S4094 (root airfoil designed for and used on the E-flite UMX ASK-21 scale RC sailplane) (s4094-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: S4094 (root airfoil designed for and used on the E-flite UMX ASK-21 scale RC sailplane) (s4094-il) Reynolds number: 50,000 Max Cl/Cd: 34.78 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4094-il-50000-n5.txt Download as CSV file: xf-s4094-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S4094 (root airfoil designed for and used on the
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5654 0.11884 0.11204 0.0106 1.0004 0.0702
-9.000 -0.5567 0.11440 0.10757 0.0100 1.0004 0.0642
-8.500 -0.5739 0.10192 0.09523 -0.0013 1.0004 0.0554
-8.250 -0.5701 0.09726 0.09060 -0.0037 1.0004 0.0551
-8.000 -0.5654 0.09237 0.08573 -0.0066 1.0004 0.0547
-7.750 -0.5597 0.08728 0.08063 -0.0099 1.0004 0.0541
-7.500 -0.5528 0.08192 0.07524 -0.0135 1.0004 0.0534
-7.250 -0.5444 0.07622 0.06947 -0.0175 1.0004 0.0524
-7.000 -0.5337 0.07018 0.06329 -0.0218 1.0004 0.0514
-6.750 -0.5199 0.06392 0.05680 -0.0261 1.0004 0.0505
-6.500 -0.5023 0.05767 0.05017 -0.0303 1.0004 0.0497
-6.250 -0.4805 0.05186 0.04388 -0.0338 1.0004 0.0492
-6.000 -0.4555 0.04674 0.03823 -0.0366 1.0004 0.0491
-5.750 -0.4281 0.04235 0.03327 -0.0387 1.0004 0.0495
-5.500 -0.3993 0.03878 0.02915 -0.0402 1.0004 0.0511
-5.250 -0.3693 0.03572 0.02545 -0.0414 1.0004 0.0540
-5.000 -0.3394 0.03306 0.02229 -0.0421 1.0004 0.0563
-4.750 -0.3110 0.03095 0.01999 -0.0426 1.0004 0.0586
-4.500 -0.2821 0.02910 0.01793 -0.0428 1.0004 0.0615
-4.250 -0.2532 0.02740 0.01598 -0.0427 1.0004 0.0655
-4.000 -0.2250 0.02598 0.01447 -0.0428 1.0004 0.0722
-3.750 -0.1969 0.02476 0.01318 -0.0428 1.0004 0.0840
-3.500 -0.1687 0.02355 0.01197 -0.0429 1.0004 0.1028
-3.250 -0.1402 0.02245 0.01107 -0.0435 1.0004 0.1469
-3.000 -0.1122 0.02129 0.01031 -0.0440 1.0004 0.2175
-2.750 -0.0851 0.02023 0.00975 -0.0444 1.0004 0.3157
-2.500 -0.0605 0.01924 0.00942 -0.0441 1.0004 0.4555
-2.250 -0.0420 0.01829 0.00929 -0.0418 1.0004 0.6316
-2.000 -0.0255 0.01742 0.00911 -0.0379 1.0004 0.8964
-1.750 -0.0027 0.01749 0.00897 -0.0380 1.0004 0.9996
-1.500 0.0317 0.01773 0.00884 -0.0402 0.9920 0.9996
-1.250 0.0781 0.01778 0.00852 -0.0444 0.9719 0.9996
-1.000 0.1222 0.01784 0.00826 -0.0481 0.9500 0.9996
-0.750 0.1652 0.01792 0.00806 -0.0513 0.9288 0.9996
-0.500 0.2036 0.01805 0.00795 -0.0534 0.9054 0.9996
-0.250 0.2390 0.01822 0.00788 -0.0547 0.8832 0.9996
0.000 0.2699 0.01844 0.00791 -0.0551 0.8596 0.9996
0.250 0.2990 0.01869 0.00796 -0.0549 0.8383 0.9996
0.500 0.3265 0.01895 0.00806 -0.0545 0.8164 0.9996
0.750 0.3535 0.01923 0.00817 -0.0539 0.7965 0.9996
1.000 0.3803 0.01951 0.00831 -0.0534 0.7769 0.9996
1.250 0.4071 0.01980 0.00848 -0.0529 0.7575 0.9996
1.500 0.4337 0.02008 0.00865 -0.0523 0.7389 0.9996
1.750 0.4604 0.02037 0.00883 -0.0517 0.7211 0.9996
2.000 0.4873 0.02067 0.00906 -0.0512 0.7026 0.9996
2.250 0.5144 0.02098 0.00930 -0.0509 0.6841 0.9996
2.500 0.5413 0.02128 0.00954 -0.0504 0.6660 0.9996
2.750 0.5683 0.02159 0.00981 -0.0500 0.6483 0.9996
3.000 0.5953 0.02190 0.01007 -0.0495 0.6305 0.9996
3.250 0.6225 0.02223 0.01039 -0.0493 0.6114 0.9996
3.500 0.6496 0.02256 0.01074 -0.0490 0.5927 0.9996
3.750 0.6765 0.02288 0.01104 -0.0486 0.5744 0.9996
4.000 0.7035 0.02323 0.01138 -0.0482 0.5557 0.9996
4.250 0.7305 0.02359 0.01178 -0.0480 0.5357 0.9996
4.500 0.7574 0.02395 0.01218 -0.0477 0.5165 0.9996
4.750 0.7843 0.02433 0.01256 -0.0474 0.4972 0.9996
5.000 0.8112 0.02475 0.01304 -0.0472 0.4764 0.9996
5.250 0.8378 0.02515 0.01345 -0.0469 0.4568 0.9996
5.500 0.8643 0.02562 0.01400 -0.0467 0.4364 0.9996
5.750 0.8906 0.02611 0.01453 -0.0464 0.4159 0.9996
6.250 0.9425 0.02724 0.01574 -0.0459 0.3758 0.9996
6.500 0.9680 0.02787 0.01644 -0.0456 0.3562 0.9996
6.750 0.9932 0.02856 0.01716 -0.0453 0.3373 0.9996
7.000 1.0181 0.02932 0.01804 -0.0451 0.3173 0.9996
7.250 1.0426 0.03013 0.01891 -0.0447 0.2989 0.9996
7.500 1.0665 0.03096 0.01981 -0.0444 0.2813 0.9996
7.750 1.0901 0.03192 0.02090 -0.0441 0.2634 0.9996
8.000 1.1130 0.03293 0.02204 -0.0437 0.2460 0.9996
8.250 1.1354 0.03401 0.02324 -0.0432 0.2299 0.9996
8.500 1.1570 0.03515 0.02453 -0.0427 0.2144 0.9996
8.750 1.1779 0.03640 0.02590 -0.0422 0.2001 0.9996
9.000 1.1978 0.03772 0.02736 -0.0416 0.1863 0.9996
9.250 1.2169 0.03915 0.02895 -0.0409 0.1735 0.9996
9.500 1.2348 0.04067 0.03063 -0.0401 0.1616 0.9996
9.750 1.2516 0.04225 0.03233 -0.0392 0.1508 0.9996
10.000 1.2676 0.04387 0.03409 -0.0382 0.1410 0.9996
10.250 1.2804 0.04587 0.03641 -0.0371 0.1310 0.9996
10.500 1.2926 0.04790 0.03863 -0.0359 0.1229 0.9996
10.750 1.3032 0.04987 0.04074 -0.0346 0.1153 0.9996
11.000 1.3085 0.05244 0.04364 -0.0331 0.1081 0.9996
11.250 1.3148 0.05454 0.04583 -0.0315 0.1020 0.9996
11.500 1.3134 0.05766 0.04929 -0.0297 0.0969 0.9996
11.750 1.3066 0.06066 0.05255 -0.0276 0.0924 0.9996
12.000 1.3066 0.06285 0.05466 -0.0260 0.0877 0.9996
12.250 1.2882 0.06764 0.05988 -0.0252 0.0851 0.9996
12.500 1.2709 0.07290 0.06547 -0.0257 0.0828 0.9996
12.750 1.2543 0.07843 0.07124 -0.0271 0.0805 0.9996
13.000 1.2579 0.08065 0.07335 -0.0270 0.0755 0.9996
13.250 1.2331 0.08822 0.08124 -0.0302 0.0748 0.9996
13.500 1.2061 0.09683 0.09006 -0.0344 0.0746 0.9996
13.750 1.1767 0.10664 0.10007 -0.0397 0.0749 0.9996
14.000 1.1449 0.11784 0.11141 -0.0461 0.0755 0.9996
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Polar data table (+)
Polar graphs
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