AG04 (ag04-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG04 (ag04-il) Reynolds number: 200,000 Max Cl/Cd: 56.97 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag04-il-200000-n5.txt Download as CSV file: xf-ag04-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5873 0.10945 0.10594 0.0203 1.0000 0.0117
-9.000 -0.5842 0.10552 0.10203 0.0188 1.0000 0.0114
-8.750 -0.5814 0.10145 0.09799 0.0170 1.0000 0.0111
-8.500 -0.5790 0.09725 0.09382 0.0149 1.0000 0.0109
-8.250 -0.5770 0.09293 0.08953 0.0125 1.0000 0.0107
-8.000 -0.5753 0.08848 0.08512 0.0098 1.0000 0.0105
-7.750 -0.5739 0.08383 0.08052 0.0065 1.0000 0.0103
-7.500 -0.5692 0.07849 0.07521 0.0012 1.0000 0.0102
-7.250 -0.5607 0.07229 0.06901 -0.0057 1.0000 0.0101
-7.000 -0.5487 0.06510 0.06179 -0.0137 1.0000 0.0099
-6.750 -0.5330 0.05722 0.05380 -0.0217 1.0000 0.0101
-6.500 -0.5148 0.04851 0.04486 -0.0287 1.0000 0.0105
-6.250 -0.4961 0.03917 0.03507 -0.0337 1.0000 0.0110
-6.000 -0.4759 0.03201 0.02724 -0.0361 1.0000 0.0115
-5.750 -0.4538 0.02705 0.02161 -0.0370 1.0000 0.0115
-5.500 -0.4297 0.02347 0.01742 -0.0371 1.0000 0.0116
-5.250 -0.4045 0.02085 0.01430 -0.0369 1.0000 0.0118
-5.000 -0.3788 0.01888 0.01194 -0.0365 1.0000 0.0122
-4.750 -0.3529 0.01718 0.00992 -0.0361 1.0000 0.0126
-4.500 -0.3275 0.01552 0.00808 -0.0357 1.0000 0.0137
-4.250 -0.3015 0.01458 0.00705 -0.0354 1.0000 0.0152
-4.000 -0.2752 0.01399 0.00636 -0.0350 1.0000 0.0186
-3.750 -0.2492 0.01301 0.00529 -0.0346 1.0000 0.0223
-3.500 -0.2229 0.01241 0.00459 -0.0342 1.0000 0.0284
-3.250 -0.1968 0.01178 0.00397 -0.0338 1.0000 0.0427
-3.000 -0.1709 0.01130 0.00357 -0.0335 1.0000 0.0664
-2.750 -0.1451 0.01088 0.00327 -0.0332 1.0000 0.0957
-2.500 -0.1194 0.01053 0.00303 -0.0329 1.0000 0.1295
-2.250 -0.0938 0.01019 0.00281 -0.0326 1.0000 0.1690
-2.000 -0.0681 0.00988 0.00265 -0.0323 1.0000 0.2165
-1.750 -0.0326 0.00950 0.00250 -0.0341 0.9904 0.2855
-1.500 0.0039 0.00912 0.00238 -0.0361 0.9768 0.3684
-1.250 0.0393 0.00870 0.00227 -0.0378 0.9606 0.4674
-1.000 0.0726 0.00819 0.00220 -0.0389 0.9420 0.5918
-0.750 0.0986 0.00751 0.00215 -0.0377 0.9192 0.7797
-0.500 0.1424 0.00719 0.00202 -0.0401 0.8946 1.0000
-0.250 0.1708 0.00724 0.00190 -0.0398 0.8631 1.0000
0.000 0.1972 0.00732 0.00182 -0.0390 0.8302 1.0000
0.250 0.2228 0.00743 0.00176 -0.0381 0.7959 1.0000
0.500 0.2483 0.00757 0.00171 -0.0372 0.7614 1.0000
0.750 0.2741 0.00773 0.00169 -0.0365 0.7270 1.0000
1.000 0.3000 0.00791 0.00168 -0.0358 0.6929 1.0000
1.250 0.3261 0.00810 0.00170 -0.0352 0.6587 1.0000
1.500 0.3523 0.00831 0.00174 -0.0346 0.6242 1.0000
1.750 0.3786 0.00853 0.00181 -0.0341 0.5894 1.0000
2.000 0.4050 0.00876 0.00188 -0.0337 0.5542 1.0000
2.250 0.4314 0.00900 0.00197 -0.0333 0.5188 1.0000
2.500 0.4578 0.00927 0.00208 -0.0330 0.4835 1.0000
2.750 0.4843 0.00954 0.00225 -0.0327 0.4488 1.0000
3.000 0.5107 0.00983 0.00241 -0.0324 0.4148 1.0000
3.250 0.5372 0.01013 0.00259 -0.0321 0.3821 1.0000
3.500 0.5637 0.01044 0.00280 -0.0319 0.3506 1.0000
3.750 0.5901 0.01078 0.00306 -0.0316 0.3196 1.0000
4.000 0.6165 0.01113 0.00332 -0.0314 0.2904 1.0000
4.250 0.6429 0.01149 0.00360 -0.0312 0.2623 1.0000
4.500 0.6691 0.01187 0.00391 -0.0310 0.2348 1.0000
4.750 0.6954 0.01226 0.00425 -0.0307 0.2088 1.0000
5.000 0.7215 0.01267 0.00464 -0.0305 0.1840 1.0000
5.250 0.7475 0.01312 0.00505 -0.0303 0.1595 1.0000
5.500 0.7733 0.01360 0.00548 -0.0301 0.1369 1.0000
5.750 0.7988 0.01413 0.00597 -0.0298 0.1137 1.0000
6.000 0.8243 0.01468 0.00653 -0.0295 0.0938 1.0000
6.250 0.8493 0.01533 0.00713 -0.0293 0.0744 1.0000
6.500 0.8742 0.01599 0.00781 -0.0289 0.0596 1.0000
6.750 0.8989 0.01672 0.00856 -0.0286 0.0468 1.0000
7.000 0.9228 0.01759 0.00945 -0.0281 0.0374 1.0000
7.250 0.9471 0.01837 0.01033 -0.0277 0.0299 1.0000
7.500 0.9702 0.01940 0.01153 -0.0271 0.0249 1.0000
7.750 0.9934 0.02035 0.01258 -0.0266 0.0204 1.0000
8.000 1.0148 0.02166 0.01403 -0.0259 0.0172 1.0000
8.250 1.0363 0.02294 0.01552 -0.0251 0.0151 1.0000
8.500 1.0575 0.02418 0.01690 -0.0244 0.0132 1.0000
8.750 1.0753 0.02603 0.01890 -0.0236 0.0114 1.0000
9.000 1.0952 0.02747 0.02060 -0.0227 0.0102 1.0000
9.250 1.1126 0.02938 0.02277 -0.0217 0.0094 1.0000
9.500 1.1286 0.03140 0.02505 -0.0207 0.0088 1.0000
9.750 1.1428 0.03352 0.02747 -0.0197 0.0083 1.0000
10.000 1.1544 0.03589 0.03010 -0.0186 0.0079 1.0000
10.250 1.1613 0.03879 0.03329 -0.0175 0.0076 1.0000
10.500 1.1616 0.04238 0.03721 -0.0161 0.0074 1.0000
10.750 1.1543 0.04641 0.04159 -0.0148 0.0073 1.0000
11.250 1.1268 0.05493 0.05064 -0.0151 0.0072 1.0000
11.500 1.1121 0.06069 0.05664 -0.0188 0.0072 1.0000
11.750 1.0979 0.06756 0.06375 -0.0242 0.0072 1.0000
12.000 1.0841 0.07531 0.07169 -0.0305 0.0073 1.0000
12.250 1.0692 0.08385 0.08039 -0.0369 0.0074 1.0000
12.500 1.0505 0.09366 0.09035 -0.0436 0.0075 1.0000
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