S4096 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4096-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: S4096 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4096-il) Reynolds number: 100,000 Max Cl/Cd: 39.59 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4096-il-100000.txt Download as CSV file: xf-s4096-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: S4096 (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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.6321 0.11843 0.11366 0.0118 1.0011 0.1134
-8.750 -0.6669 0.11226 0.10758 0.0027 1.0011 0.1168
-8.500 -0.6709 0.10555 0.10089 -0.0013 1.0011 0.1188
-8.250 -0.6509 0.10308 0.09843 0.0040 1.0011 0.1220
-8.000 -0.6470 0.09840 0.09374 0.0013 1.0011 0.1271
-7.750 -0.5469 0.08636 0.08197 -0.0109 1.0011 0.1441
-7.500 -0.6359 0.08726 0.08251 -0.0066 1.0011 0.1383
-7.250 -0.5464 0.07637 0.07195 -0.0132 1.0011 0.1552
-7.000 -0.5484 0.07005 0.06553 -0.0171 1.0011 0.1649
-6.750 -0.5921 0.07247 0.06744 -0.0165 1.0011 0.1677
-6.500 -0.5371 0.04710 0.03967 -0.0352 1.0011 0.0784
-6.250 -0.5050 0.04231 0.03432 -0.0365 1.0011 0.0719
-6.000 -0.4723 0.03778 0.02913 -0.0378 1.0011 0.0680
-5.750 -0.4395 0.03441 0.02509 -0.0386 1.0011 0.0664
-5.500 -0.4084 0.03203 0.02240 -0.0391 1.0011 0.0670
-5.250 -0.3782 0.03034 0.02055 -0.0397 1.0011 0.0705
-5.000 -0.3474 0.02870 0.01868 -0.0400 1.0011 0.0736
-4.750 -0.3167 0.02724 0.01701 -0.0402 1.0011 0.0761
-4.500 -0.2877 0.02547 0.01541 -0.0405 1.0011 0.0814
-4.250 -0.2580 0.02430 0.01424 -0.0409 1.0011 0.0911
-4.000 -0.2282 0.02306 0.01319 -0.0414 1.0011 0.1144
-3.750 -0.1991 0.02064 0.01215 -0.0425 1.0011 0.3276
-3.500 -0.1725 0.01980 0.01202 -0.0425 1.0011 0.4851
-3.250 -0.1498 0.01905 0.01206 -0.0409 1.0011 0.6541
-2.750 -0.1007 0.01729 0.01093 -0.0369 1.0011 0.9989
-2.500 -0.0705 0.01735 0.01070 -0.0380 1.0011 0.9989
-2.250 -0.0410 0.01749 0.01062 -0.0390 1.0011 0.9989
-2.000 -0.0120 0.01771 0.01065 -0.0398 1.0011 0.9989
-1.750 0.0163 0.01803 0.01081 -0.0405 1.0011 0.9989
-1.500 0.0436 0.01849 0.01116 -0.0411 1.0011 0.9989
-1.250 0.0694 0.01917 0.01174 -0.0415 1.0011 0.9989
-1.000 0.0933 0.02013 0.01261 -0.0418 1.0011 0.9989
-0.750 0.1147 0.02147 0.01388 -0.0420 1.0011 0.9989
-0.500 0.1454 0.02234 0.01466 -0.0443 0.9976 0.9989
-0.250 0.1987 0.02166 0.01387 -0.0504 0.9869 0.9989
0.000 0.2518 0.02090 0.01302 -0.0563 0.9750 0.9989
0.250 0.3015 0.02028 0.01232 -0.0614 0.9599 0.9989
0.500 0.3455 0.01986 0.01184 -0.0649 0.9405 0.9989
0.750 0.3822 0.01970 0.01162 -0.0666 0.9176 0.9989
1.000 0.4122 0.01976 0.01161 -0.0667 0.8939 0.9989
1.250 0.4387 0.01993 0.01171 -0.0659 0.8707 0.9989
1.500 0.4645 0.02015 0.01186 -0.0649 0.8487 0.9989
1.750 0.4902 0.02038 0.01202 -0.0641 0.8271 0.9989
2.000 0.5158 0.02062 0.01217 -0.0631 0.8074 0.9989
2.250 0.5423 0.02087 0.01236 -0.0626 0.7868 0.9989
2.500 0.5691 0.02111 0.01255 -0.0621 0.7667 0.9989
2.750 0.5958 0.02136 0.01271 -0.0615 0.7476 0.9989
3.000 0.6229 0.02161 0.01290 -0.0611 0.7282 0.9989
3.250 0.6505 0.02186 0.01313 -0.0609 0.7076 0.9989
3.500 0.6779 0.02210 0.01331 -0.0606 0.6878 0.9989
3.750 0.7053 0.02236 0.01349 -0.0603 0.6686 0.9989
4.000 0.7333 0.02262 0.01376 -0.0603 0.6468 0.9989
4.250 0.7610 0.02287 0.01396 -0.0601 0.6262 0.9989
4.500 0.7889 0.02314 0.01418 -0.0600 0.6050 0.9989
4.750 0.8168 0.02340 0.01444 -0.0600 0.5826 0.9989
5.000 0.8445 0.02368 0.01465 -0.0599 0.5610 0.9989
5.250 0.8725 0.02396 0.01493 -0.0599 0.5373 0.9989
5.500 0.9002 0.02426 0.01520 -0.0599 0.5143 0.9989
5.750 0.9280 0.02457 0.01548 -0.0599 0.4901 0.9989
6.000 0.9557 0.02492 0.01582 -0.0600 0.4653 0.9989
6.250 0.9830 0.02532 0.01613 -0.0600 0.4414 0.9989
6.500 1.0104 0.02578 0.01659 -0.0601 0.4157 0.9989
6.750 1.0376 0.02631 0.01709 -0.0602 0.3904 0.9989
7.000 1.0644 0.02692 0.01760 -0.0603 0.3666 0.9989
7.250 1.0911 0.02756 0.01825 -0.0604 0.3415 0.9989
7.500 1.1176 0.02828 0.01896 -0.0605 0.3177 0.9989
7.750 1.1436 0.02905 0.01964 -0.0606 0.2951 0.9989
8.000 1.1695 0.02989 0.02052 -0.0607 0.2722 0.9989
8.250 1.1948 0.03078 0.02135 -0.0607 0.2513 0.9989
8.500 1.2199 0.03177 0.02238 -0.0607 0.2306 0.9989
8.750 1.2445 0.03278 0.02339 -0.0606 0.2111 0.9989
9.000 1.2686 0.03391 0.02447 -0.0605 0.1938 0.9989
9.250 1.2923 0.03519 0.02573 -0.0604 0.1775 0.9989
9.500 1.3155 0.03651 0.02713 -0.0601 0.1623 0.9989
9.750 1.3383 0.03795 0.02861 -0.0598 0.1487 0.9989
10.000 1.3610 0.03952 0.03014 -0.0595 0.1367 0.9989
10.250 1.3821 0.04098 0.03182 -0.0589 0.1253 0.9989
10.500 1.4027 0.04285 0.03394 -0.0583 0.1154 0.9989
10.750 1.4225 0.04476 0.03592 -0.0577 0.1063 0.9989
11.000 1.4420 0.04656 0.03758 -0.0573 0.0969 0.9989
11.250 1.4544 0.04786 0.03929 -0.0556 0.0878 0.9989
11.500 1.4660 0.04986 0.04151 -0.0541 0.0794 0.9989
11.750 1.4790 0.05196 0.04351 -0.0530 0.0718 0.9989
12.000 1.4832 0.05424 0.04625 -0.0504 0.0651 0.9989
12.250 1.4894 0.05715 0.04921 -0.0484 0.0595 0.9989
12.500 1.4861 0.05998 0.05242 -0.0452 0.0549 0.9989
12.750 1.4939 0.06312 0.05537 -0.0438 0.0505 0.9989
13.000 1.4778 0.06674 0.05947 -0.0394 0.0491 0.9989
13.250 1.4588 0.07085 0.06396 -0.0353 0.0480 0.9989
13.500 1.4408 0.07548 0.06893 -0.0328 0.0469 0.9989
13.750 1.4227 0.08057 0.07432 -0.0315 0.0461 0.9989
14.000 1.4038 0.08616 0.08020 -0.0312 0.0455 0.9989
14.250 1.3830 0.09241 0.08673 -0.0321 0.0450 0.9989
14.500 1.3574 0.09984 0.09446 -0.0343 0.0450 0.9989
14.750 1.3247 0.10909 0.10404 -0.0385 0.0456 0.9989
15.000 1.2876 0.12019 0.11546 -0.0450 0.0467 0.9989
15.250 1.2501 0.13277 0.12828 -0.0533 0.0480 0.9989
15.500 1.2150 0.14634 0.14197 -0.0625 0.0494 0.9989
15.750 1.1848 0.16034 0.15602 -0.0717 0.0504 0.9989
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Polar data table (+)
Polar graphs
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