AG04 (ag04-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG04 (ag04-il) Reynolds number: 50,000 Max Cl/Cd: 32 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag04-il-50000.txt Download as CSV file: xf-ag04-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: AG04
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5714 0.11486 0.10829 0.0200 1.0000 0.1872
-8.250 -0.5585 0.10997 0.10337 0.0208 1.0000 0.1952
-8.000 -0.5711 0.10880 0.10238 0.0167 1.0000 0.2019
-7.750 -0.5520 0.10328 0.09680 0.0187 1.0000 0.2122
-7.500 -0.5501 0.09977 0.09337 0.0174 1.0000 0.2197
-7.250 -0.5586 0.09807 0.09178 0.0125 1.0000 0.2299
-7.000 -0.5422 0.09312 0.08685 0.0152 1.0000 0.2415
-6.750 -0.5331 0.08914 0.08291 0.0149 1.0000 0.2527
-6.500 -0.5258 0.08545 0.07928 0.0138 1.0000 0.2659
-6.250 -0.5188 0.08194 0.07582 0.0122 1.0000 0.2821
-6.000 -0.5137 0.07854 0.07248 0.0091 1.0000 0.3007
-5.750 -0.4996 0.07463 0.06860 0.0120 1.0000 0.3213
-5.500 -0.4906 0.07139 0.06542 0.0129 1.0000 0.3518
-5.250 -0.4822 0.06810 0.06219 0.0143 1.0000 0.3855
-5.000 -0.4046 0.04724 0.03970 -0.0336 1.0000 0.1317
-4.750 -0.3800 0.04242 0.03459 -0.0351 1.0000 0.1276
-4.500 -0.3490 0.03688 0.02803 -0.0377 1.0000 0.1186
-4.250 -0.3212 0.03288 0.02346 -0.0381 1.0000 0.1181
-4.000 -0.2951 0.02996 0.02030 -0.0379 1.0000 0.1275
-3.750 -0.2672 0.02718 0.01710 -0.0377 1.0000 0.1397
-3.500 -0.2391 0.02486 0.01428 -0.0372 1.0000 0.1614
-3.250 -0.2124 0.02271 0.01214 -0.0364 1.0000 0.1924
-3.000 -0.1861 0.02095 0.01042 -0.0355 1.0000 0.2448
-2.750 -0.1609 0.01936 0.00915 -0.0345 1.0000 0.3187
-2.500 -0.1363 0.01769 0.00803 -0.0332 1.0000 0.4343
-2.250 -0.1217 0.01538 0.00715 -0.0289 1.0000 0.6613
-2.000 -0.0747 0.01413 0.00581 -0.0308 1.0000 1.0000
-1.750 -0.0489 0.01410 0.00531 -0.0306 1.0000 1.0000
-1.500 -0.0239 0.01409 0.00494 -0.0302 1.0000 1.0000
-1.250 0.0006 0.01411 0.00467 -0.0298 1.0000 1.0000
-1.000 0.0249 0.01414 0.00443 -0.0293 1.0000 1.0000
-0.750 0.0489 0.01420 0.00429 -0.0288 1.0000 1.0000
-0.500 0.0727 0.01428 0.00422 -0.0283 1.0000 1.0000
-0.250 0.0962 0.01439 0.00420 -0.0278 1.0000 1.0000
0.000 0.1195 0.01453 0.00423 -0.0274 1.0000 1.0000
0.250 0.1424 0.01471 0.00433 -0.0270 1.0000 1.0000
0.500 0.1649 0.01494 0.00451 -0.0266 1.0000 1.0000
0.750 0.1872 0.01523 0.00477 -0.0264 1.0000 1.0000
1.000 0.2092 0.01558 0.00512 -0.0263 1.0000 1.0000
1.250 0.2305 0.01603 0.00557 -0.0264 1.0000 1.0000
1.500 0.2510 0.01659 0.00615 -0.0266 1.0000 1.0000
1.750 0.2707 0.01728 0.00688 -0.0272 1.0000 1.0000
2.000 0.2893 0.01814 0.00780 -0.0280 1.0000 1.0000
2.250 0.3729 0.01899 0.00892 -0.0403 0.9623 1.0000
2.500 0.4605 0.01922 0.00948 -0.0513 0.9167 1.0000
2.750 0.5197 0.01912 0.00968 -0.0551 0.8700 1.0000
3.000 0.5542 0.01911 0.00980 -0.0539 0.8219 1.0000
3.250 0.5799 0.01918 0.00989 -0.0507 0.7756 1.0000
3.500 0.6010 0.01943 0.01011 -0.0472 0.7275 1.0000
3.750 0.6220 0.01977 0.01043 -0.0437 0.6798 1.0000
4.000 0.6433 0.02024 0.01081 -0.0407 0.6311 1.0000
4.250 0.6651 0.02080 0.01125 -0.0381 0.5830 1.0000
4.500 0.6873 0.02148 0.01180 -0.0357 0.5357 1.0000
4.750 0.7098 0.02226 0.01248 -0.0337 0.4886 1.0000
5.000 0.7325 0.02313 0.01328 -0.0318 0.4438 1.0000
5.250 0.7554 0.02413 0.01413 -0.0301 0.4005 1.0000
5.500 0.7781 0.02526 0.01515 -0.0286 0.3577 1.0000
5.750 0.8008 0.02653 0.01632 -0.0272 0.3164 1.0000
6.000 0.8231 0.02792 0.01765 -0.0258 0.2763 1.0000
6.250 0.8455 0.02967 0.01951 -0.0246 0.2396 1.0000
6.500 0.8681 0.03158 0.02143 -0.0234 0.2085 1.0000
6.750 0.8899 0.03356 0.02339 -0.0223 0.1802 1.0000
7.000 0.9113 0.03668 0.02702 -0.0212 0.1608 1.0000
7.250 0.9320 0.03910 0.02954 -0.0202 0.1416 1.0000
7.500 0.9494 0.04308 0.03412 -0.0192 0.1306 1.0000
7.750 0.9653 0.04742 0.03886 -0.0184 0.1232 1.0000
8.000 0.9817 0.05066 0.04220 -0.0176 0.1121 1.0000
8.250 0.9857 0.05658 0.04892 -0.0173 0.1105 1.0000
8.500 0.9861 0.06287 0.05574 -0.0176 0.1107 1.0000
8.750 0.9843 0.06922 0.06243 -0.0183 0.1115 1.0000
9.000 0.9829 0.07548 0.06889 -0.0191 0.1124 1.0000
9.250 0.9335 0.08642 0.08021 -0.0278 0.1228 1.0000
9.500 0.9219 0.09368 0.08748 -0.0318 0.1273 1.0000
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Polar data table (+)
Polar graphs
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