NASA/LANGLEY RC10-64C AIRFOIL (rc1064c-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY RC10-64C AIRFOIL (rc1064c-il) Reynolds number: 500,000 Max Cl/Cd: 59.38 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rc1064c-il-500000-n5.txt Download as CSV file: xf-rc1064c-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.9440 0.04753 0.04456 -0.0525 1.0000 0.0110
-12.500 -0.9661 0.04327 0.04007 -0.0514 1.0000 0.0110
-12.250 -0.9798 0.04049 0.03711 -0.0486 1.0000 0.0111
-12.000 -0.9913 0.03836 0.03480 -0.0446 1.0000 0.0112
-11.750 -0.9962 0.03642 0.03269 -0.0410 1.0000 0.0114
-11.500 -0.9963 0.03451 0.03059 -0.0379 1.0000 0.0115
-11.250 -0.9935 0.03271 0.02859 -0.0350 1.0000 0.0118
-11.000 -0.9885 0.03099 0.02665 -0.0322 1.0000 0.0120
-10.750 -0.9810 0.02942 0.02488 -0.0295 1.0000 0.0123
-10.500 -0.9712 0.02803 0.02327 -0.0271 1.0000 0.0126
-10.250 -0.9600 0.02677 0.02182 -0.0247 1.0000 0.0129
-10.000 -0.9415 0.02548 0.02031 -0.0238 0.9990 0.0133
-9.750 -0.9187 0.02422 0.01884 -0.0237 0.9969 0.0135
-9.500 -0.8958 0.02310 0.01752 -0.0235 0.9947 0.0137
-9.250 -0.8766 0.02147 0.01568 -0.0227 0.9920 0.0141
-9.000 -0.8562 0.02031 0.01438 -0.0218 0.9883 0.0144
-8.500 -0.8112 0.01875 0.01266 -0.0206 0.9801 0.0151
-8.250 -0.7862 0.01811 0.01194 -0.0205 0.9771 0.0156
-8.000 -0.7597 0.01748 0.01123 -0.0206 0.9742 0.0161
-7.750 -0.7320 0.01682 0.01047 -0.0209 0.9714 0.0167
-7.500 -0.7028 0.01612 0.00967 -0.0215 0.9691 0.0172
-7.250 -0.6720 0.01545 0.00890 -0.0225 0.9668 0.0176
-7.000 -0.6397 0.01484 0.00820 -0.0238 0.9647 0.0180
-6.750 -0.6071 0.01416 0.00745 -0.0251 0.9629 0.0184
-6.250 -0.5423 0.01293 0.00613 -0.0278 0.9591 0.0200
-6.000 -0.5089 0.01251 0.00568 -0.0293 0.9574 0.0211
-5.750 -0.4758 0.01211 0.00524 -0.0306 0.9554 0.0223
-5.500 -0.4431 0.01175 0.00482 -0.0319 0.9533 0.0232
-5.250 -0.4110 0.01135 0.00439 -0.0330 0.9509 0.0246
-5.000 -0.3792 0.01103 0.00405 -0.0341 0.9475 0.0269
-4.750 -0.3500 0.01082 0.00380 -0.0345 0.9433 0.0295
-4.500 -0.3211 0.01063 0.00360 -0.0348 0.9394 0.0340
-4.250 -0.2958 0.01048 0.00346 -0.0343 0.9356 0.0403
-4.000 -0.2697 0.01033 0.00335 -0.0341 0.9320 0.0510
-3.750 -0.2447 0.01021 0.00327 -0.0335 0.9281 0.0626
-3.500 -0.2194 0.01011 0.00321 -0.0330 0.9243 0.0739
-3.250 -0.1950 0.00995 0.00312 -0.0323 0.9202 0.0873
-3.000 -0.1699 0.00983 0.00304 -0.0318 0.9161 0.1032
-2.500 -0.1243 0.00928 0.00286 -0.0299 0.8913 0.1761
-2.250 -0.0975 0.00920 0.00274 -0.0295 0.8752 0.1876
-2.000 -0.0707 0.00904 0.00253 -0.0291 0.8670 0.1936
-1.750 -0.0446 0.00883 0.00227 -0.0285 0.8604 0.1992
-1.500 -0.0196 0.00858 0.00199 -0.0278 0.8535 0.2042
-1.250 0.0067 0.00844 0.00179 -0.0274 0.8457 0.2073
-1.000 0.0334 0.00838 0.00169 -0.0271 0.8369 0.2105
-0.750 0.0602 0.00832 0.00163 -0.0268 0.8284 0.2142
-0.500 0.0862 0.00823 0.00160 -0.0265 0.8166 0.2199
-0.250 0.1107 0.00800 0.00155 -0.0258 0.8010 0.2838
0.000 0.1241 0.00679 0.00139 -0.0233 0.7836 0.5935
0.250 0.1450 0.00645 0.00137 -0.0218 0.7671 0.6923
0.500 0.1685 0.00633 0.00138 -0.0207 0.7506 0.7445
0.750 0.1934 0.00631 0.00140 -0.0199 0.7316 0.7734
1.000 0.2185 0.00636 0.00142 -0.0191 0.7079 0.7919
1.250 0.2437 0.00643 0.00145 -0.0184 0.6820 0.8062
1.500 0.2688 0.00653 0.00149 -0.0177 0.6561 0.8194
1.750 0.2945 0.00662 0.00155 -0.0172 0.6335 0.8316
2.000 0.3194 0.00676 0.00161 -0.0164 0.6031 0.8431
2.250 0.3421 0.00704 0.00170 -0.0153 0.5492 0.8539
2.500 0.3634 0.00745 0.00182 -0.0140 0.4726 0.8651
2.750 0.3855 0.00787 0.00199 -0.0129 0.4029 0.8757
3.000 0.4074 0.00838 0.00220 -0.0118 0.3249 0.8857
3.250 0.4301 0.00886 0.00241 -0.0110 0.2557 0.8958
3.500 0.4543 0.00924 0.00263 -0.0104 0.2093 0.9054
3.750 0.4786 0.00964 0.00286 -0.0098 0.1676 0.9146
4.000 0.5035 0.01002 0.00310 -0.0094 0.1311 0.9239
4.250 0.5293 0.01036 0.00334 -0.0091 0.1035 0.9318
4.500 0.5553 0.01070 0.00359 -0.0089 0.0833 0.9398
4.750 0.5822 0.01101 0.00385 -0.0089 0.0682 0.9465
5.000 0.6095 0.01134 0.00413 -0.0089 0.0564 0.9529
5.250 0.6361 0.01163 0.00441 -0.0088 0.0494 0.9589
5.500 0.6646 0.01197 0.00473 -0.0092 0.0442 0.9636
5.750 0.6921 0.01228 0.00506 -0.0093 0.0414 0.9690
6.000 0.7204 0.01259 0.00540 -0.0096 0.0391 0.9737
6.250 0.7493 0.01294 0.00576 -0.0102 0.0366 0.9779
6.500 0.7756 0.01337 0.00619 -0.0101 0.0340 0.9831
6.750 0.8053 0.01380 0.00666 -0.0109 0.0325 0.9868
7.000 0.8337 0.01417 0.00709 -0.0113 0.0314 0.9899
7.250 0.8610 0.01457 0.00754 -0.0115 0.0302 0.9932
7.500 0.8897 0.01500 0.00801 -0.0121 0.0290 0.9955
7.750 0.9180 0.01546 0.00850 -0.0126 0.0277 0.9979
8.000 0.9431 0.01602 0.00909 -0.0126 0.0263 1.0000
8.250 0.9592 0.01662 0.00973 -0.0105 0.0253 1.0000
8.500 0.9776 0.01704 0.01021 -0.0089 0.0248 1.0000
8.750 0.9957 0.01750 0.01073 -0.0072 0.0242 1.0000
9.000 1.0138 0.01799 0.01129 -0.0056 0.0236 1.0000
9.250 1.0321 0.01850 0.01187 -0.0041 0.0228 1.0000
9.500 1.0510 0.01898 0.01240 -0.0027 0.0221 1.0000
9.750 1.0702 0.01944 0.01291 -0.0014 0.0213 1.0000
10.000 1.0885 0.01999 0.01348 -0.0001 0.0206 1.0000
10.250 1.1042 0.02079 0.01434 0.0016 0.0198 1.0000
10.500 1.1215 0.02147 0.01510 0.0031 0.0192 1.0000
10.750 1.1396 0.02204 0.01578 0.0044 0.0187 1.0000
11.000 1.1568 0.02267 0.01650 0.0058 0.0181 1.0000
11.250 1.1730 0.02328 0.01720 0.0074 0.0174 1.0000
11.500 1.1882 0.02386 0.01784 0.0090 0.0168 1.0000
11.750 1.2034 0.02441 0.01845 0.0107 0.0162 1.0000
12.000 1.2172 0.02509 0.01919 0.0124 0.0157 1.0000
12.250 1.2280 0.02603 0.02020 0.0144 0.0152 1.0000
12.500 1.2378 0.02712 0.02140 0.0163 0.0148 1.0000
12.750 1.2490 0.02811 0.02252 0.0180 0.0144 1.0000
13.000 1.2591 0.02920 0.02374 0.0197 0.0140 1.0000
13.250 1.2687 0.03031 0.02498 0.0213 0.0136 1.0000
13.500 1.2780 0.03148 0.02626 0.0227 0.0131 1.0000
13.750 1.2870 0.03267 0.02754 0.0240 0.0127 1.0000
14.000 1.2957 0.03393 0.02890 0.0252 0.0123 1.0000
14.250 1.3029 0.03537 0.03041 0.0262 0.0119 1.0000
14.500 1.3064 0.03722 0.03237 0.0272 0.0115 1.0000
14.750 1.3067 0.03948 0.03476 0.0280 0.0112 1.0000
15.000 1.3079 0.04181 0.03726 0.0285 0.0109 1.0000
15.250 1.3068 0.04450 0.04011 0.0288 0.0107 1.0000
15.500 1.3037 0.04756 0.04333 0.0286 0.0104 1.0000
15.750 1.2987 0.05107 0.04700 0.0279 0.0102 1.0000
16.000 1.2910 0.05513 0.05122 0.0268 0.0100 1.0000
16.250 1.2806 0.05985 0.05611 0.0249 0.0098 1.0000
16.500 1.2670 0.06540 0.06183 0.0223 0.0097 1.0000
16.750 1.2485 0.07221 0.06881 0.0187 0.0097 1.0000
17.000 1.2241 0.08057 0.07737 0.0140 0.0096 1.0000
17.250 1.1894 0.09146 0.08846 0.0078 0.0097 1.0000
17.500 1.1386 0.10618 0.10341 -0.0005 0.0100 1.0000
17.750 1.0576 0.12805 0.12550 -0.0121 0.0106 1.0000
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Polar data table (+)
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