NASA/LANGLEY RC-08(B)3 AIRFOIL (rc08b3-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY RC-08(B)3 AIRFOIL (rc08b3-il) Reynolds number: 1,000,000 Max Cl/Cd: 73.8 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rc08b3-il-1000000-n5.txt Download as CSV file: xf-rc08b3-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY RC-08(B)3 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.6449 0.10966 0.10801 0.0095 1.0000 0.0066
-10.500 -0.6474 0.10448 0.10285 0.0070 1.0000 0.0067
-9.000 -0.8406 0.02835 0.02517 -0.0184 1.0000 0.0082
-8.750 -0.8281 0.02571 0.02222 -0.0168 1.0000 0.0082
-8.500 -0.8123 0.02377 0.02002 -0.0153 1.0000 0.0083
-8.250 -0.7949 0.02221 0.01824 -0.0139 1.0000 0.0083
-8.000 -0.7844 0.01873 0.01428 -0.0116 0.9986 0.0086
-7.750 -0.7575 0.01740 0.01277 -0.0121 0.9946 0.0089
-7.500 -0.7295 0.01671 0.01197 -0.0126 0.9900 0.0091
-7.250 -0.7003 0.01612 0.01132 -0.0132 0.9857 0.0094
-7.000 -0.6725 0.01539 0.01048 -0.0135 0.9805 0.0096
-6.750 -0.6445 0.01467 0.00965 -0.0138 0.9749 0.0098
-6.500 -0.6175 0.01398 0.00886 -0.0139 0.9689 0.0101
-6.250 -0.5912 0.01336 0.00813 -0.0137 0.9621 0.0104
-6.000 -0.5657 0.01279 0.00747 -0.0133 0.9556 0.0107
-5.750 -0.5406 0.01226 0.00685 -0.0127 0.9485 0.0110
-5.500 -0.5156 0.01177 0.00628 -0.0122 0.9421 0.0112
-5.250 -0.4906 0.01131 0.00575 -0.0116 0.9351 0.0114
-5.000 -0.4655 0.01089 0.00526 -0.0111 0.9287 0.0116
-4.750 -0.4401 0.01050 0.00480 -0.0106 0.9218 0.0118
-4.500 -0.4146 0.01015 0.00439 -0.0100 0.9154 0.0119
-4.250 -0.3888 0.00982 0.00401 -0.0096 0.9082 0.0121
-4.000 -0.3629 0.00955 0.00369 -0.0092 0.9014 0.0122
-3.750 -0.3371 0.00919 0.00327 -0.0088 0.8941 0.0126
-3.500 -0.3116 0.00881 0.00281 -0.0083 0.8871 0.0132
-3.250 -0.2852 0.00854 0.00251 -0.0079 0.8797 0.0139
-3.000 -0.2587 0.00834 0.00228 -0.0076 0.8725 0.0146
-2.750 -0.2319 0.00817 0.00207 -0.0074 0.8641 0.0153
-2.500 -0.2050 0.00802 0.00188 -0.0071 0.8556 0.0160
-2.250 -0.1781 0.00790 0.00172 -0.0069 0.8461 0.0168
-2.000 -0.1509 0.00778 0.00157 -0.0067 0.8368 0.0174
-1.750 -0.1240 0.00766 0.00142 -0.0065 0.8263 0.0206
-1.500 -0.0973 0.00752 0.00130 -0.0062 0.8140 0.0313
-1.000 -0.0440 0.00718 0.00111 -0.0058 0.7895 0.0870
-0.750 -0.0175 0.00701 0.00103 -0.0055 0.7766 0.1267
-0.500 0.0081 0.00673 0.00096 -0.0052 0.7618 0.2051
-0.250 0.0323 0.00628 0.00088 -0.0047 0.7460 0.3403
0.000 0.0566 0.00591 0.00081 -0.0041 0.7300 0.4529
0.250 0.0757 0.00511 0.00072 -0.0025 0.7145 0.6777
0.500 0.0918 0.00442 0.00078 0.0004 0.6987 0.8956
0.750 0.1208 0.00459 0.00098 0.0006 0.6756 0.9481
1.000 0.1501 0.00485 0.00113 0.0005 0.6436 0.9648
1.250 0.1759 0.00504 0.00121 0.0011 0.6141 0.9729
1.500 0.2091 0.00523 0.00127 -0.0001 0.5790 0.9747
1.750 0.2410 0.00551 0.00135 -0.0012 0.5234 0.9763
2.000 0.2721 0.00581 0.00142 -0.0021 0.4665 0.9776
2.250 0.3017 0.00623 0.00153 -0.0028 0.3872 0.9790
2.500 0.3309 0.00662 0.00166 -0.0034 0.3183 0.9809
2.750 0.3585 0.00693 0.00177 -0.0036 0.2699 0.9830
3.000 0.3859 0.00721 0.00189 -0.0037 0.2297 0.9849
3.500 0.4473 0.00795 0.00221 -0.0057 0.1282 0.9864
3.750 0.4773 0.00829 0.00238 -0.0064 0.0911 0.9872
4.000 0.5070 0.00857 0.00255 -0.0071 0.0665 0.9880
4.250 0.5364 0.00883 0.00272 -0.0077 0.0509 0.9889
4.500 0.5657 0.00905 0.00291 -0.0082 0.0417 0.9899
4.750 0.5948 0.00925 0.00309 -0.0087 0.0351 0.9910
5.000 0.6233 0.00950 0.00330 -0.0090 0.0289 0.9921
5.250 0.6516 0.00970 0.00351 -0.0093 0.0262 0.9931
5.500 0.6792 0.00995 0.00375 -0.0094 0.0232 0.9942
5.750 0.7084 0.01022 0.00402 -0.0100 0.0204 0.9948
6.000 0.7376 0.01045 0.00427 -0.0105 0.0193 0.9954
6.250 0.7666 0.01071 0.00455 -0.0110 0.0182 0.9960
6.500 0.7955 0.01101 0.00486 -0.0115 0.0171 0.9967
6.750 0.8239 0.01135 0.00522 -0.0119 0.0159 0.9974
7.000 0.8515 0.01178 0.00570 -0.0122 0.0148 0.9982
7.250 0.8795 0.01206 0.00601 -0.0125 0.0144 0.9988
7.500 0.9074 0.01236 0.00634 -0.0128 0.0139 0.9995
7.750 0.9350 0.01267 0.00670 -0.0131 0.0131 1.0000
8.000 0.9568 0.01300 0.00705 -0.0121 0.0125 1.0000
8.250 0.9783 0.01334 0.00742 -0.0111 0.0120 1.0000
8.500 0.9993 0.01374 0.00785 -0.0099 0.0113 1.0000
8.750 1.0184 0.01435 0.00852 -0.0085 0.0105 1.0000
9.000 1.0397 0.01465 0.00887 -0.0074 0.0102 1.0000
9.250 1.0607 0.01498 0.00925 -0.0063 0.0098 1.0000
9.500 1.0812 0.01534 0.00966 -0.0051 0.0093 1.0000
9.750 1.1014 0.01573 0.01010 -0.0039 0.0088 1.0000
10.000 1.1213 0.01614 0.01055 -0.0027 0.0083 1.0000
10.250 1.1409 0.01658 0.01101 -0.0014 0.0078 1.0000
10.500 1.1592 0.01716 0.01164 0.0000 0.0072 1.0000
10.750 1.1774 0.01774 0.01231 0.0015 0.0069 1.0000
11.000 1.1960 0.01828 0.01292 0.0028 0.0066 1.0000
11.250 1.2141 0.01885 0.01358 0.0042 0.0063 1.0000
11.500 1.2320 0.01945 0.01425 0.0056 0.0060 1.0000
11.750 1.2499 0.02007 0.01495 0.0069 0.0057 1.0000
12.000 1.2677 0.02073 0.01566 0.0082 0.0054 1.0000
12.250 1.2849 0.02143 0.01642 0.0095 0.0051 1.0000
12.500 1.3006 0.02228 0.01737 0.0109 0.0047 1.0000
12.750 1.3131 0.02342 0.01863 0.0127 0.0044 1.0000
13.000 1.3276 0.02429 0.01960 0.0142 0.0043 1.0000
13.250 1.3403 0.02525 0.02068 0.0159 0.0042 1.0000
13.500 1.3492 0.02627 0.02182 0.0181 0.0042 1.0000
13.750 1.3563 0.02739 0.02306 0.0204 0.0041 1.0000
14.000 1.3622 0.02865 0.02445 0.0225 0.0040 1.0000
14.250 1.3668 0.03009 0.02601 0.0245 0.0039 1.0000
14.500 1.3700 0.03172 0.02777 0.0262 0.0038 1.0000
14.750 1.3718 0.03356 0.02975 0.0276 0.0037 1.0000
15.000 1.3718 0.03570 0.03203 0.0287 0.0037 1.0000
15.250 1.3698 0.03820 0.03467 0.0294 0.0036 1.0000
15.500 1.3655 0.04116 0.03778 0.0296 0.0035 1.0000
15.750 1.3590 0.04465 0.04142 0.0291 0.0035 1.0000
16.000 1.3488 0.04896 0.04590 0.0277 0.0035 1.0000
16.250 1.3344 0.05439 0.05149 0.0251 0.0034 1.0000
16.500 1.3136 0.06153 0.05882 0.0210 0.0034 1.0000
16.750 1.2833 0.07140 0.06890 0.0146 0.0035 1.0000
17.000 1.2289 0.08704 0.08477 0.0051 0.0036 1.0000
17.250 1.1198 0.11419 0.11221 -0.0090 0.0039 1.0000
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Polar data table (+)
Polar graphs
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