S4096 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4096-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: S4096 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4096-il) Reynolds number: 1,000,000 Max Cl/Cd: 63.08 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4096-il-1000000-n5.txt Download as CSV file: xf-s4096-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -1.2109 0.05545 0.05306 -0.0129 1.0011 0.0065
-13.250 -1.2229 0.04913 0.04642 -0.0141 1.0011 0.0066
-13.000 -1.2260 0.04320 0.04007 -0.0149 1.0011 0.0067
-12.750 -1.2106 0.04047 0.03712 -0.0154 1.0011 0.0068
-12.500 -1.1894 0.03887 0.03540 -0.0159 1.0011 0.0069
-12.250 -1.1667 0.03747 0.03388 -0.0164 1.0011 0.0070
-12.000 -1.1426 0.03631 0.03263 -0.0169 1.0011 0.0071
-11.750 -1.1173 0.03544 0.03169 -0.0174 1.0011 0.0072
-11.500 -1.0920 0.03443 0.03058 -0.0180 1.0011 0.0073
-11.250 -1.0665 0.03330 0.02933 -0.0186 1.0011 0.0074
-11.000 -1.0407 0.03211 0.02801 -0.0192 1.0011 0.0076
-10.750 -1.0145 0.03084 0.02659 -0.0199 1.0011 0.0077
-10.500 -0.9879 0.02959 0.02520 -0.0206 1.0011 0.0079
-10.250 -0.9608 0.02844 0.02390 -0.0212 1.0011 0.0081
-10.000 -0.9333 0.02734 0.02266 -0.0219 1.0011 0.0082
-9.750 -0.9054 0.02631 0.02149 -0.0226 1.0011 0.0084
-9.500 -0.8771 0.02539 0.02044 -0.0232 1.0011 0.0086
-9.250 -0.8486 0.02460 0.01955 -0.0239 1.0011 0.0088
-9.000 -0.8197 0.02393 0.01879 -0.0246 1.0011 0.0090
-8.750 -0.7907 0.02337 0.01815 -0.0252 1.0011 0.0091
-8.500 -0.7615 0.02280 0.01750 -0.0259 1.0011 0.0092
-8.250 -0.7323 0.02210 0.01671 -0.0266 1.0011 0.0093
-8.000 -0.7034 0.02095 0.01544 -0.0274 1.0011 0.0096
-7.750 -0.6739 0.02026 0.01469 -0.0281 1.0011 0.0098
-7.500 -0.6443 0.01974 0.01413 -0.0289 1.0011 0.0100
-7.250 -0.6145 0.01927 0.01362 -0.0296 1.0011 0.0102
-7.000 -0.5847 0.01884 0.01316 -0.0303 1.0011 0.0104
-6.750 -0.5547 0.01843 0.01271 -0.0310 1.0011 0.0106
-6.500 -0.5247 0.01804 0.01230 -0.0318 1.0011 0.0109
-6.250 -0.4945 0.01767 0.01190 -0.0325 1.0011 0.0111
-6.000 -0.4643 0.01735 0.01154 -0.0333 1.0011 0.0115
-5.750 -0.4341 0.01705 0.01122 -0.0340 1.0011 0.0118
-5.500 -0.4037 0.01679 0.01094 -0.0347 1.0011 0.0122
-5.250 -0.3724 0.01669 0.01081 -0.0357 0.9899 0.0124
-5.000 -0.3423 0.01671 0.01078 -0.0362 0.9466 0.0126
-4.750 -0.3166 0.01668 0.01060 -0.0356 0.9031 0.0129
-4.500 -0.2885 0.01654 0.01030 -0.0356 0.8688 0.0134
-4.250 -0.2594 0.01644 0.01006 -0.0360 0.8381 0.0139
-4.000 -0.2298 0.01635 0.00985 -0.0365 0.8103 0.0144
-3.750 -0.1998 0.01627 0.00967 -0.0371 0.7858 0.0150
-3.500 -0.1698 0.01620 0.00950 -0.0377 0.7631 0.0157
-3.250 -0.1396 0.01614 0.00935 -0.0383 0.7423 0.0164
-3.000 -0.1093 0.01609 0.00921 -0.0390 0.7228 0.0177
-2.750 -0.0790 0.01602 0.00909 -0.0397 0.7043 0.0202
-2.500 -0.0485 0.01591 0.00898 -0.0405 0.6872 0.0362
-2.000 0.0126 0.01561 0.00887 -0.0422 0.6559 0.1164
-1.750 0.0431 0.01549 0.00884 -0.0431 0.6411 0.1622
-1.500 0.0737 0.01535 0.00884 -0.0440 0.6269 0.2202
-1.250 0.1043 0.01521 0.00888 -0.0450 0.6131 0.2884
-1.000 0.1349 0.01512 0.00891 -0.0459 0.6000 0.3434
-0.750 0.1655 0.01502 0.00897 -0.0468 0.5874 0.4062
-0.500 0.1961 0.01492 0.00906 -0.0478 0.5749 0.4812
-0.250 0.2267 0.01479 0.00920 -0.0487 0.5625 0.5795
0.000 0.2572 0.01471 0.00932 -0.0496 0.5499 0.6608
0.250 0.2873 0.01461 0.00947 -0.0504 0.5366 0.7488
0.500 0.3158 0.01449 0.00963 -0.0506 0.5231 0.8472
0.750 0.3378 0.01420 0.00955 -0.0489 0.5100 0.9522
1.000 0.3681 0.01387 0.00917 -0.0496 0.4952 0.9989
1.250 0.3986 0.01393 0.00915 -0.0504 0.4792 0.9989
1.750 0.4594 0.01409 0.00913 -0.0519 0.4441 0.9989
2.000 0.4897 0.01417 0.00912 -0.0527 0.4260 0.9989
2.250 0.5200 0.01427 0.00913 -0.0535 0.4073 0.9989
2.500 0.5502 0.01437 0.00914 -0.0542 0.3888 0.9989
2.750 0.5803 0.01447 0.00916 -0.0550 0.3707 0.9989
3.000 0.6105 0.01458 0.00919 -0.0557 0.3531 0.9989
3.250 0.6406 0.01470 0.00923 -0.0565 0.3369 0.9989
3.500 0.6706 0.01483 0.00928 -0.0572 0.3193 0.9989
3.750 0.7006 0.01496 0.00935 -0.0580 0.3028 0.9989
4.000 0.7305 0.01511 0.00942 -0.0587 0.2857 0.9989
4.250 0.7604 0.01528 0.00950 -0.0595 0.2696 0.9989
4.500 0.7902 0.01544 0.00961 -0.0602 0.2532 0.9989
4.750 0.8199 0.01562 0.00971 -0.0609 0.2375 0.9989
5.000 0.8496 0.01580 0.00983 -0.0616 0.2220 0.9989
5.250 0.8792 0.01599 0.00996 -0.0623 0.2090 0.9989
5.500 0.9088 0.01620 0.01011 -0.0630 0.1943 0.9989
5.750 0.9383 0.01641 0.01027 -0.0637 0.1813 0.9989
6.000 0.9676 0.01664 0.01044 -0.0644 0.1675 0.9989
6.250 0.9969 0.01690 0.01063 -0.0651 0.1527 0.9989
6.500 1.0260 0.01718 0.01084 -0.0657 0.1374 0.9989
6.750 1.0551 0.01745 0.01106 -0.0664 0.1261 0.9989
7.000 1.0840 0.01775 0.01131 -0.0670 0.1128 0.9989
7.250 1.1127 0.01808 0.01158 -0.0677 0.0997 0.9989
7.500 1.1414 0.01843 0.01186 -0.0683 0.0882 0.9989
7.750 1.1700 0.01878 0.01216 -0.0689 0.0777 0.9989
8.000 1.1984 0.01914 0.01248 -0.0694 0.0683 0.9989
8.250 1.2267 0.01951 0.01282 -0.0700 0.0592 0.9989
8.500 1.2548 0.01992 0.01318 -0.0705 0.0507 0.9989
8.750 1.2827 0.02035 0.01357 -0.0710 0.0435 0.9989
9.000 1.3103 0.02080 0.01399 -0.0715 0.0365 0.9989
9.250 1.3380 0.02121 0.01440 -0.0720 0.0318 0.9989
9.500 1.3653 0.02169 0.01485 -0.0724 0.0268 0.9989
9.750 1.3923 0.02222 0.01536 -0.0728 0.0218 0.9989
10.000 1.4191 0.02274 0.01587 -0.0731 0.0175 0.9989
10.250 1.4449 0.02345 0.01655 -0.0734 0.0106 0.9989
10.500 1.4702 0.02422 0.01730 -0.0736 0.0063 0.9989
10.750 1.4959 0.02485 0.01796 -0.0737 0.0051 0.9989
11.000 1.5216 0.02543 0.01859 -0.0739 0.0046 0.9989
11.250 1.5469 0.02606 0.01926 -0.0740 0.0042 0.9989
11.500 1.5715 0.02674 0.02000 -0.0741 0.0039 0.9989
11.750 1.5956 0.02749 0.02082 -0.0740 0.0036 0.9989
12.000 1.6194 0.02820 0.02159 -0.0739 0.0035 0.9989
12.250 1.6428 0.02892 0.02238 -0.0738 0.0034 0.9989
12.500 1.6654 0.02970 0.02322 -0.0735 0.0032 0.9989
12.750 1.6872 0.03053 0.02413 -0.0732 0.0031 0.9989
13.000 1.7079 0.03143 0.02510 -0.0726 0.0030 0.9989
13.250 1.7275 0.03240 0.02616 -0.0720 0.0029 0.9989
13.500 1.7457 0.03345 0.02729 -0.0711 0.0028 0.9989
13.750 1.7622 0.03459 0.02852 -0.0700 0.0028 0.9989
14.000 1.7764 0.03586 0.02988 -0.0686 0.0027 0.9989
14.250 1.7874 0.03730 0.03141 -0.0667 0.0026 0.9989
14.500 1.7938 0.03898 0.03320 -0.0642 0.0025 0.9989
14.750 1.7834 0.04137 0.03571 -0.0589 0.0025 0.9989
15.000 1.7731 0.04427 0.03874 -0.0548 0.0025 0.9989
15.250 1.7658 0.04753 0.04213 -0.0523 0.0024 0.9989
15.500 1.7583 0.05128 0.04602 -0.0507 0.0024 0.9989
15.750 1.7495 0.05558 0.05048 -0.0500 0.0024 0.9989
16.000 1.7388 0.06045 0.05549 -0.0499 0.0023 0.9989
16.250 1.7255 0.06598 0.06119 -0.0505 0.0023 0.9989
16.500 1.7101 0.07205 0.06741 -0.0516 0.0023 0.9989
16.750 1.6915 0.07879 0.07432 -0.0532 0.0022 0.9989
17.000 1.6702 0.08612 0.08181 -0.0552 0.0022 0.9989
17.250 1.6476 0.09378 0.08964 -0.0576 0.0022 0.9989
17.500 1.6242 0.10187 0.09788 -0.0605 0.0022 0.9989
17.750 1.6002 0.11043 0.10660 -0.0639 0.0022 0.9989
18.000 1.5762 0.11921 0.11554 -0.0677 0.0022 0.9989
|
Polar data table (+)
Polar graphs
<< Back to S4096 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4096-il)