S4095 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4095-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| 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: 72.55 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4095-il-1000000-n5.txt Download as CSV file: xf-s4095-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.6788 0.14596 0.14438 0.0460 1.0007 0.0060
-11.000 -0.6763 0.14128 0.13970 0.0440 1.0007 0.0061
-9.500 -0.8605 0.03527 0.03240 -0.0220 1.0007 0.0074
-9.250 -0.8353 0.03191 0.02868 -0.0240 1.0007 0.0074
-9.000 -0.8084 0.02954 0.02604 -0.0254 1.0007 0.0075
-8.750 -0.7807 0.02767 0.02393 -0.0266 1.0007 0.0075
-8.500 -0.7525 0.02445 0.02029 -0.0283 1.0007 0.0077
-8.250 -0.7237 0.02240 0.01797 -0.0295 1.0007 0.0078
-8.000 -0.6947 0.02112 0.01653 -0.0303 1.0007 0.0080
-7.750 -0.6655 0.02015 0.01543 -0.0310 1.0007 0.0081
-7.500 -0.6362 0.01943 0.01464 -0.0316 1.0007 0.0082
-7.250 -0.6068 0.01880 0.01394 -0.0322 1.0007 0.0084
-7.000 -0.5774 0.01819 0.01326 -0.0328 1.0007 0.0086
-6.750 -0.5477 0.01750 0.01248 -0.0333 1.0007 0.0088
-6.500 -0.5180 0.01684 0.01173 -0.0339 1.0007 0.0090
-6.250 -0.4882 0.01623 0.01105 -0.0344 1.0007 0.0092
-6.000 -0.4583 0.01566 0.01041 -0.0350 1.0007 0.0095
-5.750 -0.4284 0.01516 0.00985 -0.0355 1.0007 0.0098
-5.500 -0.3985 0.01471 0.00934 -0.0360 1.0007 0.0100
-5.250 -0.3693 0.01465 0.00919 -0.0363 0.9453 0.0102
-5.000 -0.3453 0.01461 0.00896 -0.0351 0.8874 0.0104
-4.750 -0.3176 0.01446 0.00862 -0.0349 0.8461 0.0106
-4.500 -0.2887 0.01429 0.00828 -0.0351 0.8114 0.0107
-4.250 -0.2593 0.01412 0.00796 -0.0354 0.7813 0.0108
-4.000 -0.2294 0.01377 0.00746 -0.0359 0.7545 0.0112
-3.750 -0.1995 0.01354 0.00711 -0.0363 0.7305 0.0117
-3.500 -0.1697 0.01338 0.00685 -0.0368 0.7079 0.0122
-3.250 -0.1398 0.01326 0.00664 -0.0372 0.6871 0.0129
-3.000 -0.1099 0.01314 0.00644 -0.0377 0.6675 0.0135
-2.750 -0.0800 0.01305 0.00626 -0.0381 0.6495 0.0141
-2.500 -0.0501 0.01298 0.00610 -0.0385 0.6325 0.0147
-2.250 -0.0202 0.01290 0.00595 -0.0390 0.6163 0.0159
-2.000 0.0098 0.01282 0.00583 -0.0394 0.6012 0.0182
-1.750 0.0398 0.01269 0.00572 -0.0399 0.5869 0.0350
-1.500 0.0698 0.01257 0.00564 -0.0405 0.5724 0.0586
-1.250 0.0999 0.01245 0.00558 -0.0410 0.5584 0.0880
-1.000 0.1299 0.01236 0.00554 -0.0416 0.5448 0.1198
-0.750 0.1599 0.01224 0.00551 -0.0422 0.5308 0.1639
-0.500 0.1900 0.01215 0.00550 -0.0427 0.5164 0.2059
-0.250 0.2200 0.01207 0.00549 -0.0433 0.5017 0.2515
0.000 0.2502 0.01190 0.00552 -0.0441 0.4863 0.3366
0.250 0.2805 0.01164 0.00560 -0.0449 0.4707 0.4682
0.500 0.3107 0.01141 0.00569 -0.0457 0.4545 0.6021
0.750 0.3406 0.01123 0.00579 -0.0463 0.4379 0.7134
1.000 0.3676 0.01093 0.00594 -0.0461 0.4225 0.8709
1.250 0.3910 0.01038 0.00551 -0.0448 0.4071 0.9993
1.500 0.4209 0.01048 0.00553 -0.0452 0.3916 0.9993
1.750 0.4507 0.01060 0.00555 -0.0457 0.3743 0.9993
2.000 0.4804 0.01072 0.00559 -0.0462 0.3580 0.9993
2.250 0.5102 0.01084 0.00563 -0.0467 0.3425 0.9993
2.500 0.5399 0.01098 0.00568 -0.0471 0.3269 0.9993
2.750 0.5695 0.01111 0.00575 -0.0476 0.3124 0.9993
3.000 0.5992 0.01125 0.00582 -0.0481 0.2973 0.9993
3.250 0.6288 0.01140 0.00590 -0.0486 0.2828 0.9993
3.500 0.6583 0.01156 0.00599 -0.0490 0.2686 0.9993
3.750 0.6878 0.01173 0.00609 -0.0495 0.2541 0.9993
4.000 0.7173 0.01190 0.00620 -0.0500 0.2402 0.9993
4.250 0.7467 0.01209 0.00632 -0.0505 0.2260 0.9993
4.500 0.7761 0.01227 0.00645 -0.0509 0.2128 0.9993
4.750 0.8054 0.01247 0.00660 -0.0514 0.1994 0.9993
5.000 0.8347 0.01266 0.00674 -0.0518 0.1891 0.9993
5.250 0.8639 0.01287 0.00691 -0.0523 0.1769 0.9993
5.500 0.8930 0.01310 0.00709 -0.0528 0.1648 0.9993
6.000 0.9511 0.01358 0.00747 -0.0537 0.1424 0.9993
6.250 0.9800 0.01385 0.00770 -0.0541 0.1295 0.9993
6.500 1.0087 0.01419 0.00795 -0.0546 0.1146 0.9993
6.750 1.0374 0.01450 0.00821 -0.0550 0.1019 0.9993
7.000 1.0660 0.01482 0.00848 -0.0555 0.0907 0.9993
7.250 1.0946 0.01515 0.00877 -0.0559 0.0807 0.9993
7.500 1.1230 0.01548 0.00907 -0.0563 0.0722 0.9993
7.750 1.1512 0.01587 0.00940 -0.0567 0.0624 0.9993
8.000 1.1793 0.01629 0.00978 -0.0571 0.0527 0.9993
8.250 1.2073 0.01668 0.01015 -0.0575 0.0450 0.9993
8.500 1.2351 0.01715 0.01057 -0.0579 0.0365 0.9993
8.750 1.2627 0.01760 0.01100 -0.0582 0.0303 0.9993
9.000 1.2902 0.01809 0.01146 -0.0586 0.0244 0.9993
9.250 1.3173 0.01866 0.01201 -0.0589 0.0177 0.9993
9.500 1.3433 0.01955 0.01283 -0.0592 0.0074 0.9993
9.750 1.3699 0.02015 0.01345 -0.0594 0.0055 0.9993
10.000 1.3966 0.02067 0.01402 -0.0596 0.0049 0.9993
10.250 1.4230 0.02124 0.01463 -0.0598 0.0045 0.9993
10.500 1.4489 0.02188 0.01534 -0.0600 0.0040 0.9993
10.750 1.4745 0.02255 0.01608 -0.0601 0.0037 0.9993
11.000 1.5000 0.02315 0.01674 -0.0601 0.0036 0.9993
11.250 1.5250 0.02380 0.01745 -0.0602 0.0034 0.9993
11.500 1.5496 0.02448 0.01821 -0.0602 0.0033 0.9993
11.750 1.5736 0.02522 0.01902 -0.0601 0.0032 0.9993
12.000 1.5969 0.02602 0.01991 -0.0599 0.0031 0.9993
12.250 1.6195 0.02686 0.02083 -0.0597 0.0030 0.9993
12.500 1.6412 0.02776 0.02182 -0.0594 0.0029 0.9993
12.750 1.6619 0.02873 0.02287 -0.0589 0.0028 0.9993
13.000 1.6812 0.02979 0.02403 -0.0583 0.0027 0.9993
13.250 1.6989 0.03096 0.02529 -0.0576 0.0026 0.9993
13.500 1.7146 0.03226 0.02669 -0.0565 0.0025 0.9993
13.750 1.7272 0.03374 0.02830 -0.0552 0.0025 0.9993
14.000 1.7357 0.03549 0.03017 -0.0534 0.0024 0.9993
14.250 1.7380 0.03757 0.03240 -0.0510 0.0023 0.9993
14.500 1.7239 0.04037 0.03534 -0.0466 0.0023 0.9993
14.750 1.7100 0.04415 0.03928 -0.0444 0.0023 0.9993
15.000 1.6971 0.04892 0.04423 -0.0445 0.0023 0.9993
15.250 1.6837 0.05453 0.05001 -0.0459 0.0022 0.9993
15.750 1.6493 0.06800 0.06382 -0.0509 0.0022 0.9993
16.000 1.6275 0.07566 0.07165 -0.0538 0.0022 0.9993
16.250 1.6016 0.08418 0.08034 -0.0572 0.0022 0.9993
16.500 1.5752 0.09282 0.08914 -0.0607 0.0022 0.9993
16.750 1.5480 0.10177 0.09824 -0.0643 0.0022 0.9993
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Polar data table (+)
Polar graphs
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