NASA/LANGLEY RC08-64C AIRFOIL (rc0864c-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/LANGLEY RC08-64C AIRFOIL (rc0864c-il) Reynolds number: 100,000 Max Cl/Cd: 37.21 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rc0864c-il-100000.txt Download as CSV file: xf-rc0864c-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY RC08-64C AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5581 0.10302 0.09785 -0.0080 1.0000 0.0918
-8.500 -0.5699 0.09928 0.09419 -0.0143 1.0000 0.0943
-8.250 -0.5882 0.09532 0.09029 -0.0215 1.0000 0.0950
-8.000 -0.5662 0.09065 0.08566 -0.0160 1.0000 0.0988
-7.750 -0.5622 0.08723 0.08227 -0.0164 1.0000 0.1024
-7.500 -0.5683 0.08330 0.07834 -0.0201 1.0000 0.1064
-7.250 -0.5956 0.08135 0.07600 -0.0276 1.0000 0.1096
-7.000 -0.5707 0.07482 0.06983 -0.0238 1.0000 0.1131
-6.750 -0.5627 0.07164 0.06665 -0.0232 1.0000 0.1183
-6.500 -0.5718 0.06814 0.06285 -0.0262 1.0000 0.1258
-6.250 -0.5565 0.06427 0.05916 -0.0240 1.0000 0.1299
-6.000 -0.5586 0.06189 0.05643 -0.0246 1.0000 0.1413
-5.750 -0.5443 0.05783 0.05257 -0.0227 1.0000 0.1456
-5.500 -0.5399 0.05510 0.04960 -0.0219 1.0000 0.1585
-5.250 -0.5270 0.05219 0.04677 -0.0201 1.0000 0.1664
-5.000 -0.5184 0.04930 0.04382 -0.0186 1.0000 0.1794
-4.750 -0.5087 0.04670 0.04116 -0.0168 1.0000 0.1954
-4.500 -0.4981 0.04427 0.03869 -0.0149 1.0000 0.2138
-3.750 -0.4189 0.02967 0.02133 -0.0106 1.0000 0.0675
-3.500 -0.3954 0.02693 0.01801 -0.0086 1.0000 0.0582
-3.250 -0.3709 0.02506 0.01545 -0.0066 1.0000 0.0522
-3.000 -0.3468 0.02306 0.01337 -0.0056 1.0000 0.0506
-2.750 -0.3220 0.02147 0.01165 -0.0046 1.0000 0.0492
-2.500 -0.2973 0.02016 0.01024 -0.0035 1.0000 0.0485
-2.250 -0.2736 0.01918 0.00921 -0.0025 1.0000 0.0502
-2.000 -0.2504 0.01827 0.00830 -0.0014 1.0000 0.0527
-1.750 -0.2282 0.01739 0.00748 -0.0004 1.0000 0.0555
-1.500 -0.2053 0.01676 0.00681 0.0006 1.0000 0.0588
-1.250 -0.0636 0.01288 0.00629 -0.0178 1.0000 1.0000
-1.000 -0.0554 0.01287 0.00611 -0.0144 1.0000 1.0000
-0.750 -0.0471 0.01290 0.00599 -0.0112 1.0000 1.0000
-0.500 -0.0380 0.01296 0.00593 -0.0081 1.0000 1.0000
-0.250 -0.0279 0.01306 0.00591 -0.0053 1.0000 1.0000
0.000 -0.0165 0.01319 0.00594 -0.0028 1.0000 1.0000
0.250 -0.0034 0.01337 0.00602 -0.0006 1.0000 1.0000
0.500 0.0113 0.01358 0.00616 0.0011 1.0000 1.0000
0.750 0.0273 0.01384 0.00635 0.0026 1.0000 1.0000
1.000 0.0441 0.01413 0.00660 0.0038 1.0000 1.0000
1.250 0.0615 0.01448 0.00692 0.0047 1.0000 1.0000
1.500 0.0925 0.01491 0.00735 0.0030 0.9963 1.0000
1.750 0.1451 0.01540 0.00789 -0.0028 0.9864 1.0000
2.000 0.1966 0.01580 0.00838 -0.0082 0.9747 1.0000
2.250 0.2495 0.01607 0.00881 -0.0136 0.9607 1.0000
2.500 0.3911 0.01419 0.00744 -0.0319 0.9091 1.0000
2.750 0.4413 0.01287 0.00628 -0.0321 0.8435 1.0000
3.000 0.4622 0.01242 0.00519 -0.0264 0.6531 1.0000
3.250 0.4619 0.01556 0.00547 -0.0209 0.1200 1.0000
3.500 0.4797 0.01693 0.00637 -0.0189 0.0653 1.0000
3.750 0.5002 0.01771 0.00721 -0.0173 0.0578 1.0000
4.000 0.5195 0.01863 0.00817 -0.0154 0.0544 1.0000
4.250 0.5390 0.01955 0.00913 -0.0136 0.0514 1.0000
4.500 0.5576 0.02083 0.01029 -0.0120 0.0481 1.0000
4.750 0.5800 0.02189 0.01140 -0.0106 0.0459 1.0000
5.000 0.6038 0.02328 0.01283 -0.0094 0.0454 1.0000
5.250 0.6289 0.02493 0.01457 -0.0084 0.0457 1.0000
5.500 0.6544 0.02686 0.01662 -0.0074 0.0465 1.0000
5.750 0.6793 0.02919 0.01909 -0.0065 0.0476 1.0000
6.000 0.7030 0.03118 0.02173 -0.0045 0.0510 1.0000
6.250 0.7245 0.03425 0.02513 -0.0029 0.0545 1.0000
6.500 0.7439 0.03782 0.02941 -0.0004 0.0627 1.0000
8.250 0.8166 0.07791 0.07247 0.0077 0.1584 1.0000
8.500 0.7548 0.08064 0.07569 0.0042 0.1506 1.0000
8.750 0.8135 0.08524 0.08000 0.0087 0.1433 1.0000
9.000 0.7502 0.08899 0.08402 0.0042 0.1414 1.0000
9.250 0.7195 0.09578 0.09073 -0.0046 0.1361 1.0000
9.500 0.7340 0.09842 0.09340 -0.0020 0.1310 1.0000
9.750 0.7418 0.10304 0.09799 -0.0005 0.1279 1.0000
10.000 0.7079 0.10955 0.10437 -0.0110 0.1224 1.0000
10.250 0.7134 0.11311 0.10794 -0.0111 0.1179 1.0000
10.500 0.5935 0.10810 0.10320 0.0042 0.1283 1.0000
10.750 0.5529 0.11264 0.10765 -0.0022 0.1239 1.0000
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Polar data table (+)
Polar graphs
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