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=9
| 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: 29.14 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4094-il-50000.txt Download as CSV file: xf-s4094-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5491 0.12184 0.11524 0.0208 1.0004 0.2148
-8.500 -0.5393 0.11737 0.11080 0.0208 1.0004 0.2222
-8.250 -0.5541 0.11560 0.10914 0.0180 1.0004 0.2311
-8.000 -0.5313 0.11020 0.10373 0.0195 1.0004 0.2406
-7.750 -0.5392 0.10710 0.10073 0.0179 1.0004 0.2490
-7.500 -0.5432 0.10438 0.09808 0.0170 1.0004 0.2607
-7.250 -0.5252 0.09966 0.09337 0.0182 1.0004 0.2717
-7.000 -0.5218 0.09599 0.08976 0.0178 1.0004 0.2832
-6.750 -0.5176 0.09235 0.08618 0.0170 1.0004 0.2971
-6.500 -0.5110 0.08869 0.08257 0.0166 1.0004 0.3127
-6.250 -0.5031 0.08513 0.07905 0.0164 1.0004 0.3308
-6.000 -0.5001 0.08171 0.07568 0.0151 1.0004 0.3540
-5.750 -0.4934 0.07865 0.07266 0.0152 1.0004 0.3828
-5.250 -0.4277 0.05932 0.05265 -0.0214 1.0004 0.2376
-5.000 -0.3636 0.04410 0.03569 -0.0401 1.0004 0.1351
-4.750 -0.3260 0.03896 0.02947 -0.0434 1.0004 0.1270
-4.500 -0.2937 0.03542 0.02543 -0.0447 1.0004 0.1263
-4.250 -0.2609 0.03239 0.02185 -0.0456 1.0004 0.1290
-4.000 -0.2315 0.03019 0.01958 -0.0460 1.0004 0.1387
-3.750 -0.2009 0.02791 0.01707 -0.0462 1.0004 0.1492
-3.500 -0.1707 0.02600 0.01497 -0.0461 1.0004 0.1710
-3.250 -0.1429 0.02413 0.01332 -0.0458 1.0004 0.2147
-3.000 -0.1161 0.02241 0.01209 -0.0454 1.0004 0.2978
-2.750 -0.0904 0.02040 0.01094 -0.0445 1.0004 0.4424
-2.500 -0.0830 0.01799 0.01038 -0.0379 1.0004 0.7340
-2.250 -0.0508 0.01700 0.00927 -0.0377 1.0004 0.9996
-2.000 -0.0253 0.01718 0.00899 -0.0381 1.0004 0.9996
-1.750 -0.0023 0.01748 0.00895 -0.0381 1.0004 0.9996
-1.500 0.0191 0.01794 0.00912 -0.0380 1.0004 0.9996
-1.250 0.0391 0.01854 0.00948 -0.0379 1.0004 0.9996
-1.000 0.0588 0.01926 0.01000 -0.0380 1.0004 0.9996
-0.750 0.0785 0.02009 0.01062 -0.0382 1.0004 0.9996
-0.500 0.0979 0.02100 0.01136 -0.0386 1.0004 0.9996
-0.250 0.1171 0.02198 0.01219 -0.0392 1.0004 0.9996
0.000 0.1361 0.02302 0.01311 -0.0398 1.0004 0.9996
0.250 0.1940 0.02341 0.01330 -0.0471 0.9855 0.9996
0.500 0.2552 0.02357 0.01332 -0.0547 0.9661 0.9996
0.750 0.3177 0.02358 0.01322 -0.0622 0.9470 0.9996
1.000 0.3829 0.02342 0.01300 -0.0697 0.9291 0.9996
1.250 0.4320 0.02349 0.01303 -0.0738 0.9072 0.9996
1.500 0.4765 0.02359 0.01310 -0.0765 0.8857 0.9996
1.750 0.5107 0.02393 0.01343 -0.0772 0.8625 0.9996
2.000 0.5417 0.02429 0.01377 -0.0769 0.8402 0.9996
2.250 0.5683 0.02480 0.01427 -0.0759 0.8170 0.9996
2.500 0.5941 0.02525 0.01470 -0.0745 0.7951 0.9996
2.750 0.6184 0.02583 0.01529 -0.0730 0.7722 0.9996
3.000 0.6425 0.02632 0.01577 -0.0713 0.7505 0.9996
3.250 0.6663 0.02689 0.01634 -0.0697 0.7281 0.9996
3.500 0.6902 0.02742 0.01689 -0.0680 0.7062 0.9996
3.750 0.7141 0.02795 0.01742 -0.0663 0.6847 0.9996
4.000 0.7383 0.02852 0.01801 -0.0649 0.6620 0.9996
4.250 0.7625 0.02896 0.01843 -0.0631 0.6415 0.9996
4.500 0.7870 0.02962 0.01918 -0.0620 0.6178 0.9996
4.750 0.8116 0.02999 0.01951 -0.0601 0.5977 0.9996
5.000 0.8363 0.03073 0.02035 -0.0593 0.5735 0.9996
5.250 0.8613 0.03108 0.02066 -0.0576 0.5532 0.9996
5.500 0.8862 0.03184 0.02156 -0.0568 0.5290 0.9996
5.750 0.9115 0.03219 0.02187 -0.0553 0.5086 0.9996
6.000 0.9363 0.03300 0.02280 -0.0545 0.4845 0.9996
6.250 0.9619 0.03337 0.02315 -0.0531 0.4642 0.9996
6.500 0.9864 0.03427 0.02420 -0.0524 0.4404 0.9996
6.750 1.0122 0.03474 0.02460 -0.0511 0.4202 0.9996
7.000 1.0361 0.03585 0.02588 -0.0505 0.3970 0.9996
7.250 1.0616 0.03653 0.02654 -0.0494 0.3767 0.9996
7.500 1.0849 0.03787 0.02805 -0.0488 0.3548 0.9996
7.750 1.1092 0.03892 0.02914 -0.0479 0.3346 0.9996
8.000 1.1335 0.04009 0.03030 -0.0470 0.3156 0.9996
8.250 1.1543 0.04198 0.03251 -0.0464 0.2959 0.9996
8.500 1.1765 0.04358 0.03422 -0.0456 0.2779 0.9996
8.750 1.1988 0.04517 0.03588 -0.0447 0.2611 0.9996
9.000 1.2207 0.04689 0.03767 -0.0439 0.2451 0.9996
9.250 1.2400 0.04914 0.04010 -0.0431 0.2306 0.9996
9.500 1.2569 0.05156 0.04279 -0.0422 0.2166 0.9996
9.750 1.2617 0.05587 0.04770 -0.0412 0.2063 0.9996
10.000 1.2693 0.05946 0.05159 -0.0401 0.1961 0.9996
10.250 1.2857 0.06196 0.05417 -0.0390 0.1855 0.9996
10.500 1.2639 0.06881 0.06164 -0.0377 0.1826 0.9996
10.750 1.2314 0.07633 0.06954 -0.0370 0.1823 0.9996
11.000 1.1867 0.08464 0.07802 -0.0369 0.1847 0.9996
11.250 1.1452 0.09384 0.08725 -0.0393 0.1866 0.9996
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Polar data table (+)
Polar graphs
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