NASA/LANGLEY RC10-64C AIRFOIL (rc1064c-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/LANGLEY RC10-64C AIRFOIL (rc1064c-il) Reynolds number: 1,000,000 Max Cl/Cd: 71.19 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rc1064c-il-1000000.txt Download as CSV file: xf-rc1064c-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.9354 0.06077 0.05871 -0.0439 1.0000 0.0109
-13.500 -0.9594 0.05207 0.04980 -0.0511 1.0000 0.0108
-13.250 -0.9838 0.04623 0.04376 -0.0534 1.0000 0.0108
-13.000 -1.0093 0.04163 0.03894 -0.0526 1.0000 0.0108
-12.750 -1.0339 0.03798 0.03507 -0.0494 1.0000 0.0109
-12.500 -1.0522 0.03549 0.03239 -0.0446 1.0000 0.0110
-12.250 -1.0613 0.03367 0.03043 -0.0400 1.0000 0.0111
-12.000 -1.0582 0.03228 0.02895 -0.0371 1.0000 0.0113
-11.750 -1.0510 0.03115 0.02773 -0.0346 1.0000 0.0114
-11.500 -1.0415 0.03015 0.02664 -0.0322 1.0000 0.0116
-11.250 -1.0315 0.02911 0.02549 -0.0299 1.0000 0.0118
-11.000 -1.0213 0.02805 0.02431 -0.0274 1.0000 0.0121
-10.750 -1.0112 0.02698 0.02312 -0.0249 1.0000 0.0123
-10.500 -1.0013 0.02588 0.02189 -0.0222 1.0000 0.0125
-10.250 -0.9913 0.02479 0.02065 -0.0194 1.0000 0.0128
-10.000 -0.9742 0.02367 0.01938 -0.0181 0.9996 0.0131
-9.750 -0.9492 0.02275 0.01832 -0.0182 0.9987 0.0135
-9.500 -0.9230 0.02209 0.01753 -0.0184 0.9977 0.0138
-9.250 -0.8963 0.02156 0.01689 -0.0187 0.9966 0.0140
-9.000 -0.8795 0.01839 0.01337 -0.0178 0.9953 0.0146
-8.750 -0.8526 0.01748 0.01240 -0.0182 0.9944 0.0150
-8.500 -0.8270 0.01684 0.01171 -0.0182 0.9927 0.0154
-8.250 -0.8000 0.01622 0.01103 -0.0184 0.9906 0.0159
-8.000 -0.7721 0.01561 0.01035 -0.0187 0.9885 0.0164
-7.750 -0.7435 0.01508 0.00975 -0.0192 0.9867 0.0170
-7.500 -0.7144 0.01451 0.00912 -0.0198 0.9851 0.0174
-7.250 -0.6895 0.01398 0.00852 -0.0193 0.9822 0.0177
-7.000 -0.6615 0.01354 0.00803 -0.0195 0.9796 0.0180
-6.750 -0.6360 0.01236 0.00674 -0.0194 0.9773 0.0188
-6.500 -0.6067 0.01171 0.00606 -0.0200 0.9754 0.0196
-6.250 -0.5781 0.01129 0.00562 -0.0204 0.9726 0.0204
-6.000 -0.5462 0.01092 0.00522 -0.0214 0.9700 0.0213
-5.750 -0.5106 0.01053 0.00480 -0.0233 0.9679 0.0223
-5.500 -0.4728 0.01016 0.00440 -0.0256 0.9658 0.0230
-5.250 -0.4382 0.00958 0.00377 -0.0273 0.9634 0.0248
-5.000 -0.4035 0.00924 0.00342 -0.0290 0.9610 0.0268
-4.750 -0.3692 0.00898 0.00314 -0.0306 0.9585 0.0289
-4.500 -0.3363 0.00865 0.00282 -0.0318 0.9555 0.0341
-4.250 -0.3066 0.00841 0.00260 -0.0324 0.9517 0.0432
-4.000 -0.2787 0.00824 0.00248 -0.0325 0.9473 0.0576
-3.750 -0.2515 0.00815 0.00243 -0.0324 0.9424 0.0713
-3.500 -0.2266 0.00808 0.00241 -0.0318 0.9371 0.0868
-3.250 -0.2022 0.00804 0.00244 -0.0311 0.9315 0.1061
-3.000 -0.1789 0.00795 0.00245 -0.0301 0.9258 0.1343
-2.750 -0.1538 0.00790 0.00256 -0.0295 0.9205 0.1758
-2.500 -0.1270 0.00797 0.00259 -0.0292 0.9160 0.1855
-2.250 -0.1010 0.00781 0.00246 -0.0287 0.9105 0.1937
-2.000 -0.0751 0.00762 0.00227 -0.0283 0.9045 0.2012
-1.750 -0.0483 0.00732 0.00202 -0.0282 0.8816 0.2072
-1.500 -0.0215 0.00708 0.00179 -0.0278 0.8723 0.2136
-1.000 0.0268 0.00646 0.00128 -0.0260 0.8555 0.2685
-0.750 0.0517 0.00631 0.00118 -0.0254 0.8454 0.3104
-0.500 0.0758 0.00606 0.00114 -0.0247 0.8346 0.3909
-0.250 0.0985 0.00567 0.00109 -0.0237 0.8218 0.5008
0.000 0.1186 0.00513 0.00103 -0.0222 0.8079 0.6479
0.250 0.1402 0.00480 0.00102 -0.0208 0.7931 0.7439
0.500 0.1638 0.00468 0.00103 -0.0197 0.7768 0.7957
0.750 0.1885 0.00466 0.00105 -0.0188 0.7592 0.8251
1.000 0.2139 0.00470 0.00107 -0.0182 0.7385 0.8434
1.250 0.2400 0.00475 0.00110 -0.0177 0.7193 0.8556
1.500 0.2658 0.00482 0.00114 -0.0171 0.6973 0.8669
1.750 0.2907 0.00495 0.00118 -0.0164 0.6654 0.8779
2.000 0.3151 0.00511 0.00124 -0.0155 0.6277 0.8884
2.250 0.3397 0.00530 0.00131 -0.0148 0.5881 0.8976
2.500 0.3639 0.00552 0.00139 -0.0140 0.5444 0.9068
2.750 0.3880 0.00578 0.00150 -0.0132 0.4946 0.9150
3.000 0.4114 0.00611 0.00163 -0.0123 0.4389 0.9233
3.250 0.4334 0.00660 0.00181 -0.0112 0.3559 0.9311
3.500 0.4555 0.00708 0.00202 -0.0102 0.2843 0.9389
3.750 0.4789 0.00755 0.00224 -0.0094 0.2213 0.9459
4.000 0.5018 0.00797 0.00245 -0.0085 0.1698 0.9537
4.250 0.5277 0.00837 0.00267 -0.0083 0.1292 0.9591
4.500 0.5526 0.00874 0.00290 -0.0078 0.0964 0.9656
4.750 0.5790 0.00909 0.00315 -0.0077 0.0723 0.9706
5.000 0.6078 0.00944 0.00341 -0.0081 0.0564 0.9745
5.250 0.6357 0.00974 0.00368 -0.0082 0.0491 0.9789
5.500 0.6632 0.01003 0.00394 -0.0083 0.0445 0.9829
5.750 0.6945 0.01041 0.00433 -0.0093 0.0404 0.9848
6.000 0.7271 0.01067 0.00461 -0.0105 0.0387 0.9866
6.250 0.7588 0.01097 0.00493 -0.0116 0.0366 0.9886
6.500 0.7903 0.01138 0.00533 -0.0127 0.0341 0.9914
6.750 0.8186 0.01193 0.00593 -0.0131 0.0319 0.9939
7.000 0.8519 0.01221 0.00624 -0.0146 0.0310 0.9951
7.250 0.8838 0.01255 0.00661 -0.0158 0.0298 0.9965
7.500 0.9152 0.01290 0.00697 -0.0169 0.0284 0.9979
7.750 0.9461 0.01329 0.00737 -0.0179 0.0270 0.9994
8.000 0.9649 0.01416 0.00830 -0.0165 0.0254 1.0000
8.250 0.9822 0.01452 0.00871 -0.0146 0.0249 1.0000
8.500 1.0011 0.01476 0.00898 -0.0129 0.0243 1.0000
8.750 1.0199 0.01504 0.00929 -0.0113 0.0236 1.0000
9.000 1.0384 0.01536 0.00965 -0.0096 0.0228 1.0000
9.250 1.0571 0.01570 0.01001 -0.0080 0.0221 1.0000
9.500 1.0760 0.01604 0.01036 -0.0065 0.0213 1.0000
9.750 1.0921 0.01665 0.01099 -0.0046 0.0203 1.0000
10.000 1.1057 0.01756 0.01198 -0.0023 0.0195 1.0000
10.250 1.1263 0.01787 0.01235 -0.0012 0.0191 1.0000
10.500 1.1466 0.01824 0.01278 0.0000 0.0186 1.0000
10.750 1.1671 0.01860 0.01317 0.0010 0.0179 1.0000
11.000 1.1877 0.01894 0.01354 0.0020 0.0172 1.0000
11.250 1.2080 0.01931 0.01393 0.0029 0.0165 1.0000
11.500 1.2238 0.02006 0.01471 0.0046 0.0158 1.0000
11.750 1.2346 0.02122 0.01599 0.0069 0.0151 1.0000
12.000 1.2524 0.02164 0.01648 0.0083 0.0148 1.0000
12.250 1.2680 0.02217 0.01709 0.0099 0.0144 1.0000
12.500 1.2832 0.02274 0.01772 0.0116 0.0139 1.0000
12.750 1.2982 0.02332 0.01835 0.0132 0.0134 1.0000
13.000 1.3131 0.02391 0.01900 0.0147 0.0130 1.0000
13.250 1.3263 0.02465 0.01977 0.0162 0.0125 1.0000
13.500 1.3317 0.02600 0.02120 0.0185 0.0120 1.0000
13.750 1.3350 0.02755 0.02289 0.0209 0.0116 1.0000
14.000 1.3481 0.02836 0.02379 0.0222 0.0113 1.0000
14.250 1.3593 0.02934 0.02486 0.0235 0.0110 1.0000
14.500 1.3685 0.03050 0.02611 0.0248 0.0107 1.0000
14.750 1.3770 0.03178 0.02747 0.0260 0.0104 1.0000
15.000 1.3845 0.03318 0.02896 0.0270 0.0101 1.0000
15.250 1.3906 0.03478 0.03063 0.0279 0.0098 1.0000
15.500 1.3940 0.03669 0.03263 0.0287 0.0096 1.0000
15.750 1.3929 0.03917 0.03520 0.0293 0.0093 1.0000
16.000 1.3837 0.04268 0.03886 0.0296 0.0091 1.0000
16.250 1.3676 0.04730 0.04365 0.0290 0.0089 1.0000
16.500 1.3539 0.05202 0.04854 0.0278 0.0088 1.0000
16.750 1.3466 0.05624 0.05290 0.0263 0.0087 1.0000
17.000 1.3342 0.06149 0.05831 0.0239 0.0086 1.0000
17.250 1.3182 0.06768 0.06465 0.0208 0.0086 1.0000
17.500 1.2951 0.07549 0.07263 0.0166 0.0086 1.0000
17.750 1.2635 0.08527 0.08259 0.0111 0.0086 1.0000
18.000 1.2223 0.09733 0.09483 0.0045 0.0087 1.0000
18.250 1.1747 0.11087 0.10854 -0.0027 0.0088 1.0000
18.500 1.1457 0.12105 0.11884 -0.0080 0.0089 1.0000
18.750 1.1084 0.13320 0.13114 -0.0144 0.0091 1.0000
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Polar data table (+)
Polar graphs
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