AG04 (ag04-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG04 (ag04-il) Reynolds number: 1,000,000 Max Cl/Cd: 89.96 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag04-il-1000000.txt Download as CSV file: xf-ag04-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.6085 0.12510 0.12349 0.0305 1.0000 0.0076
-10.000 -0.6039 0.12117 0.11957 0.0288 1.0000 0.0077
-9.750 -0.5997 0.11717 0.11558 0.0271 1.0000 0.0078
-6.250 -0.5091 0.01760 0.01377 -0.0373 1.0000 0.0052
-6.000 -0.4843 0.01554 0.01141 -0.0371 1.0000 0.0055
-5.750 -0.4583 0.01452 0.01024 -0.0370 1.0000 0.0059
-5.500 -0.4319 0.01365 0.00924 -0.0368 1.0000 0.0064
-5.250 -0.4055 0.01272 0.00816 -0.0365 1.0000 0.0069
-5.000 -0.3790 0.01177 0.00707 -0.0361 1.0000 0.0072
-4.750 -0.3525 0.01094 0.00610 -0.0358 1.0000 0.0074
-4.500 -0.3260 0.01023 0.00529 -0.0354 1.0000 0.0077
-4.250 -0.2998 0.00954 0.00450 -0.0350 1.0000 0.0081
-4.000 -0.2737 0.00859 0.00341 -0.0345 1.0000 0.0089
-3.750 -0.2474 0.00809 0.00285 -0.0341 1.0000 0.0099
-3.500 -0.2213 0.00776 0.00249 -0.0336 1.0000 0.0118
-3.250 -0.1951 0.00732 0.00201 -0.0330 1.0000 0.0177
-3.000 -0.1606 0.00694 0.00171 -0.0345 0.9964 0.0366
-2.750 -0.1251 0.00665 0.00153 -0.0362 0.9905 0.0632
-2.500 -0.0893 0.00639 0.00137 -0.0379 0.9818 0.0913
-2.250 -0.0556 0.00613 0.00123 -0.0392 0.9678 0.1279
-2.000 -0.0259 0.00593 0.00112 -0.0394 0.9471 0.1656
-1.750 0.0002 0.00575 0.00102 -0.0388 0.9222 0.2096
-1.500 0.0257 0.00559 0.00094 -0.0381 0.8950 0.2620
-1.250 0.0514 0.00544 0.00087 -0.0375 0.8648 0.3223
-1.000 0.0775 0.00533 0.00081 -0.0370 0.8331 0.3839
-0.750 0.1039 0.00518 0.00077 -0.0366 0.8004 0.4599
-0.500 0.1305 0.00504 0.00075 -0.0363 0.7675 0.5422
-0.250 0.1566 0.00478 0.00074 -0.0359 0.7354 0.6634
0.250 0.2116 0.00415 0.00072 -0.0351 0.6727 1.0000
0.500 0.2391 0.00429 0.00072 -0.0350 0.6410 1.0000
0.750 0.2666 0.00444 0.00073 -0.0348 0.6099 1.0000
1.000 0.2941 0.00459 0.00074 -0.0346 0.5778 1.0000
1.250 0.3217 0.00475 0.00077 -0.0345 0.5452 1.0000
1.500 0.3493 0.00492 0.00080 -0.0344 0.5127 1.0000
1.750 0.3768 0.00510 0.00086 -0.0343 0.4794 1.0000
2.000 0.4044 0.00528 0.00091 -0.0342 0.4470 1.0000
2.250 0.4319 0.00549 0.00098 -0.0341 0.4143 1.0000
2.500 0.4594 0.00569 0.00106 -0.0340 0.3829 1.0000
2.750 0.4869 0.00590 0.00117 -0.0339 0.3530 1.0000
3.000 0.5144 0.00612 0.00127 -0.0338 0.3229 1.0000
3.250 0.5418 0.00633 0.00139 -0.0338 0.2958 1.0000
3.500 0.5692 0.00656 0.00151 -0.0337 0.2684 1.0000
3.750 0.5966 0.00679 0.00166 -0.0336 0.2440 1.0000
4.000 0.6238 0.00705 0.00182 -0.0335 0.2187 1.0000
4.250 0.6511 0.00730 0.00198 -0.0334 0.1956 1.0000
4.500 0.6782 0.00756 0.00217 -0.0333 0.1728 1.0000
4.750 0.7053 0.00784 0.00238 -0.0332 0.1518 1.0000
5.000 0.7323 0.00814 0.00260 -0.0331 0.1301 1.0000
5.250 0.7591 0.00846 0.00284 -0.0330 0.1095 1.0000
5.500 0.7858 0.00880 0.00310 -0.0329 0.0902 1.0000
5.750 0.8124 0.00917 0.00339 -0.0327 0.0722 1.0000
6.000 0.8389 0.00954 0.00372 -0.0325 0.0568 1.0000
6.250 0.8653 0.00994 0.00407 -0.0324 0.0437 1.0000
6.500 0.8915 0.01035 0.00444 -0.0322 0.0331 1.0000
6.750 0.9177 0.01077 0.00484 -0.0320 0.0251 1.0000
7.000 0.9435 0.01130 0.00536 -0.0317 0.0182 1.0000
7.250 0.9697 0.01168 0.00576 -0.0315 0.0151 1.0000
7.500 0.9949 0.01235 0.00649 -0.0311 0.0113 1.0000
7.750 1.0207 0.01278 0.00696 -0.0308 0.0095 1.0000
8.000 1.0444 0.01381 0.00810 -0.0302 0.0071 1.0000
8.250 1.0700 0.01421 0.00855 -0.0299 0.0064 1.0000
8.500 1.0950 0.01474 0.00913 -0.0296 0.0055 1.0000
8.750 1.1186 0.01560 0.01007 -0.0291 0.0049 1.0000
9.000 1.1370 0.01760 0.01235 -0.0280 0.0043 1.0000
9.250 1.1604 0.01834 0.01321 -0.0275 0.0042 1.0000
9.500 1.1830 0.01923 0.01421 -0.0269 0.0040 1.0000
9.750 1.2046 0.02025 0.01537 -0.0262 0.0038 1.0000
10.000 1.2254 0.02136 0.01662 -0.0255 0.0036 1.0000
10.250 1.2457 0.02249 0.01789 -0.0248 0.0033 1.0000
10.500 1.2654 0.02362 0.01914 -0.0241 0.0031 1.0000
10.750 1.2843 0.02480 0.02044 -0.0233 0.0029 1.0000
11.000 1.2999 0.02641 0.02221 -0.0224 0.0027 1.0000
11.250 1.3072 0.02915 0.02523 -0.0208 0.0026 1.0000
11.500 1.3034 0.03311 0.02955 -0.0187 0.0025 1.0000
11.750 1.2952 0.03692 0.03369 -0.0166 0.0024 1.0000
12.000 1.2788 0.04059 0.03759 -0.0146 0.0024 1.0000
12.250 1.2632 0.04517 0.04240 -0.0156 0.0024 1.0000
12.500 1.2506 0.05087 0.04830 -0.0195 0.0024 1.0000
12.750 1.2378 0.05798 0.05559 -0.0254 0.0024 1.0000
13.000 1.2228 0.06633 0.06410 -0.0320 0.0024 1.0000
13.250 1.2104 0.07414 0.07202 -0.0374 0.0025 1.0000
13.500 1.1955 0.08223 0.08021 -0.0424 0.0025 1.0000
13.750 1.1802 0.09019 0.08825 -0.0468 0.0025 1.0000
14.000 1.1626 0.09844 0.09658 -0.0510 0.0025 1.0000
14.250 1.1452 0.10670 0.10490 -0.0550 0.0026 1.0000
14.500 1.1251 0.11557 0.11385 -0.0593 0.0026 1.0000
14.750 1.1005 0.12578 0.12413 -0.0641 0.0027 1.0000
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Polar data table (+)
Polar graphs
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