AG45c -03f (ag45c03-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG45c -03f (ag45c03-il) Reynolds number: 500,000 Max Cl/Cd: 83.02 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag45c03-il-500000.txt Download as CSV file: xf-ag45c03-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: AG45c -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 -0.5818 0.11127 0.10910 0.0269 1.0000 0.0123
-8.000 -0.5866 0.10519 0.10307 0.0250 1.0000 0.0126
-7.750 -0.5831 0.10156 0.09945 0.0240 1.0000 0.0128
-7.500 -0.5785 0.09814 0.09604 0.0228 1.0000 0.0130
-7.250 -0.5737 0.09472 0.09264 0.0214 1.0000 0.0133
-7.000 -0.5692 0.09115 0.08909 0.0195 1.0000 0.0135
-6.750 -0.5650 0.08742 0.08538 0.0171 1.0000 0.0137
-6.500 -0.5594 0.08335 0.08133 0.0134 1.0000 0.0140
-6.250 -0.5493 0.07861 0.07661 0.0079 1.0000 0.0143
-6.000 -0.5364 0.07344 0.07142 0.0016 1.0000 0.0147
-5.750 -0.5207 0.06784 0.06580 -0.0051 1.0000 0.0152
-5.500 -0.5020 0.06183 0.05973 -0.0118 1.0000 0.0158
-5.250 -0.4795 0.05527 0.05305 -0.0183 1.0000 0.0168
-5.000 -0.4483 0.04908 0.04662 -0.0233 1.0000 0.0180
-4.750 -0.4250 0.04348 0.04073 -0.0263 1.0000 0.0182
-4.500 -0.4107 0.03372 0.03051 -0.0302 1.0000 0.0193
-4.250 -0.3884 0.03142 0.02814 -0.0309 1.0000 0.0202
-4.000 -0.3642 0.02894 0.02548 -0.0315 1.0000 0.0215
-3.500 -0.3089 0.01964 0.01490 -0.0312 1.0000 0.0190
-3.250 -0.2817 0.01776 0.01275 -0.0310 1.0000 0.0188
-3.000 -0.2547 0.01488 0.00961 -0.0306 1.0000 0.0164
-2.750 -0.2271 0.01278 0.00722 -0.0301 1.0000 0.0152
-2.500 -0.1998 0.01143 0.00570 -0.0297 1.0000 0.0150
-2.250 -0.1595 0.01032 0.00447 -0.0321 0.9583 0.0156
-2.000 -0.1280 0.00983 0.00367 -0.0322 0.8466 0.0172
-1.750 -0.1037 0.00936 0.00283 -0.0309 0.7866 0.0205
-1.500 -0.0769 0.00910 0.00239 -0.0305 0.7602 0.0287
-1.000 -0.0224 0.00824 0.00182 -0.0302 0.7294 0.1541
-0.750 0.0049 0.00792 0.00173 -0.0302 0.7175 0.2429
-0.500 0.0319 0.00748 0.00165 -0.0302 0.7068 0.3726
-0.250 0.0578 0.00675 0.00162 -0.0301 0.6959 0.5917
0.000 0.0793 0.00601 0.00164 -0.0284 0.6848 0.8160
0.250 0.1100 0.00567 0.00154 -0.0281 0.6728 0.9894
0.500 0.1396 0.00569 0.00144 -0.0283 0.6600 1.0000
0.750 0.1677 0.00572 0.00137 -0.0282 0.6462 1.0000
1.000 0.1957 0.00576 0.00130 -0.0280 0.6313 1.0000
1.250 0.2237 0.00582 0.00126 -0.0279 0.6153 1.0000
1.500 0.2516 0.00589 0.00122 -0.0278 0.5986 1.0000
1.750 0.2795 0.00598 0.00120 -0.0277 0.5814 1.0000
2.000 0.3074 0.00608 0.00119 -0.0276 0.5640 1.0000
2.250 0.3354 0.00618 0.00121 -0.0275 0.5460 1.0000
2.500 0.3633 0.00629 0.00123 -0.0274 0.5277 1.0000
2.750 0.3911 0.00643 0.00127 -0.0273 0.5099 1.0000
3.000 0.4190 0.00655 0.00132 -0.0272 0.4919 1.0000
3.250 0.4469 0.00668 0.00139 -0.0272 0.4736 1.0000
3.500 0.4746 0.00683 0.00146 -0.0271 0.4551 1.0000
3.750 0.5024 0.00699 0.00154 -0.0270 0.4365 1.0000
4.000 0.5302 0.00714 0.00163 -0.0270 0.4170 1.0000
4.250 0.5579 0.00732 0.00176 -0.0269 0.3967 1.0000
4.500 0.5856 0.00750 0.00188 -0.0269 0.3760 1.0000
4.750 0.6131 0.00772 0.00201 -0.0268 0.3542 1.0000
5.000 0.6407 0.00792 0.00217 -0.0268 0.3320 1.0000
5.250 0.6681 0.00817 0.00236 -0.0268 0.3089 1.0000
5.500 0.6954 0.00844 0.00255 -0.0267 0.2856 1.0000
5.750 0.7226 0.00872 0.00277 -0.0267 0.2613 1.0000
6.000 0.7497 0.00903 0.00300 -0.0267 0.2376 1.0000
6.250 0.7767 0.00938 0.00328 -0.0266 0.2135 1.0000
6.500 0.8035 0.00973 0.00357 -0.0266 0.1905 1.0000
6.750 0.8303 0.01010 0.00388 -0.0265 0.1685 1.0000
7.000 0.8568 0.01053 0.00423 -0.0265 0.1480 1.0000
7.250 0.8834 0.01092 0.00458 -0.0264 0.1292 1.0000
7.500 0.9097 0.01136 0.00499 -0.0263 0.1117 1.0000
7.750 0.9357 0.01186 0.00543 -0.0262 0.0946 1.0000
8.000 0.9618 0.01232 0.00588 -0.0261 0.0796 1.0000
8.250 0.9876 0.01284 0.00637 -0.0260 0.0651 1.0000
8.500 1.0130 0.01343 0.00695 -0.0258 0.0520 1.0000
8.750 1.0381 0.01409 0.00760 -0.0256 0.0407 1.0000
9.000 1.0627 0.01485 0.00839 -0.0254 0.0321 1.0000
9.250 1.0860 0.01592 0.00949 -0.0250 0.0251 1.0000
9.500 1.1109 0.01651 0.01016 -0.0247 0.0215 1.0000
9.750 1.1316 0.01801 0.01177 -0.0242 0.0175 1.0000
10.000 1.1555 0.01876 0.01263 -0.0238 0.0160 1.0000
10.250 1.1781 0.01971 0.01372 -0.0234 0.0143 1.0000
10.500 1.1983 0.02105 0.01515 -0.0228 0.0128 1.0000
10.750 1.2143 0.02312 0.01742 -0.0219 0.0115 1.0000
11.000 1.2355 0.02409 0.01854 -0.0214 0.0107 1.0000
11.250 1.2541 0.02548 0.02008 -0.0208 0.0099 1.0000
11.500 1.2715 0.02692 0.02166 -0.0201 0.0093 1.0000
11.750 1.2872 0.02849 0.02337 -0.0194 0.0088 1.0000
12.000 1.2977 0.03072 0.02575 -0.0185 0.0083 1.0000
12.250 1.2970 0.03440 0.02972 -0.0170 0.0079 1.0000
12.750 1.2820 0.04165 0.03755 -0.0147 0.0076 1.0000
13.000 1.2770 0.04529 0.04141 -0.0162 0.0075 1.0000
13.250 1.2707 0.04976 0.04608 -0.0190 0.0075 1.0000
13.500 1.2615 0.05493 0.05144 -0.0221 0.0074 1.0000
13.750 1.2497 0.06079 0.05750 -0.0259 0.0074 1.0000
14.000 1.2353 0.06733 0.06421 -0.0300 0.0074 1.0000
14.250 1.2181 0.07456 0.07161 -0.0344 0.0074 1.0000
14.500 1.1978 0.08254 0.07974 -0.0392 0.0074 1.0000
14.750 1.1763 0.09100 0.08834 -0.0441 0.0075 1.0000
15.000 1.1514 0.10031 0.09775 -0.0492 0.0076 1.0000
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Polar data table (+)
Polar graphs
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