S4095 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4095-il) Xfoil prediction polar at RE=1,000,000 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: 1,000,000 Max Cl/Cd: 75.59 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4095-il-1000000.txt Download as CSV file: xf-s4095-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.6556 0.10402 0.10253 0.0267 1.0007 0.0121
-8.500 -0.6604 0.09958 0.09810 0.0250 1.0007 0.0122
-8.250 -0.6637 0.09470 0.09324 0.0217 1.0007 0.0123
-8.000 -0.6604 0.08892 0.08745 0.0161 1.0007 0.0124
-7.750 -0.6657 0.05105 0.04910 -0.0166 1.0007 0.0144
-7.500 -0.6433 0.05056 0.04858 -0.0178 1.0007 0.0145
-7.250 -0.6202 0.04850 0.04643 -0.0197 1.0007 0.0147
-7.000 -0.5841 0.02263 0.01814 -0.0312 1.0007 0.0120
-6.750 -0.5541 0.02100 0.01630 -0.0320 1.0007 0.0121
-6.500 -0.5247 0.02020 0.01545 -0.0327 1.0007 0.0125
-6.250 -0.4947 0.01914 0.01426 -0.0334 1.0007 0.0128
-6.000 -0.4644 0.01787 0.01281 -0.0340 1.0007 0.0130
-5.750 -0.4341 0.01691 0.01171 -0.0346 1.0007 0.0133
-5.500 -0.4040 0.01617 0.01087 -0.0351 1.0007 0.0137
-5.250 -0.3738 0.01564 0.01025 -0.0356 1.0007 0.0141
-5.000 -0.3437 0.01489 0.00943 -0.0361 1.0007 0.0144
-4.750 -0.3136 0.01412 0.00865 -0.0368 1.0007 0.0148
-4.500 -0.2834 0.01364 0.00816 -0.0374 1.0007 0.0151
-4.250 -0.2531 0.01323 0.00774 -0.0379 1.0007 0.0155
-4.000 -0.2228 0.01286 0.00736 -0.0385 1.0007 0.0160
-3.750 -0.1924 0.01255 0.00703 -0.0390 1.0007 0.0165
-3.500 -0.1625 0.01264 0.00707 -0.0393 0.9473 0.0174
-3.250 -0.1390 0.01265 0.00692 -0.0379 0.8917 0.0182
-3.000 -0.1114 0.01259 0.00669 -0.0377 0.8508 0.0194
-2.750 -0.0824 0.01248 0.00644 -0.0378 0.8171 0.0209
-2.250 -0.0232 0.01219 0.00606 -0.0385 0.7595 0.0487
-2.000 0.0067 0.01202 0.00596 -0.0390 0.7346 0.0875
-1.750 0.0366 0.01188 0.00587 -0.0395 0.7117 0.1274
-1.500 0.0665 0.01173 0.00582 -0.0401 0.6911 0.1772
-1.250 0.0965 0.01158 0.00579 -0.0407 0.6716 0.2352
-1.000 0.1266 0.01141 0.00578 -0.0414 0.6534 0.3129
-0.750 0.1567 0.01117 0.00581 -0.0421 0.6358 0.4240
-0.500 0.1868 0.01078 0.00594 -0.0430 0.6195 0.6062
-0.250 0.2148 0.01035 0.00616 -0.0431 0.6045 0.8225
0.000 0.2369 0.00963 0.00572 -0.0413 0.5899 0.9993
0.250 0.2669 0.00970 0.00569 -0.0417 0.5745 0.9993
0.500 0.2969 0.00976 0.00567 -0.0422 0.5601 0.9993
0.750 0.3268 0.00984 0.00565 -0.0427 0.5452 0.9993
1.000 0.3567 0.00992 0.00563 -0.0431 0.5292 0.9993
1.250 0.3866 0.00999 0.00563 -0.0436 0.5139 0.9993
1.500 0.4165 0.01007 0.00564 -0.0440 0.4982 0.9993
1.750 0.4463 0.01016 0.00564 -0.0445 0.4814 0.9993
2.000 0.4761 0.01026 0.00566 -0.0450 0.4638 0.9993
2.250 0.5058 0.01037 0.00568 -0.0454 0.4457 0.9993
2.500 0.5355 0.01049 0.00571 -0.0459 0.4275 0.9993
2.750 0.5652 0.01062 0.00575 -0.0464 0.4092 0.9993
3.000 0.5948 0.01074 0.00580 -0.0468 0.3916 0.9993
3.250 0.6244 0.01088 0.00587 -0.0473 0.3742 0.9993
3.500 0.6540 0.01102 0.00594 -0.0478 0.3568 0.9993
3.750 0.6835 0.01117 0.00602 -0.0482 0.3398 0.9993
4.000 0.7130 0.01134 0.00611 -0.0487 0.3227 0.9993
4.250 0.7424 0.01151 0.00622 -0.0492 0.3059 0.9993
4.500 0.7718 0.01169 0.00634 -0.0496 0.2894 0.9993
4.750 0.8011 0.01188 0.00646 -0.0501 0.2734 0.9993
5.000 0.8304 0.01208 0.00661 -0.0506 0.2577 0.9993
5.250 0.8596 0.01229 0.00676 -0.0510 0.2423 0.9993
5.500 0.8888 0.01251 0.00692 -0.0515 0.2273 0.9993
5.750 0.9179 0.01275 0.00710 -0.0520 0.2124 0.9993
6.000 0.9469 0.01299 0.00729 -0.0524 0.1979 0.9993
6.250 0.9759 0.01326 0.00750 -0.0529 0.1828 0.9993
6.500 1.0047 0.01353 0.00772 -0.0533 0.1687 0.9993
6.750 1.0335 0.01381 0.00795 -0.0538 0.1557 0.9993
7.000 1.0622 0.01414 0.00821 -0.0542 0.1413 0.9993
7.250 1.0907 0.01448 0.00849 -0.0547 0.1275 0.9993
7.500 1.1192 0.01481 0.00877 -0.0551 0.1150 0.9993
7.750 1.1475 0.01518 0.00909 -0.0555 0.1030 0.9993
8.000 1.1757 0.01556 0.00942 -0.0559 0.0917 0.9993
8.250 1.2037 0.01598 0.00978 -0.0563 0.0803 0.9993
8.500 1.2317 0.01637 0.01014 -0.0567 0.0712 0.9993
8.750 1.2594 0.01682 0.01055 -0.0571 0.0623 0.9993
9.000 1.2871 0.01727 0.01096 -0.0575 0.0536 0.9993
9.250 1.3145 0.01774 0.01141 -0.0578 0.0459 0.9993
9.500 1.3417 0.01825 0.01189 -0.0581 0.0387 0.9993
9.750 1.3686 0.01882 0.01243 -0.0584 0.0309 0.9993
10.000 1.3946 0.01961 0.01314 -0.0587 0.0196 0.9993
10.500 1.4450 0.02150 0.01501 -0.0589 0.0073 0.9993
10.750 1.4705 0.02224 0.01582 -0.0590 0.0066 0.9993
11.000 1.4956 0.02299 0.01665 -0.0591 0.0061 0.9993
11.250 1.5195 0.02394 0.01768 -0.0590 0.0056 0.9993
11.500 1.5424 0.02500 0.01884 -0.0588 0.0052 0.9993
11.750 1.5659 0.02582 0.01975 -0.0587 0.0050 0.9993
12.000 1.5883 0.02676 0.02078 -0.0584 0.0049 0.9993
12.250 1.6096 0.02780 0.02192 -0.0581 0.0047 0.9993
12.500 1.6296 0.02892 0.02314 -0.0575 0.0046 0.9993
12.750 1.6480 0.03013 0.02446 -0.0569 0.0045 0.9993
13.000 1.6646 0.03145 0.02588 -0.0560 0.0044 0.9993
13.250 1.6788 0.03291 0.02746 -0.0548 0.0043 0.9993
13.500 1.6897 0.03456 0.02922 -0.0533 0.0042 0.9993
13.750 1.6959 0.03645 0.03124 -0.0513 0.0042 0.9993
14.000 1.6938 0.03875 0.03367 -0.0484 0.0041 0.9993
14.250 1.6762 0.04202 0.03710 -0.0443 0.0041 0.9993
14.500 1.6637 0.04622 0.04145 -0.0434 0.0041 0.9993
14.750 1.6521 0.05128 0.04667 -0.0442 0.0040 0.9993
15.000 1.6392 0.05709 0.05265 -0.0461 0.0040 0.9993
15.250 1.6233 0.06363 0.05935 -0.0485 0.0040 0.9993
15.500 1.6049 0.07073 0.06661 -0.0513 0.0040 0.9993
15.750 1.5846 0.07821 0.07425 -0.0542 0.0040 0.9993
16.000 1.5618 0.08615 0.08233 -0.0573 0.0040 0.9993
16.250 1.5382 0.09436 0.09069 -0.0605 0.0040 0.9993
16.500 1.5141 0.10269 0.09916 -0.0639 0.0040 0.9993
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Polar data table (+)
Polar graphs
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