AG10 (ag10-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: AG10 (ag10-il) Reynolds number: 1,000,000 Max Cl/Cd: 79.57 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag10-il-1000000-n5.txt Download as CSV file: xf-ag10-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG10
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.6702 0.12557 0.12391 0.0428 1.0000 0.0044
-10.000 -0.6662 0.12192 0.12027 0.0413 1.0000 0.0045
-7.500 -0.6695 0.01896 0.01535 -0.0307 1.0000 0.0055
-7.250 -0.6441 0.01687 0.01292 -0.0310 1.0000 0.0057
-7.000 -0.6179 0.01541 0.01119 -0.0311 1.0000 0.0059
-6.750 -0.5912 0.01435 0.00992 -0.0311 1.0000 0.0061
-6.500 -0.5641 0.01348 0.00887 -0.0311 1.0000 0.0063
-6.250 -0.5368 0.01276 0.00801 -0.0310 1.0000 0.0063
-6.000 -0.5096 0.01175 0.00683 -0.0310 1.0000 0.0067
-5.750 -0.4821 0.01116 0.00615 -0.0310 1.0000 0.0069
-5.500 -0.4544 0.01069 0.00561 -0.0310 1.0000 0.0072
-5.250 -0.4266 0.01024 0.00510 -0.0309 1.0000 0.0074
-5.000 -0.3988 0.00982 0.00461 -0.0308 1.0000 0.0078
-4.750 -0.3709 0.00946 0.00419 -0.0308 1.0000 0.0082
-4.500 -0.3429 0.00916 0.00385 -0.0307 1.0000 0.0087
-4.250 -0.3150 0.00872 0.00337 -0.0306 1.0000 0.0094
-4.000 -0.2870 0.00842 0.00306 -0.0306 1.0000 0.0101
-3.750 -0.2589 0.00816 0.00277 -0.0305 1.0000 0.0109
-3.500 -0.2308 0.00792 0.00251 -0.0304 1.0000 0.0116
-3.250 -0.2028 0.00765 0.00223 -0.0303 1.0000 0.0130
-3.000 -0.1747 0.00745 0.00203 -0.0303 1.0000 0.0144
-2.750 -0.1466 0.00724 0.00183 -0.0302 1.0000 0.0162
-2.500 -0.1128 0.00709 0.00168 -0.0314 0.9698 0.0188
-2.250 -0.0850 0.00700 0.00154 -0.0311 0.9267 0.0220
-2.000 -0.0610 0.00702 0.00142 -0.0298 0.8746 0.0256
-1.750 -0.0354 0.00707 0.00130 -0.0291 0.8191 0.0306
-1.500 -0.0085 0.00714 0.00119 -0.0286 0.7610 0.0376
-1.250 0.0189 0.00723 0.00109 -0.0284 0.7000 0.0471
-1.000 0.0466 0.00732 0.00102 -0.0283 0.6384 0.0585
-0.750 0.0745 0.00742 0.00096 -0.0283 0.5789 0.0728
-0.500 0.1025 0.00752 0.00092 -0.0283 0.5239 0.0894
-0.250 0.1306 0.00758 0.00090 -0.0284 0.4773 0.1107
0.000 0.1587 0.00763 0.00088 -0.0284 0.4371 0.1386
0.250 0.1868 0.00763 0.00088 -0.0285 0.4040 0.1778
0.500 0.2150 0.00759 0.00090 -0.0286 0.3745 0.2357
0.750 0.2432 0.00749 0.00093 -0.0287 0.3480 0.3173
1.000 0.2715 0.00725 0.00097 -0.0290 0.3245 0.4536
1.250 0.2927 0.00586 0.00098 -0.0275 0.3047 1.0000
1.500 0.3209 0.00600 0.00102 -0.0275 0.2834 1.0000
1.750 0.3490 0.00615 0.00107 -0.0274 0.2622 1.0000
2.000 0.3771 0.00631 0.00113 -0.0274 0.2423 1.0000
2.250 0.4052 0.00646 0.00120 -0.0274 0.2223 1.0000
2.500 0.4332 0.00664 0.00129 -0.0273 0.2018 1.0000
2.750 0.4612 0.00682 0.00138 -0.0273 0.1829 1.0000
3.000 0.4892 0.00701 0.00149 -0.0273 0.1639 1.0000
3.250 0.5171 0.00721 0.00162 -0.0272 0.1453 1.0000
3.500 0.5449 0.00743 0.00175 -0.0272 0.1272 1.0000
3.750 0.5727 0.00765 0.00190 -0.0272 0.1104 1.0000
4.000 0.6004 0.00789 0.00206 -0.0271 0.0932 1.0000
4.250 0.6280 0.00817 0.00226 -0.0271 0.0760 1.0000
4.500 0.6556 0.00844 0.00247 -0.0270 0.0609 1.0000
4.750 0.6831 0.00874 0.00269 -0.0269 0.0471 1.0000
5.000 0.7105 0.00903 0.00293 -0.0269 0.0368 1.0000
5.250 0.7378 0.00935 0.00321 -0.0268 0.0277 1.0000
5.500 0.7651 0.00968 0.00350 -0.0267 0.0207 1.0000
5.750 0.7923 0.00999 0.00380 -0.0266 0.0164 1.0000
6.000 0.8195 0.01030 0.00412 -0.0265 0.0134 1.0000
6.250 0.8466 0.01064 0.00447 -0.0263 0.0113 1.0000
6.500 0.8735 0.01099 0.00483 -0.0262 0.0097 1.0000
6.750 0.9004 0.01138 0.00526 -0.0260 0.0087 1.0000
7.000 0.9272 0.01174 0.00566 -0.0259 0.0079 1.0000
7.250 0.9537 0.01215 0.00610 -0.0257 0.0071 1.0000
7.500 0.9800 0.01266 0.00666 -0.0255 0.0064 1.0000
7.750 1.0063 0.01309 0.00716 -0.0253 0.0062 1.0000
8.000 1.0324 0.01357 0.00771 -0.0251 0.0059 1.0000
8.250 1.0583 0.01409 0.00829 -0.0248 0.0056 1.0000
8.500 1.0839 0.01463 0.00890 -0.0246 0.0053 1.0000
8.750 1.1093 0.01521 0.00956 -0.0243 0.0051 1.0000
9.000 1.1343 0.01586 0.01028 -0.0240 0.0049 1.0000
9.250 1.1586 0.01664 0.01117 -0.0237 0.0047 1.0000
9.500 1.1817 0.01774 0.01239 -0.0233 0.0045 1.0000
9.750 1.2056 0.01849 0.01326 -0.0229 0.0044 1.0000
10.000 1.2291 0.01931 0.01421 -0.0225 0.0043 1.0000
10.250 1.2520 0.02021 0.01523 -0.0220 0.0042 1.0000
10.500 1.2742 0.02121 0.01637 -0.0216 0.0041 1.0000
10.750 1.2956 0.02231 0.01762 -0.0210 0.0040 1.0000
11.000 1.3161 0.02352 0.01900 -0.0204 0.0039 1.0000
11.250 1.3356 0.02484 0.02048 -0.0198 0.0038 1.0000
11.500 1.3539 0.02629 0.02210 -0.0191 0.0038 1.0000
11.750 1.3707 0.02788 0.02388 -0.0184 0.0037 1.0000
12.000 1.3856 0.02965 0.02584 -0.0176 0.0036 1.0000
12.250 1.3984 0.03160 0.02799 -0.0167 0.0036 1.0000
12.500 1.4082 0.03381 0.03041 -0.0158 0.0035 1.0000
12.750 1.4143 0.03628 0.03309 -0.0148 0.0035 1.0000
13.000 1.4146 0.03921 0.03623 -0.0139 0.0034 1.0000
13.250 1.4038 0.04252 0.03973 -0.0126 0.0034 1.0000
13.500 1.3830 0.04864 0.04609 -0.0163 0.0034 1.0000
13.750 1.3471 0.06517 0.06293 -0.0328 0.0035 1.0000
14.000 1.2942 0.08151 0.07943 -0.0432 0.0036 1.0000
14.250 1.2435 0.09603 0.09406 -0.0510 0.0036 1.0000
|
Polar data table (+)
Polar graphs
<< Back to AG10 (ag10-il)