NASA SC(2)-0518 AIRFOIL (sc20518-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: NASA SC(2)-0518 AIRFOIL (sc20518-il) Reynolds number: 50,000 Max Cl/Cd: 26.02 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20518-il-50000.txt Download as CSV file: xf-sc20518-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0518 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.6573 0.08007 0.07115 -0.0524 1.0000 0.2153
-10.500 -0.7055 0.07269 0.06376 -0.0523 1.0000 0.2135
-10.250 -0.7662 0.06699 0.05804 -0.0491 1.0000 0.2112
-10.000 -0.8184 0.06230 0.05325 -0.0457 1.0000 0.2097
-9.750 -0.8516 0.05831 0.04907 -0.0429 1.0000 0.2095
-9.500 -0.8703 0.05487 0.04538 -0.0406 1.0000 0.2105
-9.250 -0.8802 0.05173 0.04190 -0.0388 1.0000 0.2126
-9.000 -0.8843 0.04874 0.03849 -0.0377 1.0000 0.2153
-8.750 -0.8690 0.04683 0.03668 -0.0362 1.0000 0.2196
-8.500 -0.8552 0.04512 0.03494 -0.0349 1.0000 0.2244
-8.250 -0.8437 0.04306 0.03264 -0.0341 1.0000 0.2295
-8.000 -0.8293 0.04118 0.03061 -0.0332 1.0000 0.2353
-7.750 -0.8117 0.03996 0.02947 -0.0318 1.0000 0.2424
-7.500 -0.7954 0.03828 0.02749 -0.0315 1.0000 0.2504
-7.250 -0.7765 0.03732 0.02681 -0.0294 1.0000 0.2590
-7.000 -0.7584 0.03606 0.02547 -0.0285 1.0000 0.2703
-6.750 -0.7400 0.03516 0.02471 -0.0269 1.0000 0.2833
-6.500 -0.7223 0.03432 0.02409 -0.0249 1.0000 0.2988
-6.250 -0.7050 0.03343 0.02340 -0.0232 1.0000 0.3192
-6.000 -0.6891 0.03261 0.02294 -0.0210 1.0000 0.3459
-5.750 -0.6749 0.03205 0.02296 -0.0182 1.0000 0.3846
-5.500 -0.6630 0.03290 0.02455 -0.0129 1.0000 0.4378
-5.250 -0.6495 0.03642 0.02849 -0.0045 1.0000 0.4797
-5.000 -0.6319 0.04011 0.03222 0.0023 1.0000 0.5181
-4.750 -0.6159 0.04298 0.03501 0.0075 1.0000 0.5534
-4.500 -0.5978 0.04627 0.03826 0.0140 1.0000 0.5749
-4.250 -0.5785 0.04903 0.04095 0.0198 1.0000 0.5964
-4.000 -0.5584 0.05121 0.04306 0.0249 1.0000 0.6182
-3.750 -0.5384 0.05280 0.04458 0.0291 1.0000 0.6403
-3.500 -0.5182 0.05392 0.04564 0.0328 1.0000 0.6624
-3.250 -0.4974 0.05474 0.04638 0.0359 1.0000 0.6849
-3.000 -0.4746 0.05535 0.04693 0.0385 1.0000 0.7084
-2.750 -0.4498 0.05584 0.04736 0.0407 1.0000 0.7347
-2.500 -0.4375 0.05595 0.04742 0.0436 1.0000 0.7617
-2.250 -0.3711 0.05646 0.04784 0.0404 1.0000 0.7995
-2.000 -0.3110 0.05611 0.04740 0.0360 1.0000 0.8354
-1.750 -0.2637 0.05522 0.04644 0.0324 1.0000 0.8644
-1.500 -0.2462 0.05444 0.04561 0.0325 1.0000 0.8831
-1.250 -0.2279 0.05361 0.04475 0.0323 1.0000 0.8978
-1.000 -0.2080 0.05283 0.04394 0.0315 1.0000 0.9105
-0.750 -0.1901 0.05213 0.04322 0.0310 1.0000 0.9211
-0.500 -0.1930 0.05166 0.04274 0.0338 1.0000 0.9272
-0.250 -0.1682 0.05108 0.04215 0.0319 1.0000 0.9359
0.000 -0.1708 0.05070 0.04176 0.0347 1.0000 0.9405
0.250 -0.1471 0.05032 0.04139 0.0329 1.0000 0.9471
0.500 -0.1444 0.05003 0.04110 0.0346 1.0000 0.9501
0.750 -0.1462 0.04975 0.04084 0.0371 1.0000 0.9526
1.000 -0.1312 0.04961 0.04071 0.0366 1.0000 0.9569
1.250 -0.1216 0.04953 0.04066 0.0370 1.0000 0.9601
1.500 -0.0641 0.05017 0.04134 0.0285 0.9852 0.9644
1.750 0.0287 0.05102 0.04226 0.0140 0.9596 0.9701
2.000 0.0972 0.05132 0.04265 0.0045 0.9346 0.9746
2.250 0.1647 0.05143 0.04284 -0.0041 0.9084 0.9784
2.500 0.2766 0.05059 0.04216 -0.0190 0.8743 0.9845
2.750 0.3298 0.04976 0.04145 -0.0235 0.8443 0.9870
3.000 0.4446 0.04702 0.03892 -0.0359 0.8138 0.9914
3.250 0.5571 0.04312 0.03529 -0.0469 0.7786 0.9973
3.500 0.6686 0.03769 0.03012 -0.0556 0.7471 1.0000
3.750 0.7182 0.03415 0.02670 -0.0548 0.7059 1.0000
4.000 0.7505 0.03134 0.02387 -0.0514 0.6431 1.0000
4.250 0.7725 0.02969 0.02161 -0.0466 0.5326 1.0000
4.500 0.7840 0.03023 0.02113 -0.0425 0.4396 1.0000
4.750 0.7982 0.03135 0.02162 -0.0402 0.3858 1.0000
5.000 0.8173 0.03239 0.02229 -0.0389 0.3501 1.0000
5.250 0.8398 0.03337 0.02294 -0.0383 0.3244 1.0000
5.500 0.8602 0.03432 0.02378 -0.0374 0.3048 1.0000
5.750 0.8818 0.03530 0.02462 -0.0367 0.2889 1.0000
6.000 0.9002 0.03627 0.02559 -0.0355 0.2760 1.0000
6.250 0.9161 0.03738 0.02679 -0.0340 0.2653 1.0000
6.500 0.9387 0.03856 0.02776 -0.0336 0.2555 1.0000
6.750 0.9464 0.03976 0.02930 -0.0308 0.2482 1.0000
7.000 0.9629 0.04095 0.03045 -0.0295 0.2407 1.0000
7.250 0.9717 0.04243 0.03211 -0.0270 0.2350 1.0000
7.500 0.9763 0.04387 0.03380 -0.0240 0.2299 1.0000
7.750 0.9879 0.04522 0.03516 -0.0220 0.2244 1.0000
8.000 0.9969 0.04696 0.03694 -0.0198 0.2201 1.0000
8.250 0.9874 0.04860 0.03897 -0.0148 0.2173 1.0000
8.500 0.9775 0.05030 0.04097 -0.0100 0.2148 1.0000
8.750 0.9666 0.05196 0.04287 -0.0052 0.2125 1.0000
9.000 0.9563 0.05357 0.04466 -0.0006 0.2103 1.0000
9.250 0.9573 0.05512 0.04625 0.0024 0.2072 1.0000
9.500 0.9676 0.05737 0.04846 0.0037 0.2039 1.0000
9.750 0.9469 0.06004 0.05150 0.0080 0.2031 1.0000
10.000 0.9266 0.06354 0.05537 0.0110 0.2027 1.0000
10.250 0.8992 0.06766 0.05982 0.0137 0.2027 1.0000
10.500 0.8683 0.07279 0.06524 0.0150 0.2033 1.0000
10.750 0.8383 0.07914 0.07181 0.0143 0.2040 1.0000
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Polar data table (+)
Polar graphs
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