S4095 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4095-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: S4095 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4095-il) Reynolds number: 500,000 Max Cl/Cd: 67.2 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4095-il-500000.txt Download as CSV file: xf-s4095-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: S4095 (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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5108 0.11565 0.11358 0.0167 1.0007 0.0205
-9.250 -0.5098 0.11176 0.10971 0.0157 1.0007 0.0209
-9.000 -0.6470 0.10880 0.10669 0.0237 1.0007 0.0199
-8.750 -0.6433 0.10582 0.10372 0.0235 1.0007 0.0201
-8.500 -0.6419 0.10246 0.10037 0.0227 1.0007 0.0202
-8.250 -0.6437 0.09873 0.09666 0.0214 1.0007 0.0204
-8.000 -0.6409 0.09428 0.09222 0.0179 1.0007 0.0208
-7.750 -0.6352 0.08897 0.08690 0.0128 1.0007 0.0213
-7.500 -0.6267 0.07224 0.07004 -0.0064 1.0007 0.0230
-7.250 -0.6117 0.07007 0.06783 -0.0073 1.0007 0.0233
-7.000 -0.5866 0.05407 0.05134 -0.0206 1.0007 0.0262
-6.750 -0.5660 0.05311 0.05041 -0.0211 1.0007 0.0265
-6.500 -0.5428 0.05100 0.04823 -0.0226 1.0007 0.0272
-6.250 -0.5062 0.03960 0.03565 -0.0301 1.0007 0.0330
-6.000 -0.4683 0.02719 0.02200 -0.0337 1.0007 0.0228
-5.750 -0.4342 0.02225 0.01637 -0.0351 1.0007 0.0197
-5.500 -0.4032 0.02046 0.01431 -0.0358 1.0007 0.0198
-5.250 -0.3726 0.01885 0.01252 -0.0364 1.0007 0.0200
-5.000 -0.3426 0.01762 0.01126 -0.0370 1.0007 0.0204
-4.750 -0.3125 0.01677 0.01036 -0.0376 1.0007 0.0209
-4.500 -0.2824 0.01604 0.00960 -0.0381 1.0007 0.0214
-4.250 -0.2522 0.01545 0.00896 -0.0386 1.0007 0.0222
-4.000 -0.2218 0.01483 0.00831 -0.0392 1.0007 0.0232
-3.750 -0.1915 0.01425 0.00777 -0.0398 1.0007 0.0241
-3.500 -0.1609 0.01380 0.00731 -0.0404 1.0007 0.0253
-3.250 -0.1303 0.01336 0.00688 -0.0410 1.0007 0.0269
-3.000 -0.0997 0.01302 0.00656 -0.0417 1.0007 0.0295
-2.750 -0.0689 0.01268 0.00627 -0.0423 1.0007 0.0349
-2.500 -0.0354 0.01249 0.00633 -0.0437 0.9717 0.0814
-2.250 -0.0088 0.01258 0.00651 -0.0431 0.9123 0.1254
-1.750 0.0431 0.01240 0.00644 -0.0419 0.8326 0.2381
-1.500 0.0715 0.01214 0.00640 -0.0422 0.8020 0.3419
-1.250 0.1004 0.01172 0.00643 -0.0427 0.7743 0.5032
-1.000 0.1269 0.01106 0.00660 -0.0425 0.7500 0.7677
-0.750 0.1470 0.01005 0.00594 -0.0399 0.7279 0.9993
-0.500 0.1767 0.01014 0.00586 -0.0402 0.7063 0.9993
-0.250 0.2065 0.01023 0.00580 -0.0406 0.6864 0.9993
0.000 0.2362 0.01033 0.00575 -0.0410 0.6677 0.9993
0.250 0.2660 0.01042 0.00571 -0.0414 0.6497 0.9993
0.500 0.2957 0.01053 0.00568 -0.0418 0.6325 0.9993
0.750 0.3255 0.01063 0.00567 -0.0422 0.6154 0.9993
1.000 0.3553 0.01072 0.00567 -0.0426 0.5990 0.9993
1.250 0.3850 0.01082 0.00567 -0.0430 0.5830 0.9993
1.500 0.4147 0.01093 0.00569 -0.0434 0.5669 0.9993
2.000 0.4741 0.01116 0.00575 -0.0442 0.5335 0.9993
2.250 0.5038 0.01128 0.00580 -0.0447 0.5166 0.9993
2.500 0.5334 0.01141 0.00585 -0.0451 0.4991 0.9993
2.750 0.5629 0.01155 0.00591 -0.0455 0.4808 0.9993
3.000 0.5925 0.01170 0.00598 -0.0460 0.4621 0.9993
3.250 0.6220 0.01187 0.00607 -0.0464 0.4431 0.9993
3.500 0.6514 0.01205 0.00617 -0.0468 0.4241 0.9993
3.750 0.6808 0.01224 0.00628 -0.0473 0.4051 0.9993
4.000 0.7102 0.01244 0.00641 -0.0477 0.3860 0.9993
4.250 0.7395 0.01265 0.00656 -0.0482 0.3672 0.9993
4.500 0.7688 0.01287 0.00671 -0.0486 0.3485 0.9993
4.750 0.7980 0.01310 0.00688 -0.0491 0.3300 0.9993
5.000 0.8271 0.01334 0.00707 -0.0495 0.3119 0.9993
5.250 0.8562 0.01360 0.00727 -0.0500 0.2941 0.9993
5.500 0.8852 0.01387 0.00748 -0.0504 0.2768 0.9993
5.750 0.9142 0.01415 0.00771 -0.0509 0.2597 0.9993
6.000 0.9430 0.01444 0.00796 -0.0513 0.2431 0.9993
6.250 0.9718 0.01475 0.00822 -0.0518 0.2267 0.9993
6.500 1.0005 0.01508 0.00851 -0.0522 0.2107 0.9993
6.750 1.0291 0.01542 0.00881 -0.0526 0.1947 0.9993
7.000 1.0575 0.01579 0.00913 -0.0531 0.1795 0.9993
7.250 1.0859 0.01617 0.00948 -0.0535 0.1653 0.9993
7.500 1.1141 0.01658 0.00985 -0.0539 0.1519 0.9993
8.000 1.1700 0.01745 0.01065 -0.0547 0.1245 0.9993
8.250 1.1977 0.01793 0.01109 -0.0551 0.1112 0.9993
8.500 1.2253 0.01843 0.01156 -0.0554 0.1001 0.9993
8.750 1.2527 0.01892 0.01205 -0.0558 0.0892 0.9993
9.000 1.2798 0.01948 0.01257 -0.0561 0.0790 0.9993
9.250 1.3067 0.02003 0.01311 -0.0564 0.0689 0.9993
9.500 1.3334 0.02061 0.01368 -0.0567 0.0601 0.9993
9.750 1.3597 0.02123 0.01430 -0.0570 0.0527 0.9993
10.000 1.3859 0.02183 0.01493 -0.0572 0.0454 0.9993
10.250 1.4116 0.02253 0.01562 -0.0573 0.0372 0.9993
10.500 1.4358 0.02354 0.01657 -0.0574 0.0245 0.9993
10.750 1.4581 0.02495 0.01793 -0.0573 0.0145 0.9993
11.000 1.4809 0.02611 0.01916 -0.0571 0.0119 0.9993
11.250 1.5025 0.02738 0.02051 -0.0568 0.0106 0.9993
11.500 1.5239 0.02851 0.02177 -0.0565 0.0098 0.9993
11.750 1.5432 0.02987 0.02324 -0.0559 0.0092 0.9993
12.000 1.5583 0.03168 0.02517 -0.0550 0.0088 0.9993
12.250 1.5744 0.03312 0.02677 -0.0540 0.0085 0.9993
12.500 1.5878 0.03472 0.02851 -0.0528 0.0082 0.9993
12.750 1.5979 0.03648 0.03041 -0.0513 0.0079 0.9993
13.000 1.6037 0.03846 0.03252 -0.0494 0.0077 0.9993
13.250 1.6011 0.04083 0.03503 -0.0465 0.0075 0.9993
13.500 1.5865 0.04414 0.03848 -0.0432 0.0074 0.9993
13.750 1.5750 0.04835 0.04285 -0.0425 0.0073 0.9993
14.000 1.5635 0.05340 0.04806 -0.0434 0.0072 0.9993
14.250 1.5508 0.05912 0.05394 -0.0451 0.0072 0.9993
14.500 1.5365 0.06530 0.06027 -0.0472 0.0071 0.9993
14.750 1.5211 0.07175 0.06687 -0.0495 0.0071 0.9993
15.000 1.5050 0.07834 0.07361 -0.0519 0.0071 0.9993
15.250 1.4882 0.08508 0.08050 -0.0543 0.0071 0.9993
15.500 1.4713 0.09191 0.08745 -0.0569 0.0071 0.9993
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Polar data table (+)
Polar graphs
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