AG03 (flat aft bottom) (ag03-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: AG03 (flat aft bottom) (ag03-il) Reynolds number: 100,000 Max Cl/Cd: 46.38 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag03-il-100000-n5.txt Download as CSV file: xf-ag03-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4289 0.09864 0.09403 0.0013 1.0000 0.0424
-8.500 -0.4267 0.09486 0.09029 0.0005 1.0000 0.0432
-8.250 -0.5407 0.10251 0.09776 0.0046 1.0000 0.0401
-8.000 -0.5331 0.09851 0.09377 0.0052 1.0000 0.0409
-7.750 -0.5272 0.09483 0.09012 0.0043 1.0000 0.0417
-7.500 -0.5222 0.09115 0.08649 0.0024 1.0000 0.0424
-7.250 -0.5154 0.08719 0.08256 -0.0007 1.0000 0.0430
-7.000 -0.5066 0.08293 0.07833 -0.0046 1.0000 0.0435
-6.750 -0.4960 0.07842 0.07382 -0.0090 1.0000 0.0438
-6.500 -0.4833 0.07365 0.06903 -0.0137 1.0000 0.0436
-6.250 -0.4635 0.06563 0.06083 -0.0211 1.0000 0.0259
-6.000 -0.4493 0.06106 0.05620 -0.0236 1.0000 0.0243
-5.750 -0.4315 0.05584 0.05084 -0.0270 1.0000 0.0226
-5.500 -0.4106 0.04970 0.04445 -0.0305 1.0000 0.0206
-5.000 -0.3625 0.03882 0.03274 -0.0338 1.0000 0.0179
-4.750 -0.3408 0.03481 0.02836 -0.0344 1.0000 0.0176
-4.500 -0.3176 0.03115 0.02426 -0.0346 1.0000 0.0174
-4.250 -0.2934 0.02788 0.02050 -0.0344 1.0000 0.0172
-4.000 -0.2683 0.02507 0.01719 -0.0340 1.0000 0.0173
-3.750 -0.2428 0.02269 0.01431 -0.0333 1.0000 0.0175
-3.500 -0.2172 0.02076 0.01199 -0.0325 1.0000 0.0179
-3.250 -0.1926 0.01899 0.01005 -0.0319 1.0000 0.0201
-3.000 -0.1678 0.01799 0.00894 -0.0313 1.0000 0.0240
-2.750 -0.1426 0.01680 0.00757 -0.0304 1.0000 0.0272
-2.500 -0.1181 0.01569 0.00647 -0.0297 1.0000 0.0358
-2.250 -0.0931 0.01470 0.00546 -0.0291 1.0000 0.0551
-2.000 -0.0681 0.01385 0.00482 -0.0286 1.0000 0.1057
-1.750 -0.0432 0.01312 0.00444 -0.0283 1.0000 0.1880
-1.500 -0.0185 0.01208 0.00416 -0.0283 1.0000 0.3809
-1.250 0.0123 0.01033 0.00405 -0.0274 1.0000 1.0000
-1.000 0.0356 0.01040 0.00386 -0.0267 1.0000 1.0000
-0.750 0.0766 0.01046 0.00367 -0.0296 0.9873 1.0000
-0.500 0.1197 0.01052 0.00352 -0.0328 0.9719 1.0000
-0.250 0.1608 0.01056 0.00338 -0.0355 0.9543 1.0000
0.000 0.1986 0.01059 0.00328 -0.0374 0.9329 1.0000
0.250 0.2347 0.01062 0.00320 -0.0388 0.9098 1.0000
0.500 0.2678 0.01065 0.00313 -0.0395 0.8838 1.0000
0.750 0.2977 0.01071 0.00306 -0.0394 0.8551 1.0000
1.000 0.3255 0.01078 0.00302 -0.0388 0.8244 1.0000
1.250 0.3520 0.01089 0.00300 -0.0380 0.7926 1.0000
1.500 0.3777 0.01102 0.00301 -0.0370 0.7599 1.0000
1.750 0.4032 0.01118 0.00306 -0.0361 0.7259 1.0000
2.000 0.4289 0.01137 0.00311 -0.0352 0.6918 1.0000
2.250 0.4543 0.01159 0.00319 -0.0343 0.6564 1.0000
2.500 0.4797 0.01183 0.00330 -0.0335 0.6208 1.0000
2.750 0.5050 0.01210 0.00344 -0.0327 0.5842 1.0000
3.000 0.5303 0.01240 0.00364 -0.0320 0.5471 1.0000
3.250 0.5555 0.01272 0.00383 -0.0313 0.5100 1.0000
3.500 0.5807 0.01307 0.00406 -0.0307 0.4729 1.0000
3.750 0.6059 0.01345 0.00432 -0.0301 0.4362 1.0000
4.000 0.6309 0.01386 0.00467 -0.0296 0.4010 1.0000
4.250 0.6561 0.01429 0.00501 -0.0291 0.3661 1.0000
4.750 0.7060 0.01524 0.00581 -0.0282 0.3003 1.0000
5.000 0.7309 0.01576 0.00631 -0.0278 0.2694 1.0000
5.250 0.7556 0.01631 0.00681 -0.0274 0.2397 1.0000
5.500 0.7802 0.01690 0.00736 -0.0270 0.2119 1.0000
5.750 0.8047 0.01752 0.00797 -0.0266 0.1859 1.0000
6.000 0.8290 0.01820 0.00865 -0.0262 0.1619 1.0000
6.250 0.8528 0.01895 0.00943 -0.0257 0.1396 1.0000
6.500 0.8765 0.01975 0.01029 -0.0252 0.1213 1.0000
6.750 0.8996 0.02064 0.01119 -0.0247 0.1043 1.0000
7.000 0.9224 0.02161 0.01220 -0.0242 0.0907 1.0000
7.250 0.9449 0.02264 0.01336 -0.0235 0.0798 1.0000
7.500 0.9670 0.02371 0.01454 -0.0229 0.0690 1.0000
7.750 0.9880 0.02503 0.01603 -0.0221 0.0616 1.0000
8.000 1.0090 0.02629 0.01743 -0.0214 0.0542 1.0000
8.250 1.0294 0.02773 0.01910 -0.0206 0.0472 1.0000
8.500 1.0484 0.02933 0.02082 -0.0197 0.0423 1.0000
8.750 1.0671 0.03116 0.02296 -0.0188 0.0371 1.0000
9.000 1.0848 0.03288 0.02490 -0.0179 0.0327 1.0000
9.250 1.0989 0.03543 0.02760 -0.0168 0.0298 1.0000
9.500 1.1138 0.03769 0.03037 -0.0157 0.0261 1.0000
9.750 1.1258 0.04004 0.03302 -0.0146 0.0235 1.0000
10.000 1.1342 0.04276 0.03602 -0.0134 0.0220 1.0000
10.250 1.1352 0.04662 0.04021 -0.0121 0.0207 1.0000
10.500 1.1331 0.05029 0.04439 -0.0109 0.0195 1.0000
10.750 1.1239 0.05407 0.04857 -0.0097 0.0186 1.0000
11.000 1.1096 0.05822 0.05301 -0.0095 0.0182 1.0000
11.250 1.0924 0.06342 0.05848 -0.0115 0.0181 1.0000
11.500 1.0730 0.07006 0.06534 -0.0158 0.0184 1.0000
11.750 1.0523 0.07814 0.07361 -0.0220 0.0191 1.0000
12.000 1.0318 0.08710 0.08261 -0.0286 0.0198 1.0000
12.250 1.0121 0.09630 0.09186 -0.0347 0.0205 1.0000
12.500 0.9930 0.10556 0.10113 -0.0403 0.0210 1.0000
|
Polar data table (+)
Polar graphs
<< Back to AG03 (flat aft bottom) (ag03-il)