AG03 (flat aft bottom) (ag03-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG03 (flat aft bottom) (ag03-il) Reynolds number: 500,000 Max Cl/Cd: 78.69 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag03-il-500000.txt Download as CSV file: xf-ag03-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5492 0.10620 0.10397 0.0179 1.0000 0.0104
-8.500 -0.5446 0.10234 0.10012 0.0156 1.0000 0.0108
-8.250 -0.5403 0.09841 0.09621 0.0127 1.0000 0.0111
-8.000 -0.5350 0.09453 0.09235 0.0097 1.0000 0.0113
-7.750 -0.5295 0.09072 0.08857 0.0068 1.0000 0.0114
-7.500 -0.5240 0.08668 0.08455 0.0033 1.0000 0.0115
-7.250 -0.5136 0.08195 0.07983 -0.0021 1.0000 0.0115
-7.000 -0.5006 0.07688 0.07476 -0.0079 1.0000 0.0116
-6.750 -0.4855 0.07156 0.06940 -0.0137 1.0000 0.0116
-6.500 -0.4687 0.06606 0.06385 -0.0190 1.0000 0.0116
-6.250 -0.4630 0.05792 0.05565 -0.0245 1.0000 0.0123
-6.000 -0.4467 0.05432 0.05198 -0.0267 1.0000 0.0128
-5.750 -0.4277 0.05053 0.04811 -0.0291 1.0000 0.0134
-5.500 -0.4066 0.04630 0.04375 -0.0315 1.0000 0.0144
-5.250 -0.3833 0.04165 0.03892 -0.0335 1.0000 0.0158
-5.000 -0.3513 0.03837 0.03536 -0.0339 1.0000 0.0181
-4.750 -0.3346 0.03039 0.02686 -0.0352 1.0000 0.0190
-4.500 -0.3152 0.02786 0.02426 -0.0353 1.0000 0.0203
-4.250 -0.2936 0.02674 0.02307 -0.0350 1.0000 0.0232
-4.000 -0.2660 0.02675 0.02279 -0.0335 1.0000 0.0274
-3.750 -0.2472 0.02107 0.01659 -0.0332 1.0000 0.0295
-3.500 -0.2253 0.01938 0.01483 -0.0325 1.0000 0.0312
-3.250 -0.1966 0.01418 0.00884 -0.0303 1.0000 0.0149
-3.000 -0.1703 0.01216 0.00643 -0.0290 1.0000 0.0122
-2.750 -0.1428 0.01145 0.00564 -0.0288 0.9992 0.0118
-2.500 -0.1043 0.01035 0.00445 -0.0308 0.9956 0.0116
-2.250 -0.0668 0.00914 0.00309 -0.0327 0.9908 0.0122
-2.000 -0.0276 0.00844 0.00231 -0.0348 0.9851 0.0161
-1.750 0.0088 0.00762 0.00188 -0.0367 0.9768 0.1132
-1.500 0.0439 0.00701 0.00174 -0.0385 0.9663 0.2433
-1.250 0.0739 0.00590 0.00160 -0.0395 0.9515 0.5410
-1.000 0.0926 0.00483 0.00160 -0.0368 0.9320 0.8624
-0.750 0.1372 0.00466 0.00148 -0.0397 0.9147 1.0000
-0.500 0.1622 0.00470 0.00138 -0.0387 0.8878 1.0000
-0.250 0.1872 0.00477 0.00128 -0.0377 0.8594 1.0000
0.000 0.2125 0.00486 0.00121 -0.0369 0.8297 1.0000
0.250 0.2382 0.00497 0.00115 -0.0361 0.7986 1.0000
0.500 0.2641 0.00510 0.00111 -0.0355 0.7672 1.0000
0.750 0.2903 0.00525 0.00109 -0.0349 0.7358 1.0000
1.000 0.3166 0.00541 0.00108 -0.0345 0.7042 1.0000
1.250 0.3431 0.00557 0.00109 -0.0340 0.6722 1.0000
1.500 0.3697 0.00574 0.00112 -0.0337 0.6399 1.0000
1.750 0.3963 0.00593 0.00116 -0.0333 0.6071 1.0000
2.000 0.4230 0.00612 0.00121 -0.0330 0.5728 1.0000
2.250 0.4497 0.00633 0.00128 -0.0328 0.5383 1.0000
2.500 0.4764 0.00655 0.00136 -0.0325 0.5035 1.0000
2.750 0.5031 0.00679 0.00145 -0.0323 0.4675 1.0000
3.000 0.5298 0.00705 0.00158 -0.0321 0.4314 1.0000
3.250 0.5565 0.00731 0.00171 -0.0319 0.3964 1.0000
3.500 0.5831 0.00760 0.00186 -0.0317 0.3621 1.0000
3.750 0.6097 0.00788 0.00202 -0.0316 0.3296 1.0000
4.000 0.6364 0.00817 0.00222 -0.0314 0.2999 1.0000
4.250 0.6630 0.00847 0.00242 -0.0313 0.2716 1.0000
4.500 0.6896 0.00878 0.00264 -0.0311 0.2430 1.0000
4.750 0.7161 0.00910 0.00288 -0.0310 0.2186 1.0000
5.000 0.7425 0.00944 0.00315 -0.0308 0.1939 1.0000
5.500 0.7950 0.01017 0.00373 -0.0305 0.1471 1.0000
5.750 0.8210 0.01058 0.00407 -0.0303 0.1254 1.0000
6.000 0.8467 0.01104 0.00445 -0.0301 0.1040 1.0000
6.250 0.8725 0.01150 0.00490 -0.0298 0.0873 1.0000
6.500 0.8981 0.01198 0.00536 -0.0296 0.0732 1.0000
6.750 0.9234 0.01251 0.00587 -0.0293 0.0621 1.0000
7.000 0.9481 0.01316 0.00651 -0.0289 0.0522 1.0000
7.250 0.9739 0.01355 0.00696 -0.0287 0.0458 1.0000
7.500 0.9983 0.01424 0.00772 -0.0282 0.0392 1.0000
7.750 1.0233 0.01476 0.00827 -0.0279 0.0332 1.0000
8.000 1.0470 0.01556 0.00917 -0.0274 0.0284 1.0000
8.250 1.0716 0.01610 0.00974 -0.0271 0.0238 1.0000
8.500 1.0936 0.01719 0.01096 -0.0264 0.0199 1.0000
8.750 1.1176 0.01783 0.01168 -0.0259 0.0168 1.0000
9.000 1.1363 0.01947 0.01345 -0.0249 0.0134 1.0000
9.250 1.1612 0.01982 0.01391 -0.0246 0.0113 1.0000
9.500 1.1809 0.02107 0.01523 -0.0239 0.0088 1.0000
9.750 1.2030 0.02187 0.01616 -0.0234 0.0074 1.0000
10.000 1.2242 0.02276 0.01714 -0.0228 0.0061 1.0000
10.250 1.2332 0.02563 0.02028 -0.0211 0.0050 1.0000
10.500 1.2516 0.02684 0.02168 -0.0202 0.0045 1.0000
10.750 1.2667 0.02843 0.02348 -0.0191 0.0040 1.0000
11.000 1.2807 0.02998 0.02519 -0.0181 0.0035 1.0000
11.250 1.2897 0.03200 0.02738 -0.0167 0.0032 1.0000
11.500 1.2849 0.03547 0.03115 -0.0146 0.0030 1.0000
11.750 1.2682 0.03933 0.03532 -0.0118 0.0029 1.0000
12.000 1.2510 0.04370 0.03996 -0.0114 0.0029 1.0000
12.250 1.2359 0.04890 0.04541 -0.0134 0.0029 1.0000
12.500 1.2197 0.05551 0.05226 -0.0178 0.0029 1.0000
12.750 1.2074 0.06234 0.05927 -0.0229 0.0029 1.0000
13.000 1.1945 0.06977 0.06687 -0.0283 0.0029 1.0000
13.250 1.1804 0.07756 0.07480 -0.0334 0.0029 1.0000
13.500 1.1673 0.08507 0.08242 -0.0380 0.0029 1.0000
13.750 1.1540 0.09252 0.08996 -0.0421 0.0030 1.0000
14.000 1.1397 0.10014 0.09767 -0.0461 0.0030 1.0000
14.250 1.1257 0.10769 0.10530 -0.0498 0.0031 1.0000
14.500 1.1074 0.11634 0.11405 -0.0541 0.0032 1.0000
14.750 1.0743 0.12903 0.12690 -0.0602 0.0035 1.0000
15.000 1.0174 0.14957 0.14760 -0.0699 0.0044 1.0000
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Polar data table (+)
Polar graphs
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