610 0.09238 0.08567 -0.0381 0.0728 0.9993
13.250 1.2315 0.10188 0.09536 -0.0429 0.0732 0.9993
13.500 1.1993 0.11291 0.10656 -0.0491 0.0742 0.9993
13.750 1.1653 0.12544 0.11918 -0.0564 0.0751 0.9993
|
Polar data table (+)
Polar graphs
<< Back to S4095 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4095-il)