S4096 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4096-il) Xfoil prediction polar at RE=500,000 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: 500,000 Max Cl/Cd: 59.08 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4096-il-500000.txt Download as CSV file: xf-s4096-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.6947 0.10204 0.09991 0.0091 1.0011 0.0228
-9.000 -0.7093 0.09478 0.09267 0.0041 1.0011 0.0230
-8.750 -0.7150 0.08480 0.08265 -0.0053 1.0011 0.0234
-8.500 -0.6902 0.05170 0.04885 -0.0261 1.0011 0.0267
-8.250 -0.6737 0.04927 0.04642 -0.0265 1.0011 0.0272
-8.000 -0.6571 0.04660 0.04366 -0.0272 1.0011 0.0279
-7.750 -0.6391 0.04338 0.04028 -0.0282 1.0011 0.0289
-7.500 -0.6423 0.03220 0.02677 -0.0297 1.0011 0.0209
-7.250 -0.6125 0.03097 0.02531 -0.0303 1.0011 0.0206
-7.000 -0.5831 0.02774 0.02174 -0.0314 1.0011 0.0208
-6.750 -0.5534 0.02559 0.01937 -0.0322 1.0011 0.0209
-6.500 -0.5236 0.02389 0.01751 -0.0328 1.0011 0.0210
-6.250 -0.4939 0.02245 0.01596 -0.0335 1.0011 0.0213
-6.000 -0.4641 0.02137 0.01481 -0.0342 1.0011 0.0217
-5.750 -0.4342 0.02052 0.01391 -0.0348 1.0011 0.0222
-5.500 -0.4041 0.01979 0.01314 -0.0355 1.0011 0.0227
-5.250 -0.3739 0.01920 0.01253 -0.0362 1.0011 0.0236
-5.000 -0.3436 0.01868 0.01197 -0.0370 1.0011 0.0246
-4.750 -0.3131 0.01816 0.01141 -0.0377 1.0011 0.0253
-4.500 -0.2826 0.01773 0.01095 -0.0384 1.0011 0.0259
-4.250 -0.2517 0.01713 0.01031 -0.0393 1.0011 0.0275
-4.000 -0.2210 0.01679 0.00997 -0.0401 1.0011 0.0294
-3.750 -0.1903 0.01654 0.00971 -0.0409 1.0011 0.0319
-3.500 -0.1594 0.01626 0.00946 -0.0417 1.0011 0.0394
-3.250 -0.1283 0.01568 0.00930 -0.0429 1.0011 0.1237
-3.000 -0.0975 0.01528 0.00931 -0.0442 1.0011 0.2194
-2.750 -0.0666 0.01503 0.00938 -0.0453 1.0011 0.3048
-2.500 -0.0358 0.01485 0.00948 -0.0464 1.0011 0.3778
-2.250 0.0005 0.01486 0.00979 -0.0488 0.9756 0.4639
-2.000 0.0316 0.01472 0.00997 -0.0496 0.9355 0.5629
-1.750 0.0562 0.01459 0.01019 -0.0486 0.8978 0.6842
-1.500 0.0761 0.01432 0.01046 -0.0461 0.8673 0.8596
-1.250 0.0977 0.01355 0.00972 -0.0439 0.8381 0.9989
-1.000 0.1270 0.01361 0.00960 -0.0443 0.8120 0.9989
-0.750 0.1567 0.01367 0.00949 -0.0447 0.7887 0.9989
-0.500 0.1867 0.01374 0.00940 -0.0453 0.7667 0.9989
-0.250 0.2167 0.01381 0.00932 -0.0459 0.7466 0.9989
0.000 0.2468 0.01387 0.00925 -0.0465 0.7280 0.9989
0.250 0.2771 0.01394 0.00920 -0.0471 0.7102 0.9989
0.500 0.3073 0.01400 0.00916 -0.0478 0.6933 0.9989
0.750 0.3376 0.01407 0.00912 -0.0485 0.6772 0.9989
1.000 0.3678 0.01415 0.00910 -0.0492 0.6615 0.9989
1.250 0.3981 0.01422 0.00909 -0.0499 0.6464 0.9989
1.500 0.4283 0.01430 0.00909 -0.0505 0.6315 0.9989
1.750 0.4585 0.01438 0.00909 -0.0512 0.6168 0.9989
2.000 0.4887 0.01447 0.00911 -0.0519 0.6020 0.9989
2.250 0.5189 0.01456 0.00913 -0.0526 0.5872 0.9989
2.500 0.5490 0.01465 0.00916 -0.0533 0.5720 0.9989
2.750 0.5791 0.01475 0.00920 -0.0540 0.5563 0.9989
3.000 0.6092 0.01485 0.00924 -0.0547 0.5401 0.9989
3.250 0.6392 0.01497 0.00930 -0.0554 0.5227 0.9989
3.500 0.6691 0.01510 0.00936 -0.0560 0.5046 0.9989
3.750 0.6990 0.01524 0.00943 -0.0567 0.4856 0.9989
4.000 0.7289 0.01538 0.00952 -0.0574 0.4652 0.9989
4.250 0.7586 0.01556 0.00962 -0.0581 0.4439 0.9989
4.500 0.7883 0.01575 0.00973 -0.0588 0.4225 0.9989
4.750 0.8179 0.01596 0.00986 -0.0595 0.4004 0.9989
5.000 0.8474 0.01618 0.01001 -0.0601 0.3790 0.9989
5.250 0.8768 0.01642 0.01017 -0.0608 0.3572 0.9989
5.500 0.9061 0.01668 0.01036 -0.0615 0.3369 0.9989
5.750 0.9355 0.01694 0.01056 -0.0621 0.3159 0.9989
6.000 0.9646 0.01723 0.01078 -0.0628 0.2959 0.9989
6.250 0.9937 0.01753 0.01102 -0.0634 0.2761 0.9989
6.500 1.0227 0.01784 0.01127 -0.0641 0.2567 0.9989
6.750 1.0514 0.01821 0.01156 -0.0647 0.2368 0.9989
7.000 1.0802 0.01856 0.01186 -0.0653 0.2176 0.9989
7.250 1.1088 0.01894 0.01218 -0.0659 0.1992 0.9989
7.500 1.1372 0.01934 0.01252 -0.0665 0.1823 0.9989
7.750 1.1655 0.01975 0.01288 -0.0671 0.1669 0.9989
8.000 1.1935 0.02020 0.01329 -0.0676 0.1517 0.9989
8.500 1.2491 0.02116 0.01415 -0.0686 0.1222 0.9989
8.750 1.2766 0.02167 0.01462 -0.0691 0.1085 0.9989
9.000 1.3037 0.02221 0.01512 -0.0695 0.0957 0.9989
9.250 1.3306 0.02279 0.01566 -0.0699 0.0841 0.9989
9.500 1.3574 0.02336 0.01621 -0.0703 0.0741 0.9989
9.750 1.3839 0.02392 0.01677 -0.0706 0.0651 0.9989
10.000 1.4101 0.02453 0.01740 -0.0709 0.0576 0.9989
10.250 1.4356 0.02526 0.01810 -0.0711 0.0503 0.9989
10.500 1.4615 0.02583 0.01871 -0.0713 0.0453 0.9989
10.750 1.4864 0.02656 0.01946 -0.0714 0.0399 0.9989
11.000 1.5109 0.02731 0.02021 -0.0715 0.0342 0.9989
11.250 1.5348 0.02810 0.02103 -0.0715 0.0282 0.9989
11.500 1.5559 0.02933 0.02223 -0.0711 0.0200 0.9989
11.750 1.5760 0.03064 0.02356 -0.0705 0.0150 0.9989
12.000 1.5956 0.03188 0.02485 -0.0699 0.0127 0.9989
12.250 1.6138 0.03321 0.02628 -0.0690 0.0114 0.9989
12.500 1.6317 0.03444 0.02762 -0.0681 0.0106 0.9989
12.750 1.6464 0.03592 0.02922 -0.0668 0.0099 0.9989
13.000 1.6545 0.03796 0.03138 -0.0646 0.0094 0.9989
13.250 1.6594 0.04004 0.03360 -0.0620 0.0091 0.9989
13.500 1.6605 0.04210 0.03582 -0.0588 0.0089 0.9989
13.750 1.6474 0.04495 0.03882 -0.0537 0.0087 0.9989
14.000 1.6383 0.04823 0.04226 -0.0506 0.0086 0.9989
14.250 1.6301 0.05199 0.04618 -0.0488 0.0085 0.9989
14.500 1.6217 0.05622 0.05057 -0.0479 0.0083 0.9989
14.750 1.6125 0.06092 0.05544 -0.0478 0.0082 0.9989
15.000 1.6019 0.06609 0.06076 -0.0483 0.0081 0.9989
15.250 1.5901 0.07165 0.06649 -0.0492 0.0080 0.9989
15.500 1.5766 0.07763 0.07262 -0.0505 0.0080 0.9989
15.750 1.5617 0.08392 0.07908 -0.0522 0.0079 0.9989
16.000 1.5454 0.09051 0.08582 -0.0541 0.0079 0.9989
16.250 1.5286 0.09732 0.09278 -0.0563 0.0078 0.9989
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