ONERA NACA CAMBRE AIRFOIL (ncambre-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: ONERA NACA CAMBRE AIRFOIL (ncambre-il) Reynolds number: 50,000 Max Cl/Cd: 29.62 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ncambre-il-50000-n5.txt Download as CSV file: xf-ncambre-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: ONERA NACA CAMBRE 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5672 0.09583 0.08841 -0.0185 1.0000 0.0682
-9.500 -0.5773 0.08902 0.08162 -0.0236 1.0000 0.0658
-9.250 -0.6309 0.08069 0.07308 -0.0298 1.0000 0.0621
-9.000 -0.6288 0.07703 0.06941 -0.0296 1.0000 0.0614
-8.750 -0.6324 0.07321 0.06551 -0.0294 1.0000 0.0607
-8.500 -0.6366 0.06936 0.06154 -0.0289 1.0000 0.0599
-8.250 -0.6396 0.06557 0.05757 -0.0282 1.0000 0.0592
-8.000 -0.6405 0.06187 0.05364 -0.0271 1.0000 0.0585
-7.750 -0.6389 0.05831 0.04980 -0.0257 1.0000 0.0578
-7.500 -0.6345 0.05493 0.04612 -0.0241 1.0000 0.0573
-7.250 -0.6274 0.05188 0.04273 -0.0224 1.0000 0.0573
-7.000 -0.6179 0.04912 0.03966 -0.0207 1.0000 0.0579
-6.750 -0.6067 0.04654 0.03674 -0.0189 1.0000 0.0588
-6.500 -0.5939 0.04408 0.03393 -0.0170 1.0000 0.0596
-6.250 -0.5792 0.04173 0.03122 -0.0152 1.0000 0.0601
-6.000 -0.5624 0.03950 0.02865 -0.0135 1.0000 0.0603
-5.750 -0.5440 0.03744 0.02626 -0.0119 1.0000 0.0606
-5.500 -0.5240 0.03555 0.02407 -0.0104 1.0000 0.0611
-5.250 -0.5031 0.03388 0.02207 -0.0090 1.0000 0.0621
-5.000 -0.4818 0.03229 0.02050 -0.0080 1.0000 0.0641
-4.750 -0.4599 0.03098 0.01912 -0.0069 1.0000 0.0666
-4.500 -0.4368 0.02971 0.01774 -0.0058 1.0000 0.0687
-4.250 -0.4130 0.02854 0.01645 -0.0046 1.0000 0.0703
-4.000 -0.3903 0.02747 0.01537 -0.0034 1.0000 0.0724
-3.750 -0.3697 0.02659 0.01451 -0.0021 1.0000 0.0762
-3.500 -0.3493 0.02587 0.01367 -0.0006 1.0000 0.0808
-3.250 -0.3306 0.02501 0.01286 0.0009 1.0000 0.0848
-3.000 -0.3118 0.02431 0.01209 0.0024 1.0000 0.0897
-2.750 -0.2933 0.02361 0.01138 0.0037 1.0000 0.0974
-2.500 -0.2743 0.02294 0.01072 0.0048 1.0000 0.1088
-2.250 -0.2559 0.02220 0.01009 0.0060 1.0000 0.1292
-2.000 -0.2462 0.01947 0.00959 0.0080 1.0000 0.4939
-1.750 -0.2331 0.01897 0.01031 0.0138 1.0000 0.7733
-1.500 -0.0902 0.02045 0.01155 -0.0016 1.0000 0.9731
-1.250 -0.0416 0.02037 0.01125 -0.0068 1.0000 0.9904
-1.000 -0.0038 0.02030 0.01101 -0.0104 0.9955 1.0000
-0.750 0.0472 0.02020 0.01072 -0.0161 0.9761 1.0000
-0.500 0.0978 0.02007 0.01045 -0.0215 0.9575 1.0000
-0.250 0.1430 0.01992 0.01019 -0.0255 0.9369 1.0000
0.000 0.1849 0.01974 0.00992 -0.0286 0.9141 1.0000
0.250 0.2244 0.01953 0.00963 -0.0310 0.8898 1.0000
0.500 0.2595 0.01934 0.00936 -0.0322 0.8635 1.0000
0.750 0.2886 0.01921 0.00915 -0.0322 0.8356 1.0000
1.000 0.3162 0.01910 0.00896 -0.0318 0.8089 1.0000
1.250 0.3417 0.01904 0.00879 -0.0308 0.7818 1.0000
1.500 0.3642 0.01905 0.00871 -0.0294 0.7526 1.0000
1.750 0.3864 0.01908 0.00862 -0.0279 0.7239 1.0000
2.000 0.4085 0.01914 0.00855 -0.0263 0.6961 1.0000
2.250 0.4301 0.01927 0.00855 -0.0247 0.6685 1.0000
2.500 0.4512 0.01945 0.00863 -0.0231 0.6409 1.0000
2.750 0.4725 0.01965 0.00870 -0.0215 0.6145 1.0000
3.000 0.4936 0.01989 0.00884 -0.0200 0.5884 1.0000
3.250 0.5146 0.02016 0.00902 -0.0185 0.5624 1.0000
3.500 0.5360 0.02046 0.00920 -0.0170 0.5365 1.0000
3.750 0.5571 0.02080 0.00945 -0.0157 0.5100 1.0000
4.000 0.5784 0.02117 0.00969 -0.0143 0.4852 1.0000
4.250 0.5994 0.02158 0.01004 -0.0130 0.4602 1.0000
4.500 0.6207 0.02202 0.01036 -0.0117 0.4375 1.0000
4.750 0.6417 0.02248 0.01080 -0.0105 0.4141 1.0000
5.000 0.6628 0.02297 0.01125 -0.0093 0.3931 1.0000
5.250 0.6839 0.02348 0.01166 -0.0081 0.3735 1.0000
5.500 0.7050 0.02404 0.01219 -0.0070 0.3541 1.0000
5.750 0.7259 0.02464 0.01279 -0.0058 0.3353 1.0000
6.000 0.7468 0.02527 0.01341 -0.0047 0.3176 1.0000
6.250 0.7678 0.02593 0.01406 -0.0037 0.3014 1.0000
6.500 0.7888 0.02663 0.01475 -0.0027 0.2866 1.0000
6.750 0.8099 0.02737 0.01551 -0.0017 0.2732 1.0000
7.000 0.8310 0.02814 0.01623 -0.0007 0.2608 1.0000
7.250 0.8518 0.02900 0.01721 0.0002 0.2484 1.0000
7.500 0.8727 0.02992 0.01823 0.0011 0.2375 1.0000
7.750 0.8937 0.03081 0.01914 0.0020 0.2279 1.0000
8.000 0.9138 0.03179 0.02026 0.0030 0.2180 1.0000
8.250 0.9343 0.03289 0.02148 0.0038 0.2099 1.0000
8.500 0.9544 0.03397 0.02267 0.0047 0.2020 1.0000
8.750 0.9734 0.03520 0.02407 0.0057 0.1944 1.0000
9.000 0.9922 0.03638 0.02538 0.0066 0.1871 1.0000
9.250 1.0111 0.03776 0.02690 0.0075 0.1811 1.0000
9.500 1.0266 0.03932 0.02876 0.0087 0.1744 1.0000
9.750 1.0470 0.04039 0.02978 0.0095 0.1686 1.0000
10.000 1.0557 0.04242 0.03228 0.0111 0.1619 1.0000
10.250 1.0727 0.04353 0.03342 0.0122 0.1557 1.0000
10.500 1.0782 0.04548 0.03571 0.0140 0.1488 1.0000
10.750 1.0916 0.04642 0.03671 0.0153 0.1417 1.0000
11.000 1.0927 0.04857 0.03917 0.0172 0.1355 1.0000
11.250 1.0978 0.05013 0.04087 0.0189 0.1291 1.0000
11.500 1.1008 0.05191 0.04277 0.0206 0.1236 1.0000
11.750 1.0861 0.05495 0.04613 0.0230 0.1194 1.0000
12.000 1.0906 0.05623 0.04741 0.0244 0.1139 1.0000
12.250 1.0785 0.05951 0.05087 0.0254 0.1104 1.0000
12.500 1.0498 0.06510 0.05678 0.0248 0.1086 1.0000
12.750 1.0136 0.07274 0.06467 0.0217 0.1079 1.0000
13.000 0.9563 0.08559 0.07771 0.0143 0.1093 1.0000
13.250 0.8694 0.10801 0.10008 0.0007 0.1104 1.0000
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Polar data table (+)
Polar graphs
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