NASA/LANGLEY RC-SC2 AIRFOIL (rcsc2-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/LANGLEY RC-SC2 AIRFOIL (rcsc2-il) Reynolds number: 50,000 Max Cl/Cd: 24.06 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rcsc2-il-50000.txt Download as CSV file: xf-rcsc2-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY RC-SC2 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5028 0.09736 0.08974 0.0015 1.0000 0.3794
-7.500 -0.4858 0.09112 0.08358 0.0043 1.0000 0.4149
-6.750 -0.6711 0.06249 0.05431 -0.0191 1.0000 0.1772
-6.500 -0.6656 0.05697 0.04840 -0.0180 1.0000 0.1585
-6.250 -0.6559 0.05287 0.04417 -0.0165 1.0000 0.1521
-6.000 -0.6530 0.04859 0.03908 -0.0141 1.0000 0.1425
-5.750 -0.6397 0.04531 0.03555 -0.0124 1.0000 0.1403
-5.500 -0.6260 0.04238 0.03225 -0.0105 1.0000 0.1396
-5.250 -0.6104 0.03977 0.02922 -0.0086 1.0000 0.1404
-5.000 -0.5924 0.03736 0.02639 -0.0069 1.0000 0.1416
-4.750 -0.5721 0.03510 0.02370 -0.0053 1.0000 0.1428
-4.500 -0.5500 0.03290 0.02118 -0.0040 1.0000 0.1452
-4.250 -0.5272 0.03108 0.01938 -0.0030 1.0000 0.1520
-4.000 -0.5032 0.02958 0.01748 -0.0017 1.0000 0.1599
-3.750 -0.4773 0.02780 0.01582 -0.0010 1.0000 0.1703
-3.500 -0.4508 0.02632 0.01436 -0.0002 1.0000 0.1881
-3.250 -0.4226 0.02479 0.01301 0.0004 1.0000 0.2170
-3.000 -0.3956 0.02297 0.01162 0.0010 1.0000 0.2799
-2.750 -0.1276 0.02244 0.01304 -0.0306 1.0000 1.0000
-2.500 -0.1212 0.02197 0.01243 -0.0282 1.0000 1.0000
-2.250 -0.1144 0.02157 0.01191 -0.0255 1.0000 1.0000
-2.000 -0.1075 0.02123 0.01146 -0.0227 1.0000 1.0000
-1.750 -0.1004 0.02095 0.01108 -0.0199 1.0000 1.0000
-1.500 -0.0929 0.02072 0.01075 -0.0170 1.0000 1.0000
-1.250 -0.0852 0.02052 0.01047 -0.0140 1.0000 1.0000
-1.000 -0.0771 0.02037 0.01023 -0.0110 1.0000 1.0000
-0.750 -0.0684 0.02025 0.01004 -0.0081 1.0000 1.0000
-0.500 -0.0592 0.02017 0.00989 -0.0053 1.0000 1.0000
-0.250 -0.0492 0.02013 0.00979 -0.0026 1.0000 1.0000
0.000 -0.0385 0.02013 0.00973 0.0001 1.0000 1.0000
0.250 -0.0270 0.02016 0.00971 0.0025 1.0000 1.0000
0.500 -0.0149 0.02023 0.00974 0.0049 1.0000 1.0000
0.750 -0.0021 0.02034 0.00982 0.0071 1.0000 1.0000
1.000 0.0115 0.02049 0.00995 0.0091 1.0000 1.0000
1.250 0.0259 0.02069 0.01013 0.0109 1.0000 1.0000
1.500 0.0410 0.02093 0.01038 0.0126 1.0000 1.0000
1.750 0.0567 0.02121 0.01068 0.0140 1.0000 1.0000
2.000 0.0728 0.02155 0.01105 0.0153 1.0000 1.0000
2.250 0.0892 0.02194 0.01149 0.0165 1.0000 1.0000
2.500 0.1057 0.02239 0.01200 0.0175 1.0000 1.0000
2.750 0.1221 0.02291 0.01260 0.0184 1.0000 1.0000
3.000 0.1383 0.02351 0.01329 0.0191 1.0000 1.0000
3.250 0.1540 0.02420 0.01410 0.0197 1.0000 1.0000
3.500 0.1779 0.02513 0.01519 0.0184 0.9964 1.0000
3.750 0.3345 0.02597 0.01679 -0.0048 0.9229 1.0000
4.000 0.4938 0.02084 0.01278 -0.0178 0.7648 1.0000
4.250 0.5494 0.02283 0.01185 -0.0160 0.3461 1.0000
4.500 0.5771 0.02493 0.01328 -0.0155 0.2719 1.0000
4.750 0.6025 0.02652 0.01467 -0.0146 0.2266 1.0000
5.000 0.6282 0.02820 0.01621 -0.0138 0.1965 1.0000
5.250 0.6536 0.03000 0.01790 -0.0130 0.1765 1.0000
5.500 0.6770 0.03185 0.01989 -0.0117 0.1626 1.0000
5.750 0.6996 0.03401 0.02222 -0.0105 0.1540 1.0000
6.000 0.7202 0.03589 0.02426 -0.0090 0.1460 1.0000
6.250 0.7399 0.03836 0.02686 -0.0075 0.1412 1.0000
6.500 0.7558 0.04100 0.03000 -0.0053 0.1395 1.0000
6.750 0.7693 0.04384 0.03327 -0.0029 0.1383 1.0000
7.000 0.7801 0.04683 0.03667 -0.0005 0.1372 1.0000
7.250 0.7881 0.05004 0.04028 0.0020 0.1368 1.0000
7.500 0.7935 0.05355 0.04416 0.0044 0.1372 1.0000
7.750 0.7976 0.05739 0.04830 0.0066 0.1388 1.0000
8.000 0.8053 0.06144 0.05251 0.0082 0.1412 1.0000
8.250 0.7789 0.06774 0.05950 0.0107 0.1520 1.0000
8.500 0.7968 0.07257 0.06426 0.0110 0.1575 1.0000
8.750 0.6071 0.10362 0.09591 -0.0208 0.3745 1.0000
9.000 0.6009 0.10651 0.09873 -0.0203 0.3593 1.0000
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Polar data table (+)
Polar graphs
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