AG47ct -02f rot. (ag47ct02r-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: AG47ct -02f rot. (ag47ct02r-il) Reynolds number: 1,000,000 Max Cl/Cd: 80.8 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag47ct02r-il-1000000.txt Download as CSV file: xf-ag47ct02r-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: AG47ct -02f rot.
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.6288 0.09855 0.09701 0.0299 1.0000 0.0070
-8.000 -0.6254 0.09440 0.09288 0.0275 1.0000 0.0070
-7.750 -0.6220 0.09015 0.08864 0.0246 1.0000 0.0071
-7.500 -0.6158 0.08539 0.08388 0.0201 1.0000 0.0071
-7.250 -0.6047 0.07981 0.07830 0.0136 1.0000 0.0071
-7.000 -0.5971 0.06992 0.06840 0.0026 1.0000 0.0074
-6.750 -0.5824 0.06489 0.06331 -0.0027 1.0000 0.0077
-6.500 -0.5644 0.06080 0.05918 -0.0068 1.0000 0.0080
-6.250 -0.5442 0.05625 0.05456 -0.0110 1.0000 0.0083
-6.000 -0.5219 0.05117 0.04937 -0.0151 1.0000 0.0088
-5.750 -0.4979 0.04575 0.04380 -0.0188 1.0000 0.0095
-5.500 -0.4708 0.04024 0.03810 -0.0213 1.0000 0.0105
-5.250 -0.4419 0.03678 0.03446 -0.0220 1.0000 0.0112
-5.000 -0.4167 0.03212 0.02951 -0.0231 1.0000 0.0112
-4.000 -0.3161 0.01168 0.00695 -0.0236 1.0000 0.0076
-3.750 -0.2890 0.01055 0.00565 -0.0232 1.0000 0.0074
-3.500 -0.2622 0.00916 0.00410 -0.0228 1.0000 0.0076
-3.250 -0.2351 0.00843 0.00330 -0.0225 1.0000 0.0086
-3.000 -0.2078 0.00806 0.00291 -0.0223 1.0000 0.0098
-2.750 -0.1806 0.00770 0.00252 -0.0220 1.0000 0.0108
-2.500 -0.1532 0.00724 0.00198 -0.0217 1.0000 0.0120
-2.250 -0.1260 0.00688 0.00162 -0.0214 1.0000 0.0161
-2.000 -0.0986 0.00654 0.00129 -0.0211 1.0000 0.0262
-1.750 -0.0715 0.00627 0.00111 -0.0209 1.0000 0.0503
-1.500 -0.0345 0.00592 0.00097 -0.0230 0.9848 0.1082
-1.250 0.0034 0.00553 0.00084 -0.0252 0.9304 0.2039
-1.000 0.0246 0.00547 0.00074 -0.0235 0.8123 0.3172
-0.750 0.0494 0.00511 0.00070 -0.0231 0.7533 0.5010
-0.500 0.0745 0.00458 0.00069 -0.0226 0.7266 0.7076
-0.250 0.0938 0.00403 0.00071 -0.0203 0.7102 0.9106
0.000 0.1286 0.00401 0.00069 -0.0215 0.6939 1.0000
0.250 0.1564 0.00406 0.00067 -0.0213 0.6742 1.0000
0.500 0.1841 0.00414 0.00064 -0.0211 0.6493 1.0000
0.750 0.2116 0.00424 0.00062 -0.0210 0.6175 1.0000
1.000 0.2391 0.00439 0.00062 -0.0208 0.5810 1.0000
1.250 0.2665 0.00456 0.00063 -0.0206 0.5404 1.0000
1.500 0.2939 0.00476 0.00067 -0.0204 0.4981 1.0000
1.750 0.3211 0.00499 0.00072 -0.0203 0.4478 1.0000
2.000 0.3484 0.00524 0.00078 -0.0202 0.3992 1.0000
2.250 0.3756 0.00554 0.00086 -0.0201 0.3444 1.0000
2.500 0.4029 0.00580 0.00096 -0.0200 0.2993 1.0000
2.750 0.4301 0.00610 0.00109 -0.0199 0.2530 1.0000
3.000 0.4573 0.00640 0.00122 -0.0198 0.2119 1.0000
3.250 0.4846 0.00666 0.00135 -0.0197 0.1808 1.0000
3.500 0.5119 0.00693 0.00150 -0.0196 0.1520 1.0000
3.750 0.5391 0.00721 0.00169 -0.0196 0.1259 1.0000
4.000 0.5664 0.00746 0.00187 -0.0194 0.1069 1.0000
4.250 0.5936 0.00774 0.00206 -0.0193 0.0889 1.0000
4.500 0.6208 0.00800 0.00228 -0.0192 0.0750 1.0000
4.750 0.6480 0.00826 0.00249 -0.0191 0.0646 1.0000
5.000 0.6752 0.00850 0.00274 -0.0190 0.0557 1.0000
5.250 0.7023 0.00878 0.00301 -0.0188 0.0479 1.0000
5.500 0.7291 0.00914 0.00333 -0.0187 0.0390 1.0000
5.750 0.7563 0.00936 0.00357 -0.0185 0.0350 1.0000
6.000 0.7828 0.00985 0.00407 -0.0183 0.0276 1.0000
6.250 0.8098 0.01008 0.00433 -0.0182 0.0253 1.0000
6.500 0.8362 0.01052 0.00477 -0.0180 0.0211 1.0000
6.750 0.8623 0.01111 0.00545 -0.0177 0.0183 1.0000
7.000 0.8889 0.01143 0.00581 -0.0175 0.0166 1.0000
7.250 0.9151 0.01187 0.00629 -0.0173 0.0149 1.0000
7.500 0.9398 0.01286 0.00741 -0.0168 0.0128 1.0000
7.750 0.9643 0.01385 0.00856 -0.0164 0.0119 1.0000
8.000 0.9904 0.01420 0.00897 -0.0162 0.0113 1.0000
8.250 1.0158 0.01476 0.00961 -0.0159 0.0106 1.0000
8.500 1.0410 0.01537 0.01031 -0.0156 0.0098 1.0000
8.750 1.0659 0.01598 0.01098 -0.0153 0.0091 1.0000
9.000 1.0884 0.01728 0.01244 -0.0148 0.0081 1.0000
9.250 1.1086 0.01923 0.01467 -0.0142 0.0074 1.0000
9.500 1.1339 0.01958 0.01509 -0.0140 0.0071 1.0000
9.750 1.1574 0.02039 0.01601 -0.0136 0.0066 1.0000
10.000 1.1805 0.02126 0.01701 -0.0133 0.0061 1.0000
10.250 1.2036 0.02204 0.01788 -0.0130 0.0057 1.0000
10.500 1.2258 0.02295 0.01888 -0.0127 0.0053 1.0000
10.750 1.2396 0.02571 0.02194 -0.0119 0.0048 1.0000
11.000 1.2423 0.03054 0.02732 -0.0110 0.0045 1.0000
11.250 1.2591 0.03211 0.02906 -0.0106 0.0044 1.0000
11.500 1.2721 0.03420 0.03138 -0.0102 0.0043 1.0000
11.750 1.2806 0.03681 0.03422 -0.0099 0.0041 1.0000
12.000 1.2819 0.04020 0.03787 -0.0099 0.0040 1.0000
12.250 1.2713 0.04440 0.04230 -0.0104 0.0039 1.0000
12.500 1.2457 0.05360 0.05177 -0.0198 0.0040 1.0000
|
Polar data table (+)
Polar graphs
<< Back to AG47ct -02f rot. (ag47ct02r-il)