AG03 (flat aft bottom) (ag03-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG03 (flat aft bottom) (ag03-il) Reynolds number: 200,000 Max Cl/Cd: 58.24 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag03-il-200000-n5.txt Download as CSV file: xf-ag03-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG03 (flat aft bottom)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4441 0.12560 0.12218 0.0099 1.0000 0.0175
-10.500 -0.4444 0.12238 0.11898 0.0083 1.0000 0.0177
-9.750 -0.5605 0.12232 0.11874 0.0225 1.0000 0.0160
-6.500 -0.4745 0.06549 0.06206 -0.0215 1.0000 0.0187
-6.250 -0.4683 0.06461 0.06124 -0.0191 1.0000 0.0217
-6.000 -0.4501 0.06010 0.05665 -0.0232 1.0000 0.0236
-5.750 -0.4206 0.05197 0.04821 -0.0293 1.0000 0.0178
-5.500 -0.4082 0.04707 0.04322 -0.0311 1.0000 0.0152
-5.000 -0.3601 0.03348 0.02878 -0.0343 1.0000 0.0112
-4.750 -0.3382 0.02923 0.02413 -0.0346 1.0000 0.0109
-4.500 -0.3149 0.02550 0.01994 -0.0344 1.0000 0.0106
-4.250 -0.2908 0.02236 0.01631 -0.0339 1.0000 0.0104
-4.000 -0.2660 0.01984 0.01331 -0.0332 1.0000 0.0102
-3.750 -0.2409 0.01782 0.01087 -0.0324 1.0000 0.0102
-3.500 -0.2158 0.01622 0.00898 -0.0316 1.0000 0.0103
-3.250 -0.1908 0.01492 0.00749 -0.0308 1.0000 0.0105
-3.000 -0.1659 0.01387 0.00630 -0.0300 1.0000 0.0109
-2.750 -0.1409 0.01305 0.00537 -0.0293 1.0000 0.0115
-2.500 -0.1158 0.01220 0.00444 -0.0288 1.0000 0.0132
-2.250 -0.0780 0.01153 0.00371 -0.0308 0.9920 0.0216
-2.000 -0.0407 0.01076 0.00320 -0.0330 0.9828 0.0740
-1.750 -0.0050 0.01025 0.00293 -0.0348 0.9708 0.1433
-1.500 0.0300 0.00973 0.00270 -0.0365 0.9573 0.2328
-1.250 0.0624 0.00880 0.00250 -0.0379 0.9418 0.4518
-1.000 0.0847 0.00764 0.00247 -0.0361 0.9228 0.7775
-0.750 0.1336 0.00730 0.00230 -0.0395 0.9050 1.0000
-0.500 0.1628 0.00732 0.00215 -0.0394 0.8784 1.0000
-0.250 0.1899 0.00736 0.00201 -0.0388 0.8496 1.0000
0.000 0.2157 0.00744 0.00190 -0.0379 0.8194 1.0000
0.250 0.2412 0.00754 0.00182 -0.0371 0.7885 1.0000
0.500 0.2667 0.00766 0.00176 -0.0362 0.7567 1.0000
0.750 0.2923 0.00781 0.00171 -0.0355 0.7248 1.0000
1.000 0.3180 0.00798 0.00170 -0.0348 0.6932 1.0000
1.250 0.3439 0.00816 0.00170 -0.0342 0.6611 1.0000
1.500 0.3698 0.00835 0.00173 -0.0336 0.6285 1.0000
1.750 0.3958 0.00857 0.00179 -0.0331 0.5956 1.0000
2.000 0.4219 0.00878 0.00185 -0.0326 0.5620 1.0000
2.250 0.4479 0.00902 0.00193 -0.0322 0.5280 1.0000
2.500 0.4741 0.00928 0.00203 -0.0318 0.4939 1.0000
2.750 0.5002 0.00955 0.00216 -0.0314 0.4599 1.0000
3.000 0.5263 0.00983 0.00234 -0.0311 0.4264 1.0000
3.250 0.5524 0.01013 0.00251 -0.0308 0.3942 1.0000
3.500 0.5785 0.01044 0.00270 -0.0305 0.3630 1.0000
3.750 0.6045 0.01077 0.00292 -0.0303 0.3320 1.0000
4.000 0.6306 0.01111 0.00320 -0.0300 0.3023 1.0000
4.250 0.6566 0.01147 0.00347 -0.0298 0.2739 1.0000
4.500 0.6826 0.01184 0.00376 -0.0295 0.2463 1.0000
4.750 0.7084 0.01223 0.00409 -0.0293 0.2206 1.0000
5.000 0.7343 0.01263 0.00446 -0.0291 0.1972 1.0000
5.250 0.7600 0.01305 0.00484 -0.0288 0.1739 1.0000
5.500 0.7856 0.01351 0.00526 -0.0286 0.1520 1.0000
5.750 0.8111 0.01398 0.00571 -0.0283 0.1328 1.0000
6.000 0.8362 0.01451 0.00621 -0.0281 0.1138 1.0000
6.250 0.8614 0.01504 0.00678 -0.0278 0.0970 1.0000
6.500 0.8863 0.01562 0.00738 -0.0274 0.0838 1.0000
6.750 0.9109 0.01624 0.00803 -0.0271 0.0716 1.0000
7.000 0.9351 0.01692 0.00875 -0.0267 0.0620 1.0000
7.250 0.9591 0.01764 0.00952 -0.0263 0.0538 1.0000
7.500 0.9832 0.01833 0.01033 -0.0258 0.0465 1.0000
7.750 1.0058 0.01927 0.01136 -0.0253 0.0404 1.0000
8.000 1.0295 0.01999 0.01225 -0.0248 0.0350 1.0000
8.250 1.0509 0.02109 0.01341 -0.0242 0.0299 1.0000
8.500 1.0736 0.02198 0.01451 -0.0236 0.0260 1.0000
8.750 1.0945 0.02307 0.01568 -0.0230 0.0217 1.0000
9.000 1.1143 0.02443 0.01725 -0.0221 0.0192 1.0000
9.250 1.1348 0.02554 0.01855 -0.0214 0.0163 1.0000
9.500 1.1509 0.02727 0.02043 -0.0205 0.0136 1.0000
9.750 1.1681 0.02891 0.02237 -0.0194 0.0123 1.0000
10.000 1.1833 0.03074 0.02446 -0.0182 0.0109 1.0000
10.250 1.1994 0.03208 0.02596 -0.0175 0.0094 1.0000
10.500 1.2080 0.03446 0.02856 -0.0163 0.0082 1.0000
10.750 1.2163 0.03683 0.03127 -0.0149 0.0075 1.0000
11.000 1.2193 0.03960 0.03436 -0.0133 0.0070 1.0000
11.250 1.2167 0.04244 0.03749 -0.0116 0.0066 1.0000
11.500 1.2094 0.04558 0.04088 -0.0104 0.0064 1.0000
11.750 1.1996 0.04940 0.04494 -0.0107 0.0062 1.0000
12.000 1.1877 0.05425 0.05003 -0.0128 0.0061 1.0000
12.250 1.1737 0.06036 0.05638 -0.0168 0.0061 1.0000
12.500 1.1569 0.06792 0.06417 -0.0223 0.0061 1.0000
12.750 1.1368 0.07683 0.07329 -0.0287 0.0063 1.0000
13.000 1.1135 0.08680 0.08343 -0.0352 0.0065 1.0000
13.250 1.0884 0.09730 0.09407 -0.0415 0.0068 1.0000
13.500 1.0625 0.10806 0.10492 -0.0475 0.0072 1.0000
13.750 1.0378 0.11871 0.11562 -0.0529 0.0076 1.0000
14.000 1.0136 0.12946 0.12638 -0.0582 0.0080 1.0000
14.250 0.9912 0.14021 0.13713 -0.0633 0.0084 1.0000
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Polar data table (+)
Polar graphs
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