AG25 Bubble Dancer DLG by Mark Drela (ag25-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG25 Bubble Dancer DLG by Mark Drela (ag25-il) Reynolds number: 200,000 Max Cl/Cd: 70.85 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag25-il-200000.txt Download as CSV file: xf-ag25-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: AG25 Bubble Dancer DLG by Mark Drela
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.4195 0.13738 0.13395 -0.0031 1.0000 0.0291
-11.500 -0.4179 0.13422 0.13080 -0.0045 1.0000 0.0292
-7.250 -0.4683 0.07746 0.07427 -0.0220 1.0000 0.0432
-7.000 -0.4579 0.07417 0.07096 -0.0234 1.0000 0.0446
-6.750 -0.4461 0.06997 0.06677 -0.0276 1.0000 0.0464
-6.500 -0.4318 0.06481 0.06159 -0.0338 1.0000 0.0487
-6.250 -0.4053 0.05657 0.05279 -0.0499 1.0000 0.0536
-6.000 -0.3980 0.04979 0.04608 -0.0513 1.0000 0.0552
-5.750 -0.3840 0.04729 0.04365 -0.0505 1.0000 0.0570
-5.500 -0.3674 0.04426 0.04054 -0.0512 1.0000 0.0600
-5.250 -0.3464 0.03894 0.03463 -0.0549 1.0000 0.0684
-5.000 -0.3291 0.03628 0.03202 -0.0544 1.0000 0.0708
-4.750 -0.2920 0.02427 0.01828 -0.0559 1.0000 0.0306
-4.250 -0.2423 0.02015 0.01346 -0.0547 1.0000 0.0289
-4.000 -0.2155 0.01741 0.01034 -0.0547 1.0000 0.0308
-3.750 -0.1905 0.01618 0.00904 -0.0545 1.0000 0.0348
-3.500 -0.1635 0.01489 0.00759 -0.0541 1.0000 0.0372
-3.250 -0.1366 0.01399 0.00657 -0.0538 1.0000 0.0409
-3.000 -0.1086 0.01295 0.00554 -0.0541 1.0000 0.0530
-2.750 -0.0780 0.01182 0.00455 -0.0549 1.0000 0.0852
-2.500 -0.0456 0.01059 0.00410 -0.0567 1.0000 0.2517
-2.250 -0.0170 0.01012 0.00405 -0.0575 1.0000 0.3796
-2.000 0.0149 0.00977 0.00407 -0.0588 0.9982 0.4936
-1.750 0.0570 0.00934 0.00404 -0.0617 0.9917 0.6141
-1.500 0.0952 0.00888 0.00402 -0.0635 0.9841 0.7464
-1.250 0.1262 0.00840 0.00389 -0.0629 0.9749 0.9251
-1.000 0.1752 0.00831 0.00365 -0.0672 0.9666 1.0000
-0.750 0.2170 0.00827 0.00348 -0.0700 0.9565 1.0000
-0.500 0.2542 0.00823 0.00332 -0.0716 0.9443 1.0000
-0.250 0.2885 0.00817 0.00317 -0.0726 0.9306 1.0000
0.000 0.3195 0.00813 0.00305 -0.0727 0.9156 1.0000
0.250 0.3481 0.00809 0.00293 -0.0723 0.8996 1.0000
0.500 0.3742 0.00809 0.00285 -0.0715 0.8802 1.0000
0.750 0.4003 0.00811 0.00278 -0.0705 0.8611 1.0000
1.000 0.4261 0.00814 0.00273 -0.0696 0.8407 1.0000
1.250 0.4519 0.00821 0.00270 -0.0687 0.8190 1.0000
1.500 0.4778 0.00829 0.00270 -0.0678 0.7960 1.0000
1.750 0.5038 0.00840 0.00271 -0.0670 0.7724 1.0000
2.000 0.5299 0.00853 0.00272 -0.0662 0.7475 1.0000
2.250 0.5560 0.00868 0.00278 -0.0655 0.7208 1.0000
2.500 0.5822 0.00885 0.00287 -0.0649 0.6930 1.0000
2.750 0.6084 0.00905 0.00296 -0.0643 0.6642 1.0000
3.000 0.6345 0.00927 0.00307 -0.0637 0.6336 1.0000
3.250 0.6606 0.00951 0.00321 -0.0632 0.6021 1.0000
3.500 0.6866 0.00979 0.00340 -0.0626 0.5700 1.0000
3.750 0.7125 0.01009 0.00359 -0.0621 0.5373 1.0000
4.000 0.7383 0.01042 0.00382 -0.0616 0.5037 1.0000
4.250 0.7639 0.01079 0.00406 -0.0612 0.4704 1.0000
4.500 0.7896 0.01115 0.00434 -0.0607 0.4362 1.0000
4.750 0.8150 0.01157 0.00468 -0.0603 0.4027 1.0000
5.000 0.8404 0.01199 0.00503 -0.0599 0.3685 1.0000
5.250 0.8655 0.01246 0.00540 -0.0595 0.3350 1.0000
5.500 0.8905 0.01296 0.00582 -0.0591 0.3015 1.0000
5.750 0.9153 0.01348 0.00627 -0.0587 0.2678 1.0000
6.000 0.9397 0.01408 0.00680 -0.0582 0.2352 1.0000
6.250 0.9641 0.01469 0.00735 -0.0578 0.2019 1.0000
6.500 0.9878 0.01542 0.00796 -0.0574 0.1698 1.0000
6.750 1.0112 0.01619 0.00865 -0.0569 0.1372 1.0000
7.000 1.0339 0.01711 0.00945 -0.0563 0.1060 1.0000
7.250 1.0553 0.01826 0.01047 -0.0556 0.0783 1.0000
7.500 1.0760 0.01956 0.01177 -0.0546 0.0557 1.0000
7.750 1.0931 0.02142 0.01356 -0.0533 0.0405 1.0000
8.000 1.1137 0.02273 0.01501 -0.0522 0.0325 1.0000
8.250 1.1307 0.02474 0.01713 -0.0506 0.0272 1.0000
8.500 1.1501 0.02615 0.01865 -0.0495 0.0233 1.0000
8.750 1.1645 0.02908 0.02168 -0.0479 0.0211 1.0000
9.000 1.1800 0.03240 0.02531 -0.0462 0.0201 1.0000
9.250 1.1963 0.03501 0.02826 -0.0446 0.0195 1.0000
9.500 1.2090 0.03821 0.03186 -0.0429 0.0191 1.0000
9.750 1.2183 0.04138 0.03544 -0.0410 0.0185 1.0000
10.000 1.2249 0.04424 0.03872 -0.0391 0.0176 1.0000
10.250 1.2280 0.04712 0.04191 -0.0372 0.0167 1.0000
10.500 1.2263 0.05022 0.04531 -0.0352 0.0161 1.0000
10.750 1.2135 0.05397 0.04938 -0.0325 0.0162 1.0000
11.000 1.1957 0.05808 0.05380 -0.0307 0.0163 1.0000
11.250 1.1760 0.06286 0.05885 -0.0307 0.0165 1.0000
11.500 1.1551 0.06851 0.06475 -0.0326 0.0167 1.0000
11.750 1.1337 0.07519 0.07165 -0.0363 0.0169 1.0000
12.000 1.1113 0.08310 0.07975 -0.0417 0.0172 1.0000
12.250 1.0863 0.09275 0.08952 -0.0488 0.0177 1.0000
12.500 1.0585 0.10403 0.10092 -0.0566 0.0189 1.0000
12.750 1.0314 0.11547 0.11240 -0.0635 0.0199 1.0000
13.000 0.9716 0.14482 0.14177 -0.0792 0.0260 1.0000
13.250 0.9644 0.15234 0.14925 -0.0825 0.0275 1.0000
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Polar data table (+)
Polar graphs
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