S4095 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4095-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: S4095 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4095-il) Reynolds number: 500,000 Max Cl/Cd: 65.22 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4095-il-500000-n5.txt Download as CSV file: xf-s4095-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.6614 0.10368 0.10153 0.0249 1.0007 0.0102
-8.750 -0.6696 0.09813 0.09601 0.0225 1.0007 0.0101
-8.500 -0.6776 0.09205 0.08994 0.0184 1.0007 0.0101
-8.250 -0.6790 0.08396 0.08186 0.0106 1.0007 0.0101
-8.000 -0.6744 0.07309 0.07090 -0.0004 1.0007 0.0101
-7.750 -0.6648 0.03247 0.02842 -0.0276 1.0007 0.0102
-7.500 -0.6358 0.02914 0.02459 -0.0294 1.0007 0.0105
-7.250 -0.6064 0.02730 0.02243 -0.0305 1.0007 0.0107
-7.000 -0.5765 0.02499 0.01974 -0.0318 1.0007 0.0109
-6.750 -0.5466 0.02274 0.01717 -0.0330 1.0007 0.0111
-6.500 -0.5168 0.02119 0.01543 -0.0339 1.0007 0.0114
-6.250 -0.4870 0.02006 0.01416 -0.0346 1.0007 0.0116
-6.000 -0.4572 0.01912 0.01311 -0.0352 1.0007 0.0119
-5.750 -0.4274 0.01829 0.01219 -0.0358 1.0007 0.0122
-5.500 -0.3975 0.01755 0.01135 -0.0364 1.0007 0.0125
-5.250 -0.3675 0.01687 0.01059 -0.0370 1.0007 0.0129
-5.000 -0.3375 0.01625 0.00991 -0.0375 1.0007 0.0132
-4.750 -0.3074 0.01569 0.00929 -0.0381 1.0007 0.0136
-4.500 -0.2772 0.01519 0.00873 -0.0387 1.0007 0.0140
-4.250 -0.2471 0.01475 0.00826 -0.0392 1.0007 0.0143
-4.000 -0.2156 0.01481 0.00825 -0.0399 0.9420 0.0148
-3.750 -0.1906 0.01464 0.00793 -0.0389 0.8879 0.0156
-3.500 -0.1640 0.01448 0.00759 -0.0384 0.8478 0.0163
-3.250 -0.1358 0.01435 0.00729 -0.0383 0.8141 0.0171
-3.000 -0.1070 0.01423 0.00702 -0.0384 0.7847 0.0181
-2.750 -0.0777 0.01413 0.00677 -0.0386 0.7582 0.0193
-2.500 -0.0482 0.01402 0.00655 -0.0389 0.7342 0.0219
-2.250 -0.0185 0.01385 0.00637 -0.0393 0.7116 0.0348
-2.000 0.0112 0.01368 0.00623 -0.0398 0.6912 0.0654
-1.750 0.0410 0.01353 0.00612 -0.0403 0.6718 0.0963
-1.500 0.0709 0.01340 0.00603 -0.0409 0.6534 0.1312
-1.250 0.1007 0.01327 0.00596 -0.0414 0.6362 0.1726
-1.000 0.1306 0.01311 0.00592 -0.0420 0.6200 0.2305
-0.750 0.1606 0.01289 0.00590 -0.0427 0.6040 0.3147
-0.500 0.1907 0.01262 0.00592 -0.0435 0.5886 0.4216
-0.250 0.2206 0.01220 0.00599 -0.0443 0.5737 0.5912
0.000 0.2478 0.01169 0.00613 -0.0441 0.5592 0.7953
0.250 0.2688 0.01076 0.00550 -0.0419 0.5452 0.9993
0.500 0.2987 0.01086 0.00548 -0.0424 0.5298 0.9993
0.750 0.3286 0.01096 0.00548 -0.0428 0.5144 0.9993
1.000 0.3584 0.01107 0.00548 -0.0433 0.4986 0.9993
1.250 0.3882 0.01118 0.00550 -0.0437 0.4819 0.9993
1.500 0.4180 0.01130 0.00552 -0.0442 0.4648 0.9993
1.750 0.4478 0.01143 0.00556 -0.0447 0.4476 0.9993
2.000 0.4775 0.01158 0.00561 -0.0451 0.4301 0.9993
2.250 0.5071 0.01173 0.00566 -0.0456 0.4128 0.9993
2.500 0.5367 0.01189 0.00573 -0.0461 0.3950 0.9993
2.750 0.5663 0.01205 0.00582 -0.0465 0.3778 0.9993
3.000 0.5959 0.01223 0.00591 -0.0470 0.3608 0.9993
3.250 0.6254 0.01241 0.00602 -0.0475 0.3440 0.9993
3.500 0.6549 0.01260 0.00615 -0.0479 0.3280 0.9993
3.750 0.6843 0.01281 0.00628 -0.0484 0.3114 0.9993
4.000 0.7136 0.01301 0.00642 -0.0489 0.2960 0.9993
4.250 0.7430 0.01323 0.00658 -0.0493 0.2801 0.9993
4.500 0.7722 0.01345 0.00674 -0.0498 0.2649 0.9993
4.750 0.8014 0.01369 0.00692 -0.0503 0.2493 0.9993
5.000 0.8306 0.01393 0.00711 -0.0507 0.2348 0.9993
5.250 0.8596 0.01419 0.00733 -0.0512 0.2199 0.9993
5.500 0.8886 0.01446 0.00755 -0.0516 0.2067 0.9993
5.750 0.9176 0.01473 0.00779 -0.0521 0.1937 0.9993
6.000 0.9464 0.01503 0.00804 -0.0525 0.1801 0.9993
6.500 1.0038 0.01565 0.00861 -0.0534 0.1551 0.9993
6.750 1.0324 0.01599 0.00892 -0.0538 0.1423 0.9993
7.000 1.0608 0.01636 0.00924 -0.0542 0.1293 0.9993
7.250 1.0891 0.01672 0.00960 -0.0546 0.1181 0.9993
7.500 1.1173 0.01713 0.00997 -0.0551 0.1062 0.9993
7.750 1.1452 0.01758 0.01038 -0.0555 0.0931 0.9993
8.000 1.1730 0.01806 0.01081 -0.0559 0.0813 0.9993
8.250 1.2007 0.01851 0.01126 -0.0562 0.0727 0.9993
8.500 1.2282 0.01902 0.01175 -0.0566 0.0637 0.9993
8.750 1.2555 0.01953 0.01224 -0.0569 0.0551 0.9993
9.000 1.2826 0.02006 0.01277 -0.0572 0.0474 0.9993
9.250 1.3093 0.02065 0.01336 -0.0575 0.0401 0.9993
9.500 1.3356 0.02132 0.01401 -0.0578 0.0320 0.9993
9.750 1.3615 0.02203 0.01470 -0.0580 0.0252 0.9993
10.000 1.3870 0.02279 0.01546 -0.0581 0.0186 0.9993
10.250 1.4114 0.02377 0.01642 -0.0582 0.0107 0.9993
10.500 1.4356 0.02472 0.01742 -0.0582 0.0078 0.9993
10.750 1.4599 0.02555 0.01833 -0.0582 0.0068 0.9993
11.000 1.4833 0.02648 0.01935 -0.0581 0.0062 0.9993
11.250 1.5057 0.02752 0.02051 -0.0579 0.0056 0.9993
11.500 1.5281 0.02845 0.02154 -0.0576 0.0053 0.9993
11.750 1.5495 0.02944 0.02266 -0.0573 0.0051 0.9993
12.000 1.5697 0.03053 0.02389 -0.0568 0.0048 0.9993
12.250 1.5883 0.03172 0.02521 -0.0561 0.0046 0.9993
12.500 1.6051 0.03304 0.02666 -0.0553 0.0044 0.9993
12.750 1.6195 0.03451 0.02826 -0.0542 0.0043 0.9993
13.000 1.6306 0.03618 0.03007 -0.0528 0.0041 0.9993
13.250 1.6371 0.03812 0.03216 -0.0509 0.0040 0.9993
13.500 1.6365 0.04043 0.03463 -0.0484 0.0039 0.9993
13.750 1.6219 0.04356 0.03792 -0.0446 0.0039 0.9993
14.000 1.6099 0.04764 0.04218 -0.0435 0.0039 0.9993
14.250 1.5981 0.05261 0.04734 -0.0442 0.0038 0.9993
14.500 1.5851 0.05838 0.05329 -0.0460 0.0038 0.9993
14.750 1.5700 0.06484 0.05994 -0.0485 0.0038 0.9993
15.000 1.5516 0.07198 0.06726 -0.0513 0.0037 0.9993
15.250 1.5319 0.07946 0.07491 -0.0543 0.0037 0.9993
15.500 1.5096 0.08749 0.08311 -0.0576 0.0037 0.9993
15.750 1.4873 0.09557 0.09135 -0.0609 0.0038 0.9993
16.000 1.4639 0.10402 0.09996 -0.0644 0.0038 0.9993
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