AG47c -03f (ag47c03-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG47c -03f (ag47c03-il) Reynolds number: 1,000,000 Max Cl/Cd: 80.25 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag47c03-il-1000000.txt Download as CSV file: xf-ag47c03-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: AG47c -03f
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
------ -------- --------- --------- -------- -------- --------
-7.250 -0.5298 0.08348 0.08205 0.0210 1.0000 0.0077
-7.000 -0.5303 0.07938 0.07796 0.0197 1.0000 0.0078
-6.750 -0.5313 0.07518 0.07377 0.0182 1.0000 0.0080
-6.500 -0.5331 0.07094 0.06955 0.0164 1.0000 0.0081
-6.250 -0.5350 0.06645 0.06507 0.0136 1.0000 0.0083
-6.000 -0.5315 0.06094 0.05957 0.0082 1.0000 0.0084
-5.750 -0.5240 0.05491 0.05351 0.0022 1.0000 0.0087
-5.500 -0.5129 0.04868 0.04724 -0.0037 1.0000 0.0090
-5.250 -0.4982 0.04211 0.04059 -0.0092 1.0000 0.0096
-5.000 -0.4760 0.03662 0.03498 -0.0133 1.0000 0.0105
-4.750 -0.4556 0.03134 0.02956 -0.0161 1.0000 0.0107
-4.500 -0.4356 0.02582 0.02386 -0.0183 1.0000 0.0107
-4.250 -0.4150 0.02073 0.01853 -0.0198 1.0000 0.0108
-4.000 -0.3936 0.01628 0.01378 -0.0208 1.0000 0.0108
-3.750 -0.3771 0.00904 0.00590 -0.0223 1.0000 0.0117
-3.500 -0.3530 0.00749 0.00415 -0.0224 1.0000 0.0122
-3.250 -0.3365 0.01226 0.00764 -0.0213 1.0000 0.0072
-3.000 -0.3091 0.01094 0.00610 -0.0209 1.0000 0.0071
-2.750 -0.2820 0.00944 0.00443 -0.0206 1.0000 0.0075
-2.500 -0.2546 0.00885 0.00380 -0.0204 1.0000 0.0084
-2.250 -0.2270 0.00843 0.00335 -0.0202 1.0000 0.0095
-2.000 -0.1994 0.00800 0.00288 -0.0200 1.0000 0.0102
-1.750 -0.1717 0.00770 0.00255 -0.0198 1.0000 0.0108
-1.500 -0.1408 0.00703 0.00180 -0.0203 0.9889 0.0138
-1.250 -0.1074 0.00681 0.00138 -0.0211 0.8857 0.0214
-1.000 -0.0844 0.00695 0.00117 -0.0197 0.7791 0.0362
-0.750 -0.0574 0.00682 0.00104 -0.0194 0.7491 0.0711
-0.500 -0.0300 0.00660 0.00093 -0.0194 0.7332 0.1329
-0.250 -0.0025 0.00632 0.00086 -0.0194 0.7214 0.2183
0.000 0.0247 0.00587 0.00081 -0.0195 0.7114 0.3643
0.250 0.0513 0.00525 0.00079 -0.0195 0.7020 0.5744
0.500 0.0766 0.00465 0.00078 -0.0190 0.6922 0.7686
0.750 0.1040 0.00410 0.00076 -0.0182 0.6805 1.0000
1.000 0.1320 0.00412 0.00071 -0.0181 0.6663 1.0000
1.250 0.1600 0.00415 0.00067 -0.0180 0.6483 1.0000
1.500 0.1878 0.00422 0.00064 -0.0178 0.6264 1.0000
1.750 0.2156 0.00431 0.00062 -0.0177 0.6003 1.0000
2.000 0.2433 0.00443 0.00062 -0.0176 0.5694 1.0000
2.250 0.2710 0.00457 0.00063 -0.0175 0.5354 1.0000
2.500 0.2986 0.00475 0.00066 -0.0173 0.4948 1.0000
2.750 0.3262 0.00495 0.00071 -0.0173 0.4558 1.0000
3.000 0.3537 0.00520 0.00077 -0.0172 0.4057 1.0000
3.250 0.3811 0.00546 0.00086 -0.0172 0.3586 1.0000
3.500 0.4085 0.00576 0.00097 -0.0171 0.3088 1.0000
3.750 0.4358 0.00609 0.00110 -0.0171 0.2556 1.0000
4.000 0.4632 0.00639 0.00123 -0.0171 0.2131 1.0000
4.250 0.4905 0.00670 0.00139 -0.0171 0.1754 1.0000
4.500 0.5178 0.00702 0.00156 -0.0171 0.1410 1.0000
5.000 0.5726 0.00755 0.00194 -0.0170 0.0981 1.0000
5.250 0.6000 0.00782 0.00214 -0.0169 0.0823 1.0000
5.500 0.6273 0.00807 0.00236 -0.0169 0.0709 1.0000
5.750 0.6547 0.00833 0.00260 -0.0168 0.0606 1.0000
6.000 0.6818 0.00864 0.00287 -0.0167 0.0507 1.0000
6.250 0.7091 0.00888 0.00311 -0.0166 0.0446 1.0000
6.500 0.7362 0.00919 0.00341 -0.0165 0.0379 1.0000
6.750 0.7632 0.00951 0.00372 -0.0164 0.0322 1.0000
7.000 0.7901 0.00988 0.00413 -0.0163 0.0275 1.0000
7.250 0.8170 0.01020 0.00447 -0.0162 0.0238 1.0000
7.500 0.8431 0.01088 0.00520 -0.0160 0.0193 1.0000
7.750 0.8700 0.01114 0.00550 -0.0159 0.0178 1.0000
8.000 0.8964 0.01155 0.00595 -0.0157 0.0159 1.0000
8.250 0.9220 0.01235 0.00684 -0.0155 0.0136 1.0000
8.500 0.9465 0.01343 0.00810 -0.0151 0.0125 1.0000
8.750 0.9728 0.01378 0.00851 -0.0150 0.0119 1.0000
9.000 0.9986 0.01429 0.00909 -0.0148 0.0111 1.0000
9.250 1.0241 0.01488 0.00976 -0.0146 0.0103 1.0000
9.500 1.0493 0.01549 0.01043 -0.0144 0.0095 1.0000
9.750 1.0716 0.01698 0.01211 -0.0140 0.0084 1.0000
10.000 1.0935 0.01853 0.01389 -0.0135 0.0078 1.0000
10.250 1.1188 0.01895 0.01437 -0.0134 0.0074 1.0000
10.500 1.1426 0.01977 0.01532 -0.0131 0.0069 1.0000
10.750 1.1661 0.02060 0.01626 -0.0129 0.0064 1.0000
11.000 1.1896 0.02134 0.01709 -0.0127 0.0059 1.0000
11.250 1.2120 0.02229 0.01813 -0.0125 0.0055 1.0000
11.500 1.2222 0.02615 0.02243 -0.0117 0.0049 1.0000
11.750 1.2343 0.02916 0.02580 -0.0112 0.0047 1.0000
12.000 1.2524 0.03062 0.02744 -0.0109 0.0046 1.0000
12.250 1.2671 0.03261 0.02964 -0.0106 0.0044 1.0000
12.500 1.2778 0.03506 0.03233 -0.0104 0.0042 1.0000
12.750 1.2830 0.03814 0.03565 -0.0105 0.0040 1.0000
13.000 1.2816 0.04182 0.03958 -0.0110 0.0039 1.0000
13.250 1.2604 0.04824 0.04626 -0.0158 0.0040 1.0000
13.500 1.2317 0.06058 0.05885 -0.0284 0.0041 1.0000
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Polar data table (+)
Polar graphs
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