AG46c -03f (ag46c03-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: AG46c -03f (ag46c03-il) Reynolds number: 500,000 Max Cl/Cd: 74.6 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag46c03-il-500000.txt Download as CSV file: xf-ag46c03-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: AG46c -03f
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.6093 0.11314 0.11096 0.0341 1.0000 0.0133
-8.000 -0.6051 0.10921 0.10704 0.0317 1.0000 0.0137
-7.750 -0.6010 0.10523 0.10308 0.0288 1.0000 0.0140
-7.500 -0.5961 0.10131 0.09918 0.0260 1.0000 0.0142
-7.250 -0.5908 0.09747 0.09536 0.0234 1.0000 0.0143
-7.000 -0.5860 0.09348 0.09139 0.0206 1.0000 0.0144
-6.750 -0.5808 0.08932 0.08723 0.0172 1.0000 0.0144
-6.500 -0.5714 0.08449 0.08242 0.0117 1.0000 0.0145
-6.250 -0.5586 0.07917 0.07710 0.0054 1.0000 0.0145
-6.000 -0.4920 0.05730 0.05536 -0.0059 1.0000 0.0150
-5.750 -0.4860 0.05137 0.04940 -0.0103 1.0000 0.0153
-5.500 -0.4759 0.04648 0.04447 -0.0134 1.0000 0.0157
-5.250 -0.4630 0.04163 0.03954 -0.0164 1.0000 0.0161
-5.000 -0.4479 0.03679 0.03462 -0.0193 1.0000 0.0165
-4.750 -0.4307 0.03190 0.02959 -0.0220 1.0000 0.0172
-4.500 -0.4116 0.02704 0.02456 -0.0243 1.0000 0.0180
-4.250 -0.3907 0.02240 0.01970 -0.0260 1.0000 0.0193
-4.000 -0.3631 0.01980 0.01679 -0.0263 1.0000 0.0218
-3.750 -0.3393 0.01701 0.01363 -0.0265 1.0000 0.0221
-3.250 -0.3055 0.01751 0.01257 -0.0271 1.0000 0.0138
-3.000 -0.2781 0.01527 0.00994 -0.0268 1.0000 0.0140
-2.750 -0.2506 0.01415 0.00862 -0.0264 1.0000 0.0144
-2.500 -0.2240 0.01195 0.00617 -0.0261 1.0000 0.0159
-2.250 -0.1969 0.01082 0.00494 -0.0257 1.0000 0.0160
-2.000 -0.1698 0.00990 0.00396 -0.0253 1.0000 0.0167
-1.750 -0.1424 0.00925 0.00328 -0.0250 1.0000 0.0185
-1.500 -0.1150 0.00880 0.00277 -0.0247 1.0000 0.0219
-1.250 -0.0803 0.00807 0.00206 -0.0261 0.9851 0.0388
-1.000 -0.0394 0.00743 0.00172 -0.0289 0.9284 0.1219
-0.750 -0.0150 0.00721 0.00155 -0.0278 0.8399 0.2104
-0.500 0.0092 0.00682 0.00141 -0.0272 0.7921 0.3557
-0.250 0.0332 0.00601 0.00136 -0.0266 0.7665 0.6190
0.000 0.0516 0.00533 0.00138 -0.0241 0.7489 0.8570
0.250 0.0868 0.00521 0.00130 -0.0249 0.7335 1.0000
0.500 0.1143 0.00532 0.00126 -0.0247 0.7203 1.0000
0.750 0.1418 0.00544 0.00124 -0.0245 0.7083 1.0000
1.000 0.1695 0.00554 0.00124 -0.0243 0.6959 1.0000
1.250 0.1973 0.00559 0.00122 -0.0242 0.6825 1.0000
1.500 0.2252 0.00563 0.00119 -0.0240 0.6681 1.0000
1.750 0.2531 0.00567 0.00116 -0.0239 0.6518 1.0000
2.000 0.2809 0.00571 0.00114 -0.0237 0.6327 1.0000
2.250 0.3085 0.00580 0.00112 -0.0236 0.6115 1.0000
2.500 0.3361 0.00589 0.00113 -0.0234 0.5867 1.0000
2.750 0.3637 0.00602 0.00115 -0.0232 0.5601 1.0000
3.000 0.3912 0.00617 0.00118 -0.0231 0.5314 1.0000
3.250 0.4186 0.00635 0.00124 -0.0229 0.5010 1.0000
3.500 0.4460 0.00654 0.00133 -0.0228 0.4695 1.0000
3.750 0.4734 0.00676 0.00142 -0.0227 0.4355 1.0000
4.000 0.5007 0.00701 0.00153 -0.0226 0.4021 1.0000
4.250 0.5279 0.00727 0.00166 -0.0225 0.3662 1.0000
4.500 0.5551 0.00755 0.00184 -0.0225 0.3325 1.0000
4.750 0.5823 0.00785 0.00201 -0.0224 0.2957 1.0000
5.000 0.6093 0.00818 0.00221 -0.0224 0.2620 1.0000
5.250 0.6363 0.00853 0.00243 -0.0223 0.2278 1.0000
5.500 0.6632 0.00890 0.00270 -0.0223 0.1966 1.0000
5.750 0.6901 0.00927 0.00298 -0.0222 0.1699 1.0000
6.000 0.7169 0.00964 0.00327 -0.0221 0.1461 1.0000
6.250 0.7436 0.01005 0.00360 -0.0221 0.1268 1.0000
6.500 0.7703 0.01040 0.00394 -0.0220 0.1100 1.0000
6.750 0.7970 0.01079 0.00430 -0.0219 0.0951 1.0000
7.000 0.8235 0.01120 0.00469 -0.0218 0.0814 1.0000
7.250 0.8499 0.01163 0.00510 -0.0217 0.0689 1.0000
7.500 0.8761 0.01210 0.00557 -0.0215 0.0576 1.0000
7.750 0.9020 0.01264 0.00613 -0.0214 0.0475 1.0000
8.000 0.9273 0.01336 0.00683 -0.0211 0.0383 1.0000
8.250 0.9534 0.01381 0.00733 -0.0210 0.0321 1.0000
8.500 0.9781 0.01465 0.00825 -0.0207 0.0266 1.0000
8.750 1.0032 0.01532 0.00898 -0.0204 0.0226 1.0000
9.000 1.0257 0.01669 0.01048 -0.0199 0.0191 1.0000
9.250 1.0508 0.01727 0.01118 -0.0196 0.0169 1.0000
9.500 1.0746 0.01813 0.01213 -0.0192 0.0150 1.0000
9.750 1.0920 0.02062 0.01484 -0.0183 0.0131 1.0000
10.000 1.1137 0.02197 0.01639 -0.0177 0.0124 1.0000
10.250 1.1356 0.02317 0.01776 -0.0172 0.0116 1.0000
10.500 1.1573 0.02424 0.01898 -0.0168 0.0105 1.0000
10.750 1.1785 0.02525 0.02010 -0.0164 0.0097 1.0000
11.000 1.1960 0.02702 0.02202 -0.0158 0.0091 1.0000
11.250 1.2047 0.03053 0.02588 -0.0148 0.0085 1.0000
11.750 1.2096 0.03850 0.03468 -0.0129 0.0080 1.0000
12.000 1.2120 0.04152 0.03799 -0.0124 0.0079 1.0000
12.250 1.2045 0.04501 0.04174 -0.0119 0.0078 1.0000
12.500 1.1913 0.04968 0.04664 -0.0142 0.0078 1.0000
12.750 1.1762 0.05606 0.05324 -0.0194 0.0078 1.0000
13.000 1.1593 0.06370 0.06108 -0.0257 0.0078 1.0000
13.250 1.1376 0.07303 0.07058 -0.0330 0.0079 1.0000
13.500 1.1101 0.08393 0.08162 -0.0405 0.0081 1.0000
13.750 0.9886 0.07568 0.07327 -0.0237 0.0084 1.0000
14.000 0.9717 0.08311 0.08079 -0.0267 0.0085 1.0000
14.250 0.9544 0.09067 0.08843 -0.0297 0.0087 1.0000
14.500 0.9324 0.09933 0.09719 -0.0333 0.0088 1.0000
|
Polar data table (+)
Polar graphs
<< Back to AG46c -03f (ag46c03-il)