AG46c -03f (ag46c03-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG46c -03f (ag46c03-il) Reynolds number: 100,000 Max Cl/Cd: 44.53 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag46c03-il-100000.txt Download as CSV file: xf-ag46c03-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.5888 0.10860 0.10390 0.0239 1.0000 0.0688
-7.250 -0.5927 0.10594 0.10133 0.0170 1.0000 0.0700
-7.000 -0.5910 0.10225 0.09768 0.0062 1.0000 0.0705
-6.750 -0.5819 0.09652 0.09199 0.0145 1.0000 0.0723
-6.500 -0.5710 0.09284 0.08833 0.0164 1.0000 0.0753
-6.250 -0.5631 0.08901 0.08453 0.0131 1.0000 0.0792
-6.000 -0.5502 0.08401 0.07945 -0.0033 1.0000 0.0836
-5.750 -0.5424 0.07894 0.07446 -0.0016 1.0000 0.0860
-5.500 -0.5304 0.07583 0.07137 0.0001 1.0000 0.0922
-5.250 -0.5116 0.06986 0.06522 -0.0119 1.0000 0.0990
-5.000 -0.4998 0.06680 0.06227 -0.0082 1.0000 0.1044
-4.750 -0.4791 0.06160 0.05689 -0.0154 1.0000 0.1136
-4.500 -0.4606 0.05820 0.05346 -0.0162 1.0000 0.1225
-4.250 -0.4417 0.05397 0.04917 -0.0180 1.0000 0.1307
-4.000 -0.4200 0.05010 0.04513 -0.0205 1.0000 0.1437
-3.750 -0.3980 0.04661 0.04153 -0.0219 1.0000 0.1582
-3.500 -0.3752 0.04341 0.03823 -0.0230 1.0000 0.1751
-3.250 -0.3218 0.03305 0.02633 -0.0291 1.0000 0.0815
-3.000 -0.2905 0.02758 0.02011 -0.0293 1.0000 0.0619
-2.750 -0.2590 0.02501 0.01670 -0.0286 1.0000 0.0570
-2.500 -0.2325 0.02210 0.01360 -0.0286 1.0000 0.0610
-2.250 -0.2042 0.02010 0.01132 -0.0281 1.0000 0.0634
-2.000 -0.1758 0.01829 0.00925 -0.0274 1.0000 0.0670
-1.750 -0.1485 0.01678 0.00768 -0.0269 1.0000 0.0785
-1.500 -0.1216 0.01531 0.00626 -0.0262 1.0000 0.0958
-1.250 -0.0957 0.01380 0.00511 -0.0257 1.0000 0.1488
-1.000 -0.0795 0.01051 0.00438 -0.0234 1.0000 0.6615
-0.750 -0.0412 0.00973 0.00387 -0.0235 1.0000 1.0000
-0.500 -0.0150 0.00971 0.00355 -0.0232 1.0000 1.0000
-0.250 0.0110 0.00970 0.00334 -0.0230 1.0000 1.0000
0.000 0.0366 0.00972 0.00320 -0.0228 1.0000 1.0000
0.250 0.0617 0.00977 0.00313 -0.0226 1.0000 1.0000
0.500 0.0858 0.00987 0.00313 -0.0224 1.0000 1.0000
0.750 0.1080 0.01007 0.00326 -0.0224 1.0000 1.0000
1.000 0.1371 0.01037 0.00348 -0.0240 0.9950 1.0000
1.250 0.1962 0.01051 0.00355 -0.0307 0.9703 1.0000
1.500 0.2476 0.01060 0.00357 -0.0354 0.9414 1.0000
1.750 0.2880 0.01068 0.00360 -0.0374 0.9079 1.0000
2.000 0.3191 0.01082 0.00364 -0.0373 0.8747 1.0000
2.250 0.3446 0.01100 0.00373 -0.0359 0.8434 1.0000
2.500 0.3683 0.01124 0.00385 -0.0342 0.8127 1.0000
2.750 0.3918 0.01152 0.00401 -0.0326 0.7830 1.0000
3.000 0.4153 0.01185 0.00422 -0.0310 0.7541 1.0000
3.250 0.4390 0.01221 0.00450 -0.0295 0.7258 1.0000
3.500 0.4629 0.01261 0.00479 -0.0282 0.6973 1.0000
3.750 0.4874 0.01289 0.00502 -0.0270 0.6672 1.0000
4.000 0.5123 0.01303 0.00515 -0.0259 0.6352 1.0000
4.250 0.5371 0.01314 0.00522 -0.0248 0.6018 1.0000
4.500 0.5619 0.01329 0.00534 -0.0237 0.5654 1.0000
4.750 0.5867 0.01351 0.00545 -0.0226 0.5253 1.0000
5.000 0.6114 0.01384 0.00564 -0.0216 0.4803 1.0000
5.250 0.6359 0.01428 0.00591 -0.0208 0.4329 1.0000
5.500 0.6604 0.01484 0.00633 -0.0200 0.3825 1.0000
5.750 0.6848 0.01555 0.00681 -0.0194 0.3343 1.0000
6.000 0.7092 0.01637 0.00742 -0.0188 0.2901 1.0000
6.250 0.7337 0.01725 0.00814 -0.0183 0.2517 1.0000
6.500 0.7583 0.01823 0.00900 -0.0179 0.2200 1.0000
6.750 0.7828 0.01925 0.00999 -0.0174 0.1926 1.0000
7.000 0.8074 0.02036 0.01104 -0.0170 0.1691 1.0000
7.250 0.8319 0.02157 0.01232 -0.0165 0.1476 1.0000
7.500 0.8561 0.02287 0.01360 -0.0160 0.1295 1.0000
7.750 0.8800 0.02453 0.01519 -0.0156 0.1138 1.0000
8.000 0.9037 0.02621 0.01704 -0.0150 0.0996 1.0000
8.250 0.9274 0.02802 0.01902 -0.0145 0.0881 1.0000
8.500 0.9502 0.02986 0.02125 -0.0138 0.0776 1.0000
8.750 0.9715 0.03304 0.02482 -0.0130 0.0714 1.0000
9.000 0.9925 0.03488 0.02680 -0.0126 0.0635 1.0000
9.250 1.0085 0.03916 0.03171 -0.0118 0.0602 1.0000
9.500 1.0204 0.04402 0.03734 -0.0111 0.0584 1.0000
9.750 1.0269 0.04923 0.04320 -0.0108 0.0567 1.0000
10.000 1.0448 0.05080 0.04469 -0.0104 0.0516 1.0000
10.250 1.0468 0.05655 0.05074 -0.0105 0.0504 1.0000
10.500 1.0424 0.06201 0.05670 -0.0109 0.0508 1.0000
10.750 0.9817 0.07494 0.07044 -0.0181 0.0583 1.0000
11.000 0.9635 0.08219 0.07775 -0.0236 0.0599 1.0000
11.250 0.9499 0.08966 0.08522 -0.0286 0.0610 1.0000
11.500 0.9410 0.09671 0.09226 -0.0320 0.0617 1.0000
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Polar data table (+)
Polar graphs
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