SC(2)-0714 Supercritical airfoil (coordinates from Raymer w/ one correction) (nasasc2-0714-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: SC(2)-0714 Supercritical airfoil (coordinates from Raymer w/ one correction) (nasasc2-0714-il) Reynolds number: 50,000 Max Cl/Cd: 24.55 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nasasc2-0714-il-50000.txt Download as CSV file: xf-nasasc2-0714-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: SC(2)-0714 Supercritical airfoil (coordinates fr
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5741 0.09717 0.08906 -0.0376 1.0000 0.2053
-10.000 -0.5599 0.09380 0.08569 -0.0363 1.0000 0.2026
-9.750 -0.6432 0.08046 0.07248 -0.0416 1.0000 0.1832
-9.500 -0.7679 0.06836 0.06001 -0.0461 1.0000 0.1709
-9.250 -0.7707 0.06373 0.05523 -0.0461 1.0000 0.1695
-9.000 -0.7723 0.05900 0.05021 -0.0468 1.0000 0.1685
-8.750 -0.7686 0.05445 0.04524 -0.0482 1.0000 0.1689
-8.500 -0.7567 0.05035 0.04060 -0.0500 1.0000 0.1707
-8.250 -0.7389 0.04675 0.03665 -0.0512 1.0000 0.1732
-8.000 -0.7189 0.04415 0.03397 -0.0510 1.0000 0.1761
-7.750 -0.6971 0.04183 0.03146 -0.0512 1.0000 0.1807
-7.500 -0.6718 0.03944 0.02862 -0.0525 1.0000 0.1869
-7.250 -0.6484 0.03732 0.02641 -0.0523 1.0000 0.1926
-7.000 -0.6248 0.03570 0.02470 -0.0519 1.0000 0.1998
-6.750 -0.6005 0.03409 0.02296 -0.0516 1.0000 0.2094
-6.500 -0.5770 0.03280 0.02161 -0.0508 1.0000 0.2208
-6.250 -0.5566 0.03165 0.02063 -0.0488 1.0000 0.2332
-6.000 -0.5361 0.03064 0.01974 -0.0468 1.0000 0.2507
-5.750 -0.5151 0.02961 0.01884 -0.0451 1.0000 0.2746
-5.500 -0.4945 0.02843 0.01810 -0.0435 1.0000 0.3114
-5.250 -0.4746 0.02693 0.01773 -0.0419 1.0000 0.3908
-5.000 -0.4818 0.02874 0.02075 -0.0296 1.0000 0.4898
-4.750 -0.4778 0.03276 0.02480 -0.0188 1.0000 0.5843
-4.500 -0.4698 0.03585 0.02773 -0.0103 1.0000 0.6331
-4.250 -0.4651 0.03813 0.02994 -0.0008 1.0000 0.6606
-4.000 -0.4562 0.03963 0.03133 0.0064 1.0000 0.6908
-3.750 -0.4454 0.04049 0.03206 0.0121 1.0000 0.7215
-3.500 -0.4346 0.04092 0.03240 0.0185 1.0000 0.7476
-3.250 -0.4227 0.04085 0.03223 0.0232 1.0000 0.7757
-3.000 -0.4111 0.04052 0.03179 0.0273 1.0000 0.8042
-2.750 -0.3975 0.03992 0.03109 0.0315 1.0000 0.8346
-2.500 -0.3649 0.03894 0.02999 0.0335 1.0000 0.8744
-2.250 -0.2490 0.03775 0.02847 0.0199 1.0000 0.9305
-2.000 -0.1773 0.03664 0.02717 0.0108 1.0000 0.9546
-1.750 -0.1359 0.03584 0.02628 0.0065 1.0000 0.9677
-1.500 -0.0984 0.03519 0.02557 0.0027 1.0000 0.9773
-1.250 -0.0667 0.03470 0.02504 0.0000 1.0000 0.9848
-1.000 -0.0367 0.03433 0.02465 -0.0024 1.0000 0.9913
-0.750 -0.0099 0.03405 0.02437 -0.0042 1.0000 0.9964
-0.500 0.0094 0.03388 0.02422 -0.0047 1.0000 1.0000
-0.250 0.0136 0.03372 0.02409 -0.0023 1.0000 1.0000
0.000 0.0176 0.03359 0.02400 0.0000 1.0000 1.0000
0.250 0.0212 0.03349 0.02394 0.0024 1.0000 1.0000
0.500 0.0246 0.03341 0.02391 0.0048 1.0000 1.0000
0.750 0.0275 0.03336 0.02392 0.0072 1.0000 1.0000
1.000 0.0300 0.03334 0.02395 0.0096 1.0000 1.0000
1.250 0.0322 0.03334 0.02402 0.0120 1.0000 1.0000
1.500 0.0339 0.03337 0.02412 0.0144 1.0000 1.0000
1.750 0.0353 0.03343 0.02425 0.0167 1.0000 1.0000
2.000 0.0365 0.03352 0.02442 0.0188 1.0000 1.0000
2.250 0.0377 0.03366 0.02465 0.0209 1.0000 1.0000
2.500 0.0391 0.03387 0.02495 0.0227 1.0000 1.0000
2.750 0.0649 0.03485 0.02605 0.0199 0.9931 1.0000
3.000 0.1668 0.03705 0.02845 0.0048 0.9513 1.0000
3.250 0.2677 0.03751 0.02917 -0.0078 0.9037 1.0000
3.500 0.3751 0.03615 0.02815 -0.0188 0.8571 1.0000
3.750 0.4503 0.03382 0.02617 -0.0234 0.8121 1.0000
4.000 0.5433 0.02868 0.02149 -0.0263 0.7450 1.0000
4.250 0.6652 0.02710 0.01704 -0.0315 0.3420 1.0000
4.500 0.7021 0.02875 0.01818 -0.0332 0.2853 1.0000
4.750 0.7431 0.03027 0.01939 -0.0355 0.2528 1.0000
5.000 0.7748 0.03164 0.02070 -0.0363 0.2337 1.0000
5.250 0.8029 0.03310 0.02202 -0.0366 0.2195 1.0000
5.500 0.8211 0.03435 0.02353 -0.0351 0.2098 1.0000
5.750 0.8424 0.03596 0.02511 -0.0344 0.2011 1.0000
6.000 0.8550 0.03732 0.02677 -0.0320 0.1943 1.0000
6.250 0.8733 0.03899 0.02847 -0.0307 0.1885 1.0000
6.500 0.8855 0.04090 0.03059 -0.0286 0.1838 1.0000
6.750 0.8938 0.04269 0.03281 -0.0258 0.1794 1.0000
7.000 0.9079 0.04489 0.03531 -0.0242 0.1756 1.0000
7.250 0.9267 0.04738 0.03796 -0.0237 0.1722 1.0000
7.500 0.9459 0.05054 0.04123 -0.0235 0.1687 1.0000
7.750 0.9504 0.05354 0.04479 -0.0214 0.1669 1.0000
8.000 0.9542 0.05711 0.04885 -0.0196 0.1662 1.0000
8.250 0.9570 0.06120 0.05334 -0.0183 0.1668 1.0000
8.500 0.9579 0.06560 0.05809 -0.0172 0.1675 1.0000
8.750 0.9572 0.07027 0.06305 -0.0164 0.1682 1.0000
9.000 0.9580 0.07527 0.06827 -0.0162 0.1690 1.0000
9.250 0.8533 0.08438 0.07811 -0.0133 0.1829 1.0000
9.500 0.8654 0.09011 0.08389 -0.0150 0.1855 1.0000
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Polar data table (+)
Polar graphs
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