AG45c -03f (ag45c03-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG45c -03f (ag45c03-il) Reynolds number: 100,000 Max Cl/Cd: 46.03 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag45c03-il-100000.txt Download as CSV file: xf-ag45c03-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.5641 0.11150 0.10683 0.0242 1.0000 0.0730
-7.500 -0.5679 0.10886 0.10427 0.0185 1.0000 0.0750
-7.250 -0.5730 0.10609 0.10160 0.0108 1.0000 0.0756
-7.000 -0.5585 0.10001 0.09552 0.0161 1.0000 0.0780
-6.750 -0.5483 0.09637 0.09189 0.0169 1.0000 0.0811
-6.500 -0.5436 0.09282 0.08836 0.0146 1.0000 0.0844
-6.250 -0.5387 0.08849 0.08409 0.0014 1.0000 0.0887
-6.000 -0.5301 0.08286 0.07844 -0.0041 1.0000 0.0906
-5.750 -0.5191 0.07967 0.07531 0.0012 1.0000 0.0938
-5.500 -0.5054 0.07551 0.07114 -0.0033 1.0000 0.0998
-5.250 -0.4900 0.06974 0.06528 -0.0121 1.0000 0.1052
-5.000 -0.4759 0.06651 0.06208 -0.0107 1.0000 0.1098
-4.750 -0.4560 0.06128 0.05670 -0.0179 1.0000 0.1193
-4.500 -0.4372 0.05796 0.05334 -0.0189 1.0000 0.1283
-4.250 -0.4185 0.05381 0.04914 -0.0208 1.0000 0.1363
-4.000 -0.3968 0.04998 0.04518 -0.0233 1.0000 0.1492
-3.750 -0.3747 0.04651 0.04162 -0.0249 1.0000 0.1635
-3.500 -0.3225 0.03458 0.02809 -0.0324 1.0000 0.0743
-3.250 -0.2928 0.02936 0.02220 -0.0327 1.0000 0.0601
-3.000 -0.2649 0.02636 0.01869 -0.0327 1.0000 0.0601
-2.750 -0.2363 0.02378 0.01562 -0.0325 1.0000 0.0606
-2.500 -0.2075 0.02135 0.01279 -0.0320 1.0000 0.0606
-2.250 -0.1787 0.01955 0.01062 -0.0313 1.0000 0.0625
-2.000 -0.1519 0.01772 0.00887 -0.0311 1.0000 0.0723
-1.750 -0.1248 0.01615 0.00733 -0.0305 1.0000 0.0844
-1.500 -0.0981 0.01479 0.00609 -0.0299 1.0000 0.1169
-1.250 -0.0732 0.01272 0.00505 -0.0297 1.0000 0.2687
-1.000 -0.0619 0.01031 0.00489 -0.0253 1.0000 0.7863
-0.750 -0.0201 0.00992 0.00438 -0.0272 1.0000 1.0000
-0.500 0.0047 0.00996 0.00420 -0.0272 1.0000 1.0000
-0.250 0.0267 0.01011 0.00416 -0.0271 1.0000 1.0000
0.000 0.0667 0.01033 0.00416 -0.0307 0.9859 1.0000
0.250 0.1231 0.01043 0.00403 -0.0367 0.9559 1.0000
0.500 0.1699 0.01050 0.00389 -0.0403 0.9217 1.0000
0.750 0.2059 0.01062 0.00382 -0.0414 0.8880 1.0000
1.000 0.2338 0.01080 0.00380 -0.0407 0.8573 1.0000
1.250 0.2589 0.01103 0.00383 -0.0395 0.8295 1.0000
1.500 0.2836 0.01130 0.00391 -0.0383 0.8038 1.0000
1.750 0.3084 0.01160 0.00405 -0.0372 0.7803 1.0000
2.000 0.3332 0.01194 0.00422 -0.0361 0.7584 1.0000
2.250 0.3584 0.01231 0.00445 -0.0352 0.7366 1.0000
2.500 0.3834 0.01270 0.00470 -0.0342 0.7165 1.0000
2.750 0.4089 0.01310 0.00501 -0.0335 0.6955 1.0000
3.000 0.4346 0.01343 0.00528 -0.0328 0.6748 1.0000
3.250 0.4604 0.01367 0.00550 -0.0321 0.6541 1.0000
3.500 0.4862 0.01387 0.00562 -0.0313 0.6351 1.0000
3.750 0.5122 0.01403 0.00576 -0.0307 0.6135 1.0000
4.000 0.5380 0.01419 0.00583 -0.0298 0.5939 1.0000
4.250 0.5641 0.01436 0.00600 -0.0292 0.5712 1.0000
4.500 0.5899 0.01456 0.00615 -0.0284 0.5497 1.0000
4.750 0.6159 0.01478 0.00634 -0.0277 0.5260 1.0000
5.000 0.6418 0.01503 0.00657 -0.0271 0.5015 1.0000
5.250 0.6676 0.01531 0.00679 -0.0264 0.4767 1.0000
5.500 0.6933 0.01563 0.00708 -0.0257 0.4512 1.0000
5.750 0.7189 0.01597 0.00737 -0.0251 0.4243 1.0000
6.000 0.7444 0.01635 0.00772 -0.0245 0.3962 1.0000
6.250 0.7698 0.01678 0.00813 -0.0240 0.3667 1.0000
6.500 0.7950 0.01727 0.00864 -0.0235 0.3366 1.0000
6.750 0.8199 0.01785 0.00918 -0.0230 0.3065 1.0000
7.000 0.8446 0.01851 0.00980 -0.0225 0.2770 1.0000
7.250 0.8690 0.01927 0.01052 -0.0220 0.2488 1.0000
7.500 0.8931 0.02012 0.01137 -0.0215 0.2217 1.0000
7.750 0.9168 0.02108 0.01231 -0.0211 0.1963 1.0000
8.000 0.9401 0.02217 0.01333 -0.0206 0.1727 1.0000
8.250 0.9630 0.02329 0.01446 -0.0201 0.1495 1.0000
8.500 0.9855 0.02473 0.01599 -0.0195 0.1288 1.0000
8.750 1.0073 0.02611 0.01735 -0.0189 0.1099 1.0000
9.000 1.0288 0.02804 0.01928 -0.0183 0.0952 1.0000
9.250 1.0495 0.03002 0.02132 -0.0177 0.0819 1.0000
9.500 1.0704 0.03212 0.02383 -0.0167 0.0726 1.0000
9.750 1.0892 0.03470 0.02668 -0.0160 0.0645 1.0000
10.000 1.1080 0.03727 0.02941 -0.0153 0.0590 1.0000
10.250 1.1215 0.04146 0.03405 -0.0144 0.0557 1.0000
10.500 1.1317 0.04484 0.03806 -0.0135 0.0519 1.0000
10.750 1.1427 0.04796 0.04145 -0.0128 0.0488 1.0000
11.000 1.1479 0.05213 0.04596 -0.0122 0.0475 1.0000
11.250 1.1464 0.05700 0.05120 -0.0118 0.0469 1.0000
11.500 1.1369 0.06208 0.05674 -0.0117 0.0469 1.0000
11.750 1.1137 0.06731 0.06234 -0.0124 0.0477 1.0000
12.000 1.0576 0.07759 0.07307 -0.0214 0.0507 1.0000
12.250 1.0203 0.08898 0.08459 -0.0311 0.0532 1.0000
12.500 0.9963 0.09904 0.09466 -0.0378 0.0554 1.0000
12.750 0.9796 0.10783 0.10342 -0.0424 0.0565 1.0000
13.000 0.9677 0.11578 0.11135 -0.0457 0.0572 1.0000
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Polar data table (+)
Polar graphs
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