NASA/LANGLEY RC10-64C AIRFOIL (rc1064c-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/LANGLEY RC10-64C AIRFOIL (rc1064c-il) Reynolds number: 50,000 Max Cl/Cd: 31.69 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rc1064c-il-50000.txt Download as CSV file: xf-rc1064c-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY RC10-64C 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5272 0.10420 0.09693 0.0000 1.0000 0.3189
-8.750 -0.5255 0.10105 0.09382 0.0007 1.0000 0.3357
-8.500 -0.5373 0.09880 0.09167 0.0013 1.0000 0.3545
-8.250 -0.5232 0.09477 0.08766 0.0027 1.0000 0.3732
-8.000 -0.5090 0.09160 0.08446 0.0048 1.0000 0.3993
-7.750 -0.5023 0.08897 0.08187 0.0074 1.0000 0.4322
-7.500 -0.4852 0.08579 0.07869 0.0102 1.0000 0.4694
-7.250 -0.4635 0.08261 0.07548 0.0126 1.0000 0.5071
-6.750 -0.6341 0.05815 0.05036 -0.0198 1.0000 0.1689
-6.500 -0.6287 0.05323 0.04505 -0.0183 1.0000 0.1532
-6.250 -0.6248 0.04899 0.04013 -0.0159 1.0000 0.1424
-6.000 -0.6133 0.04572 0.03656 -0.0139 1.0000 0.1411
-5.750 -0.6012 0.04278 0.03320 -0.0117 1.0000 0.1414
-5.500 -0.5866 0.03998 0.02996 -0.0096 1.0000 0.1418
-5.250 -0.5696 0.03728 0.02681 -0.0076 1.0000 0.1420
-5.000 -0.5505 0.03485 0.02386 -0.0057 1.0000 0.1436
-4.750 -0.5300 0.03279 0.02177 -0.0045 1.0000 0.1510
-4.500 -0.5085 0.03097 0.01951 -0.0029 1.0000 0.1591
-4.250 -0.4852 0.02924 0.01759 -0.0017 1.0000 0.1696
-4.000 -0.4611 0.02746 0.01571 -0.0007 1.0000 0.1876
-3.750 -0.4311 0.02523 0.01359 -0.0006 1.0000 0.2159
-3.500 -0.1314 0.02187 0.01253 -0.0373 1.0000 1.0000
-3.250 -0.1198 0.02145 0.01190 -0.0356 1.0000 1.0000
-3.000 -0.1089 0.02110 0.01136 -0.0336 1.0000 1.0000
-2.750 -0.0988 0.02081 0.01093 -0.0314 1.0000 1.0000
-2.500 -0.0894 0.02058 0.01057 -0.0289 1.0000 1.0000
-2.250 -0.0808 0.02039 0.01027 -0.0263 1.0000 1.0000
-2.000 -0.0731 0.02025 0.01003 -0.0235 1.0000 1.0000
-1.750 -0.0662 0.02015 0.00982 -0.0205 1.0000 1.0000
-1.500 -0.0599 0.02009 0.00968 -0.0174 1.0000 1.0000
-1.250 -0.0541 0.02007 0.00958 -0.0142 1.0000 1.0000
-1.000 -0.0484 0.02008 0.00952 -0.0109 1.0000 1.0000
-0.750 -0.0426 0.02013 0.00950 -0.0077 1.0000 1.0000
-0.500 -0.0363 0.02021 0.00951 -0.0046 1.0000 1.0000
-0.250 -0.0294 0.02032 0.00955 -0.0017 1.0000 1.0000
0.000 -0.0216 0.02048 0.00964 0.0011 1.0000 1.0000
0.250 -0.0129 0.02067 0.00977 0.0036 1.0000 1.0000
0.500 -0.0034 0.02090 0.00995 0.0060 1.0000 1.0000
0.750 0.0070 0.02118 0.01018 0.0081 1.0000 1.0000
1.000 0.0185 0.02150 0.01046 0.0100 1.0000 1.0000
1.250 0.0309 0.02187 0.01080 0.0116 1.0000 1.0000
1.500 0.0442 0.02229 0.01120 0.0130 1.0000 1.0000
1.750 0.0581 0.02276 0.01167 0.0142 1.0000 1.0000
2.000 0.0724 0.02329 0.01221 0.0152 1.0000 1.0000
2.250 0.0871 0.02387 0.01281 0.0160 1.0000 1.0000
2.500 0.1019 0.02451 0.01348 0.0167 1.0000 1.0000
2.750 0.1168 0.02522 0.01423 0.0173 1.0000 1.0000
3.000 0.1317 0.02600 0.01506 0.0177 1.0000 1.0000
3.250 0.1882 0.02742 0.01666 0.0100 0.9833 1.0000
3.500 0.2546 0.02872 0.01819 0.0011 0.9580 1.0000
3.750 0.3274 0.02992 0.01972 -0.0081 0.9283 1.0000
4.000 0.3890 0.03042 0.02056 -0.0142 0.8928 1.0000
4.250 0.5005 0.02883 0.01965 -0.0256 0.8467 1.0000
4.500 0.6014 0.02511 0.01667 -0.0308 0.7878 1.0000
4.750 0.6441 0.02239 0.01425 -0.0265 0.7143 1.0000
5.000 0.6635 0.02094 0.01237 -0.0186 0.5562 1.0000
5.250 0.6604 0.02318 0.01267 -0.0110 0.3350 1.0000
5.500 0.6769 0.02559 0.01423 -0.0087 0.2542 1.0000
5.750 0.7032 0.02751 0.01589 -0.0079 0.2147 1.0000
6.000 0.7329 0.02946 0.01763 -0.0078 0.1926 1.0000
6.250 0.7612 0.03149 0.01962 -0.0075 0.1782 1.0000
6.500 0.7841 0.03327 0.02164 -0.0063 0.1662 1.0000
6.750 0.8072 0.03562 0.02427 -0.0052 0.1597 1.0000
7.000 0.8275 0.03798 0.02701 -0.0036 0.1547 1.0000
7.250 0.8495 0.04072 0.02967 -0.0029 0.1483 1.0000
7.500 0.8609 0.04321 0.03280 -0.0002 0.1450 1.0000
7.750 0.8727 0.04636 0.03646 0.0021 0.1440 1.0000
8.000 0.8813 0.04983 0.04039 0.0045 0.1442 1.0000
8.250 0.8859 0.05350 0.04450 0.0070 0.1443 1.0000
8.500 0.8868 0.05734 0.04874 0.0094 0.1444 1.0000
8.750 0.8844 0.06143 0.05317 0.0117 0.1448 1.0000
9.000 0.8814 0.06582 0.05782 0.0136 0.1461 1.0000
9.250 0.8659 0.07075 0.06310 0.0155 0.1510 1.0000
9.500 0.8259 0.07730 0.06992 0.0164 0.1592 1.0000
9.750 0.7721 0.08566 0.07833 0.0141 0.1742 1.0000
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Polar data table (+)
Polar graphs
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