NACA/LANGLEY SYMMETRICAL (n0011sc-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: NACA/LANGLEY SYMMETRICAL (n0011sc-il) Reynolds number: 50,000 Max Cl/Cd: 22.28 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n0011sc-il-50000.txt Download as CSV file: xf-n0011sc-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA/LANGLEY SYMMETRICAL
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 -0.4993 0.10155 0.09365 -0.0004 1.0000 0.3934
-8.500 -0.5012 0.09861 0.09078 0.0010 1.0000 0.4082
-8.000 -0.7555 0.07027 0.06234 -0.0139 1.0000 0.1720
-7.750 -0.7990 0.06520 0.05673 -0.0076 1.0000 0.1593
-7.500 -0.7943 0.06129 0.05277 -0.0052 1.0000 0.1561
-7.250 -0.7993 0.05766 0.04891 -0.0014 1.0000 0.1536
-7.000 -0.8040 0.05424 0.04517 0.0028 1.0000 0.1518
-6.750 -0.8054 0.05111 0.04170 0.0069 1.0000 0.1513
-6.500 -0.8034 0.04812 0.03834 0.0108 1.0000 0.1509
-6.250 -0.7976 0.04533 0.03519 0.0144 1.0000 0.1511
-6.000 -0.7888 0.04270 0.03218 0.0177 1.0000 0.1518
-5.750 -0.7778 0.04047 0.02958 0.0208 1.0000 0.1549
-5.500 -0.7658 0.03840 0.02703 0.0240 1.0000 0.1586
-5.250 -0.7484 0.03613 0.02450 0.0261 1.0000 0.1628
-5.000 -0.7276 0.03438 0.02268 0.0276 1.0000 0.1700
-4.750 -0.7075 0.03266 0.02061 0.0294 1.0000 0.1784
-4.500 -0.6830 0.03107 0.01898 0.0303 1.0000 0.1898
-4.250 -0.6565 0.02955 0.01745 0.0309 1.0000 0.2056
-4.000 -0.6264 0.02812 0.01600 0.0310 1.0000 0.2281
-3.750 -0.5866 0.02647 0.01470 0.0291 1.0000 0.2681
-3.500 -0.2455 0.02955 0.02017 -0.0133 1.0000 0.9623
-3.250 -0.1356 0.02851 0.01853 -0.0307 1.0000 1.0000
-3.000 -0.1273 0.02787 0.01777 -0.0286 1.0000 1.0000
-2.750 -0.1183 0.02733 0.01711 -0.0265 1.0000 1.0000
-2.500 -0.1087 0.02687 0.01656 -0.0243 1.0000 1.0000
-2.250 -0.0987 0.02647 0.01607 -0.0220 1.0000 1.0000
-2.000 -0.0884 0.02614 0.01565 -0.0197 1.0000 1.0000
-1.750 -0.0778 0.02585 0.01530 -0.0173 1.0000 1.0000
-1.500 -0.0670 0.02561 0.01500 -0.0149 1.0000 1.0000
-1.250 -0.0561 0.02541 0.01475 -0.0124 1.0000 1.0000
-1.000 -0.0450 0.02526 0.01456 -0.0100 1.0000 1.0000
-0.750 -0.0338 0.02514 0.01440 -0.0075 1.0000 1.0000
-0.500 -0.0226 0.02505 0.01430 -0.0050 1.0000 1.0000
-0.250 -0.0113 0.02500 0.01423 -0.0025 1.0000 1.0000
0.000 0.0000 0.02498 0.01421 0.0000 1.0000 1.0000
0.250 0.0113 0.02500 0.01423 0.0025 1.0000 1.0000
0.500 0.0226 0.02505 0.01429 0.0050 1.0000 1.0000
0.750 0.0339 0.02513 0.01440 0.0075 1.0000 1.0000
1.000 0.0450 0.02525 0.01455 0.0100 1.0000 1.0000
1.250 0.0561 0.02541 0.01475 0.0124 1.0000 1.0000
1.500 0.0670 0.02560 0.01500 0.0149 1.0000 1.0000
1.750 0.0779 0.02584 0.01529 0.0173 1.0000 1.0000
2.000 0.0884 0.02613 0.01564 0.0197 1.0000 1.0000
2.250 0.0987 0.02646 0.01606 0.0220 1.0000 1.0000
2.500 0.1088 0.02686 0.01654 0.0243 1.0000 1.0000
2.750 0.1183 0.02732 0.01710 0.0265 1.0000 1.0000
3.000 0.1273 0.02786 0.01775 0.0286 1.0000 1.0000
3.250 0.1357 0.02850 0.01851 0.0306 1.0000 1.0000
3.500 0.2341 0.02954 0.02011 0.0153 0.9659 1.0000
3.750 0.5866 0.02647 0.01470 -0.0291 0.2681 1.0000
4.000 0.6259 0.02809 0.01599 -0.0309 0.2285 1.0000
4.250 0.6562 0.02954 0.01745 -0.0309 0.2053 1.0000
4.500 0.6829 0.03107 0.01898 -0.0303 0.1897 1.0000
4.750 0.7075 0.03267 0.02061 -0.0294 0.1783 1.0000
5.000 0.7276 0.03437 0.02267 -0.0276 0.1701 1.0000
5.250 0.7484 0.03615 0.02451 -0.0261 0.1627 1.0000
5.500 0.7660 0.03841 0.02702 -0.0240 0.1588 1.0000
5.750 0.7777 0.04048 0.02958 -0.0208 0.1550 1.0000
6.000 0.7887 0.04270 0.03218 -0.0177 0.1518 1.0000
6.250 0.7976 0.04533 0.03518 -0.0144 0.1510 1.0000
6.500 0.8033 0.04814 0.03836 -0.0108 0.1508 1.0000
6.750 0.8057 0.05106 0.04163 -0.0070 0.1509 1.0000
7.000 0.8044 0.05417 0.04508 -0.0029 0.1513 1.0000
7.250 0.7990 0.05767 0.04891 0.0014 0.1533 1.0000
7.500 0.7941 0.06128 0.05276 0.0052 0.1561 1.0000
7.750 0.7989 0.06520 0.05673 0.0076 0.1593 1.0000
8.000 0.5078 0.09315 0.08544 -0.0043 0.4364 1.0000
8.250 0.5054 0.09586 0.08809 -0.0028 0.4240 1.0000
8.500 0.5027 0.09865 0.09082 -0.0011 0.4078 1.0000
8.750 0.5001 0.10159 0.09370 0.0004 0.3928 1.0000
9.000 0.5219 0.10608 0.09820 0.0011 0.3845 1.0000
9.250 0.5317 0.10927 0.10138 0.0025 0.3685 1.0000
9.500 0.5142 0.11100 0.10301 0.0038 0.3538 1.0000
9.750 0.5100 0.11375 0.10569 0.0048 0.3391 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA/LANGLEY SYMMETRICAL (n0011sc-il)