S4094 (root airfoil designed for and used on the E-flite UMX ASK-21 scale RC sailplane) (s4094-il) Xfoil prediction polar at RE=200,000 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: 200,000 Max Cl/Cd: 58.78 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4094-il-200000-n5.txt Download as CSV file: xf-s4094-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5983 0.10974 0.10629 0.0157 1.0004 0.0197
-9.250 -0.5962 0.10567 0.10224 0.0142 1.0004 0.0194
-9.000 -0.5961 0.10112 0.09772 0.0121 1.0004 0.0191
-8.750 -0.5976 0.09630 0.09293 0.0097 1.0004 0.0189
-8.500 -0.6017 0.09124 0.08790 0.0069 1.0004 0.0187
-8.250 -0.6068 0.08566 0.08236 0.0028 1.0004 0.0185
-8.000 -0.6066 0.07834 0.07503 -0.0045 1.0004 0.0185
-7.750 -0.6023 0.06900 0.06561 -0.0138 1.0004 0.0186
-7.500 -0.5945 0.05733 0.05366 -0.0230 1.0004 0.0186
-7.250 -0.5823 0.04630 0.04208 -0.0292 1.0004 0.0185
-7.000 -0.5626 0.03804 0.03310 -0.0330 1.0004 0.0182
-6.750 -0.5373 0.03251 0.02686 -0.0351 1.0004 0.0181
-6.500 -0.5095 0.02881 0.02257 -0.0364 1.0004 0.0183
-6.250 -0.4807 0.02615 0.01943 -0.0372 1.0004 0.0186
-6.000 -0.4515 0.02411 0.01701 -0.0379 1.0004 0.0189
-5.750 -0.4221 0.02249 0.01508 -0.0384 1.0004 0.0193
-5.500 -0.3926 0.02122 0.01358 -0.0389 1.0004 0.0198
-5.250 -0.3636 0.01984 0.01209 -0.0394 1.0004 0.0208
-5.000 -0.3344 0.01891 0.01112 -0.0399 1.0004 0.0219
-4.750 -0.3050 0.01799 0.01013 -0.0404 1.0004 0.0225
-4.500 -0.2754 0.01715 0.00921 -0.0408 1.0004 0.0232
-4.250 -0.2458 0.01641 0.00842 -0.0413 1.0004 0.0241
-4.000 -0.2161 0.01577 0.00772 -0.0418 1.0004 0.0251
-3.750 -0.1862 0.01523 0.00711 -0.0423 1.0004 0.0263
-3.500 -0.1530 0.01479 0.00665 -0.0436 0.9711 0.0289
-3.250 -0.1188 0.01458 0.00637 -0.0448 0.9276 0.0342
-3.000 -0.0901 0.01428 0.00608 -0.0447 0.8903 0.0485
-2.750 -0.0634 0.01402 0.00584 -0.0441 0.8588 0.0788
-2.500 -0.0367 0.01381 0.00566 -0.0437 0.8314 0.1139
-2.250 -0.0096 0.01355 0.00551 -0.0435 0.8072 0.1652
-2.000 0.0182 0.01319 0.00538 -0.0436 0.7850 0.2432
-1.500 0.0742 0.01248 0.00519 -0.0438 0.7459 0.4421
-1.250 0.1017 0.01209 0.00514 -0.0438 0.7282 0.5582
-1.000 0.1262 0.01158 0.00510 -0.0427 0.7118 0.7079
-0.750 0.1443 0.01096 0.00486 -0.0395 0.6967 0.8848
-0.500 0.1767 0.01053 0.00432 -0.0401 0.6805 0.9996
-0.250 0.2060 0.01064 0.00426 -0.0403 0.6655 0.9996
0.000 0.2353 0.01076 0.00422 -0.0406 0.6508 0.9996
0.250 0.2646 0.01088 0.00419 -0.0408 0.6365 0.9996
0.500 0.2939 0.01101 0.00418 -0.0411 0.6224 0.9996
0.750 0.3232 0.01113 0.00418 -0.0413 0.6084 0.9996
1.000 0.3525 0.01127 0.00420 -0.0416 0.5944 0.9996
1.250 0.3818 0.01140 0.00423 -0.0419 0.5803 0.9996
1.500 0.4111 0.01154 0.00427 -0.0422 0.5660 0.9996
1.750 0.4403 0.01169 0.00432 -0.0424 0.5515 0.9996
2.000 0.4695 0.01184 0.00439 -0.0427 0.5365 0.9996
2.250 0.4987 0.01200 0.00447 -0.0430 0.5212 0.9996
2.500 0.5279 0.01216 0.00456 -0.0433 0.5052 0.9996
2.750 0.5570 0.01233 0.00467 -0.0436 0.4884 0.9996
3.000 0.5861 0.01252 0.00478 -0.0438 0.4713 0.9996
3.250 0.6151 0.01272 0.00490 -0.0441 0.4536 0.9996
3.500 0.6441 0.01293 0.00506 -0.0444 0.4351 0.9996
3.750 0.6729 0.01316 0.00522 -0.0447 0.4163 0.9996
4.000 0.7017 0.01341 0.00540 -0.0450 0.3980 0.9996
4.250 0.7304 0.01368 0.00561 -0.0453 0.3798 0.9996
4.500 0.7591 0.01395 0.00585 -0.0456 0.3613 0.9996
4.750 0.7877 0.01425 0.00609 -0.0460 0.3433 0.9996
5.000 0.8162 0.01457 0.00636 -0.0463 0.3255 0.9996
5.250 0.8446 0.01489 0.00666 -0.0466 0.3083 0.9996
5.500 0.8729 0.01523 0.00697 -0.0469 0.2907 0.9996
5.750 0.9012 0.01559 0.00730 -0.0472 0.2736 0.9996
6.000 0.9292 0.01597 0.00765 -0.0475 0.2568 0.9996
6.250 0.9571 0.01637 0.00804 -0.0477 0.2406 0.9996
6.500 0.9849 0.01679 0.00845 -0.0480 0.2250 0.9996
6.750 1.0125 0.01723 0.00887 -0.0483 0.2101 0.9996
7.000 1.0399 0.01769 0.00933 -0.0485 0.1953 0.9996
7.250 1.0671 0.01817 0.00983 -0.0487 0.1810 0.9996
7.500 1.0941 0.01868 0.01034 -0.0489 0.1670 0.9996
7.750 1.1208 0.01921 0.01089 -0.0491 0.1533 0.9996
8.250 1.1734 0.02036 0.01209 -0.0494 0.1283 0.9996
8.500 1.1993 0.02096 0.01274 -0.0494 0.1172 0.9996
8.750 1.2248 0.02160 0.01343 -0.0495 0.1070 0.9996
9.000 1.2498 0.02230 0.01416 -0.0495 0.0970 0.9996
9.250 1.2741 0.02306 0.01494 -0.0494 0.0864 0.9996
9.500 1.2978 0.02387 0.01576 -0.0493 0.0752 0.9996
9.750 1.3210 0.02469 0.01661 -0.0492 0.0650 0.9996
10.000 1.3439 0.02551 0.01749 -0.0489 0.0563 0.9996
10.250 1.3658 0.02642 0.01846 -0.0486 0.0488 0.9996
10.500 1.3865 0.02743 0.01951 -0.0481 0.0421 0.9996
10.750 1.4066 0.02844 0.02063 -0.0476 0.0356 0.9996
11.000 1.4248 0.02962 0.02188 -0.0468 0.0289 0.9996
11.250 1.4403 0.03102 0.02333 -0.0458 0.0222 0.9996
11.500 1.4529 0.03259 0.02498 -0.0445 0.0172 0.9996
11.750 1.4623 0.03434 0.02681 -0.0428 0.0143 0.9996
12.000 1.4699 0.03606 0.02870 -0.0410 0.0128 0.9996
12.250 1.4729 0.03803 0.03082 -0.0388 0.0118 0.9996
12.500 1.4671 0.04036 0.03330 -0.0358 0.0113 0.9996
12.750 1.4604 0.04330 0.03640 -0.0340 0.0108 0.9996
13.000 1.4557 0.04658 0.03988 -0.0334 0.0105 0.9996
13.250 1.4498 0.05039 0.04392 -0.0337 0.0102 0.9996
13.500 1.4426 0.05472 0.04845 -0.0346 0.0100 0.9996
13.750 1.4337 0.05955 0.05347 -0.0360 0.0098 0.9996
14.000 1.4227 0.06485 0.05896 -0.0378 0.0096 0.9996
14.250 1.4099 0.07062 0.06491 -0.0400 0.0095 0.9996
14.500 1.3952 0.07682 0.07130 -0.0424 0.0094 0.9996
14.750 1.3790 0.08344 0.07809 -0.0451 0.0094 0.9996
15.000 1.3616 0.09042 0.08524 -0.0481 0.0093 0.9996
15.250 1.3433 0.09769 0.09268 -0.0513 0.0093 0.9996
15.500 1.3252 0.10523 0.10038 -0.0547 0.0093 0.9996
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Polar data table (+)
Polar graphs
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