AG47c -03f (ag47c03-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG47c -03f (ag47c03-il) Reynolds number: 200,000 Max Cl/Cd: 49.33 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag47c03-il-200000-n5.txt Download as CSV file: xf-ag47c03-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.6253 0.10062 0.09724 0.0314 1.0000 0.0202
-7.000 -0.6214 0.09676 0.09340 0.0291 1.0000 0.0205
-6.750 -0.6175 0.09283 0.08950 0.0265 1.0000 0.0208
-6.500 -0.6126 0.08871 0.08541 0.0231 1.0000 0.0211
-6.250 -0.6035 0.08404 0.08076 0.0181 1.0000 0.0213
-6.000 -0.5918 0.07904 0.07576 0.0125 1.0000 0.0215
-5.750 -0.5774 0.07374 0.07043 0.0066 1.0000 0.0215
-5.500 -0.5607 0.06808 0.06473 0.0006 1.0000 0.0210
-5.250 -0.5384 0.05975 0.05622 -0.0072 1.0000 0.0151
-5.000 -0.5185 0.05399 0.05032 -0.0116 1.0000 0.0139
-4.750 -0.4947 0.04671 0.04276 -0.0162 1.0000 0.0125
-4.250 -0.4413 0.03244 0.02751 -0.0208 1.0000 0.0106
-4.000 -0.4161 0.02777 0.02231 -0.0217 1.0000 0.0105
-3.750 -0.3897 0.02396 0.01791 -0.0219 1.0000 0.0106
-3.500 -0.3629 0.02071 0.01408 -0.0219 1.0000 0.0110
-3.250 -0.3365 0.01852 0.01157 -0.0219 1.0000 0.0118
-3.000 -0.3098 0.01779 0.01068 -0.0219 1.0000 0.0138
-2.750 -0.2824 0.01641 0.00904 -0.0215 1.0000 0.0153
-2.500 -0.2551 0.01496 0.00737 -0.0211 1.0000 0.0159
-2.250 -0.2279 0.01385 0.00611 -0.0207 1.0000 0.0167
-2.000 -0.2012 0.01256 0.00476 -0.0204 1.0000 0.0187
-1.750 -0.1740 0.01198 0.00413 -0.0202 1.0000 0.0231
-1.500 -0.1467 0.01130 0.00341 -0.0199 1.0000 0.0298
-1.250 -0.1193 0.01076 0.00290 -0.0198 1.0000 0.0441
-1.000 -0.0920 0.01025 0.00251 -0.0197 1.0000 0.0766
-0.750 -0.0650 0.00969 0.00226 -0.0197 1.0000 0.1483
-0.500 -0.0385 0.00900 0.00206 -0.0198 1.0000 0.2828
-0.250 -0.0141 0.00796 0.00197 -0.0196 1.0000 0.5324
0.000 0.0094 0.00690 0.00197 -0.0177 0.9637 0.8449
0.250 0.0608 0.00677 0.00178 -0.0220 0.8872 1.0000
0.500 0.0894 0.00695 0.00163 -0.0215 0.8156 1.0000
1.000 0.1405 0.00734 0.00152 -0.0198 0.7484 1.0000
1.250 0.1668 0.00752 0.00152 -0.0193 0.7276 1.0000
1.500 0.1933 0.00772 0.00154 -0.0188 0.7094 1.0000
1.750 0.2202 0.00787 0.00159 -0.0184 0.6905 1.0000
2.000 0.2473 0.00799 0.00163 -0.0181 0.6683 1.0000
2.250 0.2744 0.00809 0.00165 -0.0178 0.6425 1.0000
2.500 0.3013 0.00821 0.00168 -0.0174 0.6123 1.0000
2.750 0.3280 0.00835 0.00170 -0.0170 0.5762 1.0000
3.000 0.3546 0.00854 0.00173 -0.0166 0.5348 1.0000
3.250 0.3810 0.00880 0.00179 -0.0162 0.4872 1.0000
3.500 0.4074 0.00911 0.00192 -0.0159 0.4350 1.0000
3.750 0.4338 0.00948 0.00206 -0.0156 0.3789 1.0000
4.000 0.4602 0.00989 0.00225 -0.0155 0.3218 1.0000
4.250 0.4866 0.01034 0.00248 -0.0154 0.2666 1.0000
4.500 0.5130 0.01083 0.00276 -0.0153 0.2146 1.0000
4.750 0.5396 0.01129 0.00311 -0.0152 0.1755 1.0000
5.250 0.5926 0.01223 0.00384 -0.0150 0.1190 1.0000
5.500 0.6192 0.01270 0.00427 -0.0149 0.1022 1.0000
5.750 0.6457 0.01316 0.00475 -0.0148 0.0872 1.0000
6.000 0.6720 0.01367 0.00525 -0.0147 0.0752 1.0000
6.250 0.6983 0.01417 0.00580 -0.0145 0.0654 1.0000
6.500 0.7246 0.01469 0.00638 -0.0143 0.0562 1.0000
6.750 0.7504 0.01536 0.00708 -0.0141 0.0493 1.0000
7.000 0.7763 0.01595 0.00780 -0.0139 0.0428 1.0000
7.250 0.8017 0.01670 0.00862 -0.0137 0.0369 1.0000
7.500 0.8271 0.01746 0.00951 -0.0134 0.0327 1.0000
7.750 0.8509 0.01870 0.01081 -0.0131 0.0286 1.0000
8.000 0.8762 0.01945 0.01175 -0.0128 0.0258 1.0000
8.250 0.9008 0.02042 0.01292 -0.0125 0.0231 1.0000
8.500 0.9245 0.02159 0.01423 -0.0121 0.0211 1.0000
8.750 0.9455 0.02380 0.01662 -0.0116 0.0195 1.0000
9.000 0.9683 0.02537 0.01851 -0.0111 0.0184 1.0000
9.250 0.9907 0.02691 0.02038 -0.0107 0.0167 1.0000
9.500 1.0117 0.02872 0.02249 -0.0104 0.0154 1.0000
9.750 1.0312 0.03080 0.02487 -0.0100 0.0145 1.0000
10.000 1.0488 0.03311 0.02747 -0.0098 0.0137 1.0000
10.250 1.0610 0.03661 0.03142 -0.0096 0.0131 1.0000
10.500 1.0642 0.04184 0.03721 -0.0097 0.0126 1.0000
10.750 1.0673 0.04634 0.04222 -0.0103 0.0122 1.0000
11.000 1.0602 0.05202 0.04836 -0.0121 0.0119 1.0000
11.250 1.0427 0.05847 0.05513 -0.0162 0.0119 1.0000
11.500 1.0214 0.06791 0.06474 -0.0262 0.0123 1.0000
11.750 0.9373 0.10030 0.09718 -0.0483 0.0142 1.0000
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Polar data table (+)
Polar graphs
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