S4096 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4096-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: S4096 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4096-il) Reynolds number: 500,000 Max Cl/Cd: 57.21 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4096-il-500000-n5.txt Download as CSV file: xf-s4096-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.7263 0.12709 0.12484 0.0236 1.0011 0.0096
-11.000 -0.9352 0.06398 0.06143 -0.0117 1.0011 0.0092
-10.750 -0.9549 0.05308 0.04993 -0.0166 1.0011 0.0093
-10.500 -0.9534 0.04559 0.04184 -0.0189 1.0011 0.0094
-10.250 -0.9362 0.04184 0.03778 -0.0202 1.0011 0.0096
-10.000 -0.9140 0.03940 0.03509 -0.0212 1.0011 0.0097
-9.750 -0.8899 0.03736 0.03284 -0.0221 1.0011 0.0099
-9.500 -0.8647 0.03546 0.03071 -0.0230 1.0011 0.0101
-9.250 -0.8384 0.03373 0.02878 -0.0239 1.0011 0.0104
-9.000 -0.8114 0.03223 0.02708 -0.0247 1.0011 0.0107
-8.750 -0.7839 0.03082 0.02547 -0.0255 1.0011 0.0110
-8.500 -0.7558 0.02934 0.02377 -0.0263 1.0011 0.0114
-8.250 -0.7274 0.02786 0.02205 -0.0271 1.0011 0.0117
-8.000 -0.6987 0.02657 0.02056 -0.0278 1.0011 0.0120
-7.750 -0.6696 0.02547 0.01929 -0.0285 1.0011 0.0122
-7.500 -0.6404 0.02455 0.01822 -0.0292 1.0011 0.0124
-7.250 -0.6110 0.02373 0.01727 -0.0298 1.0011 0.0126
-7.000 -0.5816 0.02284 0.01627 -0.0305 1.0011 0.0128
-6.750 -0.5524 0.02167 0.01502 -0.0313 1.0011 0.0132
-6.500 -0.5228 0.02092 0.01423 -0.0321 1.0011 0.0136
-6.250 -0.4931 0.02035 0.01363 -0.0328 1.0011 0.0140
-6.000 -0.4632 0.01985 0.01309 -0.0336 1.0011 0.0146
-5.750 -0.4332 0.01933 0.01253 -0.0343 1.0011 0.0150
-5.500 -0.4030 0.01884 0.01201 -0.0351 1.0011 0.0154
-5.250 -0.3728 0.01841 0.01153 -0.0358 1.0011 0.0158
-5.000 -0.3424 0.01803 0.01111 -0.0366 1.0011 0.0162
-4.750 -0.3121 0.01769 0.01075 -0.0374 1.0011 0.0166
-4.500 -0.2816 0.01736 0.01040 -0.0381 1.0011 0.0171
-4.250 -0.2511 0.01702 0.01004 -0.0390 1.0011 0.0179
-4.000 -0.2189 0.01699 0.00998 -0.0401 0.9866 0.0190
-3.750 -0.1859 0.01697 0.00993 -0.0414 0.9464 0.0205
-3.500 -0.1586 0.01700 0.00984 -0.0410 0.9057 0.0219
-3.250 -0.1316 0.01696 0.00969 -0.0407 0.8712 0.0251
-3.000 -0.1033 0.01683 0.00954 -0.0408 0.8419 0.0424
-2.750 -0.0742 0.01664 0.00941 -0.0412 0.8157 0.0816
-2.500 -0.0447 0.01645 0.00931 -0.0418 0.7921 0.1311
-2.250 -0.0149 0.01621 0.00926 -0.0426 0.7700 0.2058
-2.000 0.0150 0.01605 0.00923 -0.0434 0.7492 0.2707
-1.750 0.0450 0.01594 0.00920 -0.0441 0.7302 0.3240
-1.500 0.0752 0.01577 0.00921 -0.0450 0.7119 0.3959
-1.250 0.1054 0.01556 0.00927 -0.0459 0.6947 0.4942
-0.750 0.1647 0.01517 0.00951 -0.0472 0.6628 0.7089
-0.500 0.1919 0.01499 0.00965 -0.0470 0.6482 0.8149
-0.250 0.2121 0.01459 0.00949 -0.0447 0.6347 0.9423
0.000 0.2434 0.01411 0.00892 -0.0455 0.6204 0.9989
0.250 0.2739 0.01417 0.00889 -0.0463 0.6066 0.9989
0.500 0.3043 0.01425 0.00886 -0.0470 0.5927 0.9989
0.750 0.3348 0.01432 0.00884 -0.0478 0.5791 0.9989
1.000 0.3651 0.01440 0.00883 -0.0485 0.5652 0.9989
1.500 0.4258 0.01456 0.00883 -0.0500 0.5362 0.9989
1.750 0.4561 0.01465 0.00884 -0.0507 0.5214 0.9989
2.000 0.4864 0.01475 0.00886 -0.0515 0.5057 0.9989
2.250 0.5166 0.01486 0.00890 -0.0522 0.4883 0.9989
2.500 0.5467 0.01497 0.00893 -0.0529 0.4705 0.9989
2.750 0.5768 0.01510 0.00898 -0.0537 0.4516 0.9989
3.250 0.6367 0.01541 0.00911 -0.0551 0.4127 0.9989
3.500 0.6666 0.01558 0.00920 -0.0558 0.3927 0.9989
3.750 0.6964 0.01577 0.00931 -0.0566 0.3736 0.9989
4.000 0.7262 0.01595 0.00942 -0.0573 0.3554 0.9989
4.250 0.7560 0.01615 0.00954 -0.0580 0.3367 0.9989
4.500 0.7856 0.01636 0.00968 -0.0587 0.3182 0.9989
4.750 0.8152 0.01660 0.00984 -0.0594 0.2998 0.9989
5.000 0.8447 0.01683 0.01001 -0.0601 0.2820 0.9989
5.250 0.8741 0.01707 0.01019 -0.0608 0.2643 0.9989
5.500 0.9034 0.01734 0.01040 -0.0615 0.2468 0.9989
5.750 0.9327 0.01760 0.01061 -0.0621 0.2313 0.9989
6.000 0.9619 0.01789 0.01085 -0.0628 0.2154 0.9989
6.250 0.9909 0.01820 0.01111 -0.0635 0.1997 0.9989
6.500 1.0199 0.01852 0.01138 -0.0641 0.1850 0.9989
7.000 1.0773 0.01924 0.01198 -0.0653 0.1535 0.9989
7.250 1.1058 0.01962 0.01232 -0.0659 0.1393 0.9989
7.500 1.1343 0.01999 0.01266 -0.0665 0.1278 0.9989
7.750 1.1625 0.02039 0.01303 -0.0671 0.1159 0.9989
8.000 1.1905 0.02083 0.01342 -0.0676 0.1033 0.9989
8.250 1.2183 0.02130 0.01386 -0.0681 0.0909 0.9989
8.500 1.2459 0.02179 0.01431 -0.0686 0.0792 0.9989
8.750 1.2734 0.02226 0.01477 -0.0691 0.0704 0.9989
9.000 1.3007 0.02277 0.01526 -0.0695 0.0623 0.9989
9.250 1.3275 0.02335 0.01581 -0.0699 0.0534 0.9989
9.500 1.3540 0.02393 0.01638 -0.0702 0.0457 0.9989
9.750 1.3805 0.02449 0.01695 -0.0705 0.0395 0.9989
10.000 1.4064 0.02514 0.01759 -0.0708 0.0334 0.9989
10.250 1.4320 0.02581 0.01826 -0.0710 0.0285 0.9989
10.500 1.4575 0.02644 0.01894 -0.0712 0.0246 0.9989
10.750 1.4822 0.02718 0.01969 -0.0713 0.0205 0.9989
11.000 1.5061 0.02802 0.02054 -0.0713 0.0153 0.9989
11.250 1.5286 0.02902 0.02154 -0.0711 0.0102 0.9989
11.500 1.5505 0.03006 0.02262 -0.0708 0.0078 0.9989
11.750 1.5721 0.03105 0.02369 -0.0704 0.0067 0.9989
12.000 1.5930 0.03205 0.02479 -0.0700 0.0060 0.9989
12.250 1.6124 0.03318 0.02600 -0.0693 0.0055 0.9989
12.500 1.6301 0.03443 0.02736 -0.0684 0.0052 0.9989
12.750 1.6475 0.03560 0.02864 -0.0674 0.0050 0.9989
13.000 1.6628 0.03689 0.03006 -0.0662 0.0048 0.9989
13.250 1.6754 0.03834 0.03163 -0.0646 0.0046 0.9989
13.500 1.6843 0.03997 0.03342 -0.0625 0.0045 0.9989
13.750 1.6868 0.04191 0.03549 -0.0595 0.0044 0.9989
14.000 1.6755 0.04458 0.03830 -0.0546 0.0043 0.9989
14.250 1.6680 0.04761 0.04149 -0.0515 0.0042 0.9989
14.500 1.6615 0.05105 0.04509 -0.0496 0.0042 0.9989
14.750 1.6548 0.05494 0.04914 -0.0486 0.0041 0.9989
15.000 1.6468 0.05933 0.05369 -0.0482 0.0040 0.9989
15.250 1.6373 0.06422 0.05874 -0.0485 0.0040 0.9989
15.500 1.6259 0.06965 0.06433 -0.0494 0.0040 0.9989
15.750 1.6122 0.07561 0.07046 -0.0506 0.0039 0.9989
16.000 1.5963 0.08207 0.07710 -0.0524 0.0039 0.9989
16.250 1.5781 0.08902 0.08421 -0.0544 0.0039 0.9989
16.500 1.5584 0.09640 0.09176 -0.0569 0.0039 0.9989
16.750 1.5378 0.10417 0.09970 -0.0599 0.0038 0.9989
17.000 1.5170 0.11229 0.10799 -0.0632 0.0038 0.9989
|
Polar data table (+)
Polar graphs
<< Back to S4096 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4096-il)