NASA SC(2)-0714 AIRFOIL (sc20714-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: NASA SC(2)-0714 AIRFOIL (sc20714-il) Reynolds number: 50,000 Max Cl/Cd: 25.43 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20714-il-50000.txt Download as CSV file: xf-sc20714-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0714 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.6806 0.08160 0.07361 -0.0435 1.0000 0.1795
-9.750 -0.7107 0.07606 0.06804 -0.0434 1.0000 0.1755
-9.500 -0.7340 0.07057 0.06248 -0.0438 1.0000 0.1730
-9.250 -0.7581 0.06467 0.05636 -0.0450 1.0000 0.1704
-9.000 -0.7691 0.05926 0.05059 -0.0464 1.0000 0.1693
-8.750 -0.7660 0.05481 0.04578 -0.0476 1.0000 0.1703
-8.500 -0.7550 0.05076 0.04133 -0.0490 1.0000 0.1720
-8.250 -0.7379 0.04701 0.03711 -0.0506 1.0000 0.1739
-8.000 -0.7151 0.04368 0.03310 -0.0530 1.0000 0.1778
-7.750 -0.6947 0.04137 0.03089 -0.0524 1.0000 0.1829
-7.500 -0.6711 0.03924 0.02854 -0.0526 1.0000 0.1885
-7.250 -0.6447 0.03706 0.02598 -0.0536 1.0000 0.1958
-7.000 -0.6226 0.03551 0.02451 -0.0526 1.0000 0.2040
-6.750 -0.5977 0.03389 0.02270 -0.0524 1.0000 0.2132
-6.500 -0.5746 0.03265 0.02144 -0.0514 1.0000 0.2256
-6.250 -0.5543 0.03155 0.02051 -0.0494 1.0000 0.2387
-6.000 -0.5336 0.03055 0.01963 -0.0475 1.0000 0.2567
-5.750 -0.5141 0.02956 0.01889 -0.0453 1.0000 0.2803
-5.500 -0.4932 0.02837 0.01817 -0.0439 1.0000 0.3192
-5.250 -0.4743 0.02700 0.01802 -0.0418 1.0000 0.4103
-5.000 -0.4843 0.02934 0.02141 -0.0281 1.0000 0.4976
-4.750 -0.4790 0.03331 0.02534 -0.0177 1.0000 0.5865
-4.500 -0.4694 0.03617 0.02801 -0.0100 1.0000 0.6353
-4.250 -0.4641 0.03831 0.03008 -0.0008 1.0000 0.6619
-4.000 -0.4543 0.03970 0.03135 0.0058 1.0000 0.6931
-3.750 -0.4451 0.04069 0.03225 0.0130 1.0000 0.7208
-3.500 -0.4341 0.04105 0.03250 0.0182 1.0000 0.7506
-3.250 -0.4222 0.04105 0.03240 0.0233 1.0000 0.7797
-3.000 -0.4081 0.04065 0.03191 0.0281 1.0000 0.8098
-2.750 -0.3906 0.03995 0.03111 0.0317 1.0000 0.8425
-2.500 -0.3689 0.03905 0.03008 0.0340 1.0000 0.8769
-2.250 -0.2527 0.03784 0.02854 0.0204 1.0000 0.9311
-2.000 -0.1761 0.03674 0.02725 0.0104 1.0000 0.9574
-1.750 -0.1339 0.03595 0.02636 0.0060 1.0000 0.9698
-1.500 -0.0936 0.03528 0.02564 0.0017 1.0000 0.9791
-1.250 -0.0597 0.03479 0.02510 -0.0014 1.0000 0.9865
-1.000 -0.0320 0.03446 0.02475 -0.0034 1.0000 0.9930
-0.750 -0.0003 0.03418 0.02447 -0.0061 1.0000 0.9989
-0.500 0.0090 0.03399 0.02432 -0.0046 1.0000 1.0000
-0.250 0.0135 0.03383 0.02419 -0.0023 1.0000 1.0000
0.000 0.0176 0.03370 0.02410 0.0001 1.0000 1.0000
0.250 0.0215 0.03360 0.02404 0.0025 1.0000 1.0000
0.500 0.0250 0.03352 0.02401 0.0049 1.0000 1.0000
0.750 0.0281 0.03347 0.02402 0.0073 1.0000 1.0000
1.000 0.0308 0.03345 0.02405 0.0097 1.0000 1.0000
1.250 0.0331 0.03345 0.02412 0.0121 1.0000 1.0000
1.500 0.0350 0.03348 0.02423 0.0144 1.0000 1.0000
1.750 0.0365 0.03355 0.02436 0.0167 1.0000 1.0000
2.000 0.0378 0.03365 0.02455 0.0189 1.0000 1.0000
2.250 0.0390 0.03380 0.02479 0.0209 1.0000 1.0000
2.500 0.0404 0.03402 0.02510 0.0227 1.0000 1.0000
2.750 0.0589 0.03477 0.02597 0.0213 0.9951 1.0000
3.000 0.1673 0.03722 0.02862 0.0049 0.9534 1.0000
3.250 0.2741 0.03759 0.02926 -0.0085 0.9041 1.0000
3.500 0.3745 0.03610 0.02810 -0.0183 0.8559 1.0000
3.750 0.4634 0.03316 0.02555 -0.0242 0.8073 1.0000
4.000 0.6513 0.02561 0.01638 -0.0338 0.4163 1.0000
4.250 0.6671 0.02747 0.01729 -0.0316 0.3285 1.0000
4.500 0.7061 0.02904 0.01832 -0.0337 0.2790 1.0000
4.750 0.7421 0.03034 0.01950 -0.0352 0.2509 1.0000
5.000 0.7734 0.03167 0.02074 -0.0359 0.2325 1.0000
5.250 0.8008 0.03312 0.02222 -0.0360 0.2201 1.0000
5.500 0.8264 0.03469 0.02364 -0.0360 0.2093 1.0000
5.750 0.8405 0.03598 0.02528 -0.0337 0.2019 1.0000
6.000 0.8604 0.03756 0.02686 -0.0327 0.1950 1.0000
6.250 0.8728 0.03929 0.02884 -0.0304 0.1896 1.0000
6.500 0.8825 0.04094 0.03083 -0.0277 0.1847 1.0000
6.750 0.8988 0.04286 0.03290 -0.0263 0.1800 1.0000
7.000 0.9180 0.04542 0.03551 -0.0258 0.1752 1.0000
7.250 0.9254 0.04787 0.03851 -0.0234 0.1725 1.0000
7.500 0.9345 0.05085 0.04197 -0.0216 0.1705 1.0000
7.750 0.9416 0.05408 0.04565 -0.0200 0.1685 1.0000
8.000 0.9468 0.05756 0.04952 -0.0186 0.1668 1.0000
8.250 0.9464 0.06156 0.05393 -0.0170 0.1664 1.0000
8.500 0.9345 0.06642 0.05925 -0.0151 0.1685 1.0000
8.750 0.9209 0.07162 0.06478 -0.0139 0.1713 1.0000
9.000 0.9118 0.07687 0.07025 -0.0134 0.1737 1.0000
9.250 0.9169 0.08231 0.07579 -0.0141 0.1756 1.0000
9.500 0.7502 0.10712 0.10115 -0.0288 0.2261 1.0000
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Polar data table (+)
Polar graphs
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