S4096 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4096-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: S4096 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4096-il) Reynolds number: 200,000 Max Cl/Cd: 48.99 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4096-il-200000.txt Download as CSV file: xf-s4096-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.6728 0.09628 0.09295 0.0001 1.0011 0.0564
-8.250 -0.6714 0.08958 0.08621 -0.0057 1.0011 0.0583
-8.000 -0.6792 0.07379 0.06956 -0.0230 1.0011 0.0638
-7.750 -0.6613 0.06941 0.06539 -0.0228 1.0011 0.0651
-7.500 -0.6424 0.06691 0.06295 -0.0228 1.0011 0.0669
-7.250 -0.6216 0.06340 0.05931 -0.0246 1.0011 0.0713
-7.000 -0.5992 0.05673 0.05216 -0.0291 1.0011 0.0789
-6.750 -0.5571 0.03851 0.03175 -0.0335 1.0011 0.0422
-6.500 -0.5268 0.03529 0.02827 -0.0344 1.0011 0.0402
-6.250 -0.4962 0.03183 0.02441 -0.0354 1.0011 0.0393
-6.000 -0.4654 0.02963 0.02186 -0.0360 1.0011 0.0397
-5.750 -0.4347 0.02808 0.02002 -0.0366 1.0011 0.0406
-5.500 -0.4041 0.02636 0.01808 -0.0371 1.0011 0.0409
-5.250 -0.3738 0.02500 0.01655 -0.0376 1.0011 0.0413
-5.000 -0.3441 0.02317 0.01468 -0.0381 1.0011 0.0424
-4.750 -0.3144 0.02201 0.01357 -0.0387 1.0011 0.0443
-4.500 -0.2844 0.02128 0.01284 -0.0393 1.0011 0.0475
-4.250 -0.2541 0.02070 0.01220 -0.0399 1.0011 0.0513
-4.000 -0.2236 0.01979 0.01136 -0.0408 1.0011 0.0576
-3.750 -0.1926 0.01906 0.01067 -0.0416 1.0011 0.0757
-3.500 -0.1621 0.01760 0.01028 -0.0432 1.0011 0.2704
-3.250 -0.1323 0.01714 0.01022 -0.0441 1.0011 0.3763
-3.000 -0.1029 0.01673 0.01024 -0.0449 1.0011 0.4771
-2.750 -0.0748 0.01628 0.01038 -0.0452 1.0011 0.6104
-2.500 -0.0530 0.01581 0.01064 -0.0434 1.0011 0.7853
-2.250 -0.0315 0.01477 0.00994 -0.0408 1.0011 0.9989
-2.000 -0.0010 0.01496 0.00999 -0.0418 1.0011 0.9989
-1.750 0.0291 0.01524 0.01016 -0.0429 1.0011 0.9989
-1.500 0.0584 0.01570 0.01054 -0.0438 1.0011 0.9989
-1.250 0.0954 0.01595 0.01068 -0.0465 0.9945 0.9989
-1.000 0.1394 0.01561 0.01023 -0.0504 0.9747 0.9989
-0.750 0.1792 0.01540 0.00991 -0.0532 0.9482 0.9989
-0.500 0.2112 0.01536 0.00974 -0.0539 0.9176 0.9989
-0.250 0.2378 0.01543 0.00967 -0.0532 0.8878 0.9989
0.000 0.2640 0.01553 0.00963 -0.0525 0.8614 0.9989
0.250 0.2907 0.01565 0.00959 -0.0520 0.8380 0.9989
0.500 0.3186 0.01578 0.00958 -0.0519 0.8156 0.9989
0.750 0.3467 0.01591 0.00957 -0.0519 0.7952 0.9989
1.000 0.3751 0.01605 0.00958 -0.0519 0.7764 0.9989
1.250 0.4041 0.01619 0.00960 -0.0522 0.7576 0.9989
1.500 0.4332 0.01633 0.00964 -0.0525 0.7394 0.9989
1.750 0.4623 0.01647 0.00969 -0.0528 0.7218 0.9989
2.000 0.4915 0.01663 0.00975 -0.0531 0.7046 0.9989
2.250 0.5207 0.01678 0.00981 -0.0535 0.6878 0.9989
2.500 0.5500 0.01694 0.00989 -0.0539 0.6710 0.9989
2.750 0.5792 0.01711 0.00998 -0.0543 0.6542 0.9989
3.000 0.6086 0.01727 0.01008 -0.0547 0.6369 0.9989
3.250 0.6380 0.01743 0.01020 -0.0552 0.6190 0.9989
3.500 0.6673 0.01760 0.01032 -0.0556 0.6008 0.9989
3.750 0.6966 0.01778 0.01044 -0.0561 0.5824 0.9989
4.000 0.7257 0.01798 0.01058 -0.0565 0.5639 0.9989
4.250 0.7550 0.01817 0.01074 -0.0570 0.5438 0.9989
4.500 0.7842 0.01836 0.01090 -0.0574 0.5230 0.9989
4.750 0.8132 0.01860 0.01107 -0.0579 0.5025 0.9989
5.000 0.8423 0.01882 0.01127 -0.0584 0.4794 0.9989
5.250 0.8711 0.01911 0.01147 -0.0588 0.4573 0.9989
5.500 0.9000 0.01939 0.01173 -0.0593 0.4331 0.9989
5.750 0.9286 0.01973 0.01200 -0.0598 0.4098 0.9989
6.000 0.9571 0.02010 0.01231 -0.0603 0.3859 0.9989
6.250 0.9855 0.02050 0.01267 -0.0608 0.3626 0.9989
6.500 1.0136 0.02095 0.01304 -0.0612 0.3397 0.9989
6.750 1.0418 0.02139 0.01346 -0.0617 0.3168 0.9989
7.000 1.0695 0.02190 0.01389 -0.0622 0.2950 0.9989
7.250 1.0974 0.02240 0.01439 -0.0626 0.2729 0.9989
7.500 1.1248 0.02297 0.01490 -0.0630 0.2520 0.9989
7.750 1.1521 0.02354 0.01545 -0.0635 0.2313 0.9989
8.000 1.1791 0.02416 0.01605 -0.0638 0.2115 0.9989
8.250 1.2055 0.02487 0.01670 -0.0642 0.1932 0.9989
8.500 1.2319 0.02557 0.01740 -0.0645 0.1757 0.9989
8.750 1.2579 0.02632 0.01815 -0.0647 0.1593 0.9989
9.000 1.2834 0.02713 0.01899 -0.0649 0.1444 0.9989
9.250 1.3084 0.02801 0.01988 -0.0649 0.1305 0.9989
9.500 1.3326 0.02898 0.02085 -0.0649 0.1180 0.9989
9.750 1.3560 0.03005 0.02192 -0.0648 0.1068 0.9989
10.000 1.3785 0.03115 0.02300 -0.0646 0.0961 0.9989
10.250 1.4016 0.03203 0.02395 -0.0646 0.0856 0.9989
10.500 1.4248 0.03285 0.02488 -0.0645 0.0761 0.9989
10.750 1.4454 0.03404 0.02613 -0.0640 0.0686 0.9989
11.000 1.4638 0.03540 0.02749 -0.0633 0.0616 0.9989
11.250 1.4842 0.03645 0.02873 -0.0627 0.0552 0.9989
11.500 1.4989 0.03812 0.03046 -0.0615 0.0490 0.9989
11.750 1.5129 0.03967 0.03209 -0.0603 0.0422 0.9989
12.000 1.5235 0.04153 0.03410 -0.0585 0.0357 0.9989
12.250 1.5245 0.04415 0.03679 -0.0555 0.0314 0.9989
12.500 1.5258 0.04639 0.03918 -0.0525 0.0284 0.9989
12.750 1.5136 0.04942 0.04231 -0.0480 0.0271 0.9989
13.000 1.4982 0.05351 0.04647 -0.0444 0.0259 0.9989
13.250 1.4940 0.05687 0.05008 -0.0426 0.0248 0.9989
13.500 1.4887 0.06061 0.05402 -0.0413 0.0237 0.9989
13.750 1.4832 0.06456 0.05813 -0.0406 0.0228 0.9989
14.000 1.4775 0.06869 0.06240 -0.0403 0.0221 0.9989
14.250 1.4713 0.07298 0.06680 -0.0403 0.0215 0.9989
14.500 1.4640 0.07746 0.07138 -0.0403 0.0210 0.9989
14.750 1.4551 0.08216 0.07621 -0.0399 0.0205 0.9989
15.000 1.4462 0.08714 0.08138 -0.0404 0.0202 0.9989
15.250 1.4370 0.09236 0.08683 -0.0416 0.0199 0.9989
15.500 1.4266 0.09789 0.09259 -0.0432 0.0197 0.9989
15.750 1.4151 0.10376 0.09868 -0.0453 0.0195 0.9989
16.000 1.4026 0.11002 0.10516 -0.0479 0.0192 0.9989
16.250 1.3897 0.11673 0.11208 -0.0510 0.0191 0.9989
16.500 1.3760 0.12390 0.11948 -0.0549 0.0189 0.9989
16.750 1.3610 0.13167 0.12746 -0.0593 0.0189 0.9989
17.000 1.3447 0.14014 0.13615 -0.0646 0.0188 0.9989
17.250 1.3263 0.14959 0.14582 -0.0708 0.0189 0.9989
17.500 1.3053 0.16034 0.15680 -0.0782 0.0191 0.9989
17.750 1.2805 0.17293 0.16959 -0.0871 0.0194 0.9989
|
Polar data table (+)
Polar graphs
<< Back to S4096 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4096-il)