AG24 Bubble Dancer DLG by Mark Drela (ag24-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG24 Bubble Dancer DLG by Mark Drela (ag24-il) Reynolds number: 200,000 Max Cl/Cd: 70.12 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag24-il-200000.txt Download as CSV file: xf-ag24-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: AG24 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3970 0.09532 0.09207 -0.0160 1.0000 0.0469
-9.000 -0.4040 0.09100 0.08779 -0.0199 1.0000 0.0476
-8.750 -0.4080 0.08656 0.08338 -0.0231 1.0000 0.0478
-8.500 -0.4114 0.08188 0.07874 -0.0261 1.0000 0.0480
-8.250 -0.4114 0.07567 0.07258 -0.0244 1.0000 0.0493
-8.000 -0.4024 0.07271 0.06962 -0.0229 1.0000 0.0506
-7.750 -0.3996 0.06914 0.06608 -0.0233 1.0000 0.0519
-7.500 -0.4885 0.06936 0.06608 -0.0403 1.0000 0.0489
-7.250 -0.4789 0.06804 0.06484 -0.0360 1.0000 0.0502
-7.000 -0.4683 0.06484 0.06165 -0.0371 1.0000 0.0517
-6.750 -0.4572 0.06025 0.05700 -0.0410 1.0000 0.0538
-6.500 -0.4455 0.05449 0.05109 -0.0464 1.0000 0.0571
-6.250 -0.4188 0.03530 0.03189 -0.0479 1.0000 0.0627
-6.000 -0.4093 0.03270 0.02933 -0.0466 1.0000 0.0644
-5.750 -0.4006 0.02973 0.02627 -0.0462 1.0000 0.0672
-5.500 -0.3856 0.02860 0.02324 -0.0534 1.0000 0.0329
-5.250 -0.3635 0.02418 0.01820 -0.0532 1.0000 0.0299
-5.000 -0.3392 0.02119 0.01466 -0.0526 1.0000 0.0291
-4.750 -0.3159 0.01988 0.01314 -0.0519 1.0000 0.0318
-4.500 -0.2913 0.01850 0.01145 -0.0512 1.0000 0.0339
-4.250 -0.2657 0.01705 0.00977 -0.0506 1.0000 0.0351
-4.000 -0.2387 0.01520 0.00781 -0.0505 1.0000 0.0377
-3.750 -0.2130 0.01435 0.00697 -0.0503 1.0000 0.0446
-3.500 -0.1853 0.01332 0.00593 -0.0506 1.0000 0.0543
-3.250 -0.1564 0.01243 0.00509 -0.0511 1.0000 0.0807
-3.000 -0.1242 0.01115 0.00451 -0.0528 1.0000 0.2191
-2.750 -0.0958 0.01068 0.00443 -0.0537 1.0000 0.3302
-2.500 -0.0582 0.01031 0.00439 -0.0561 0.9963 0.4349
-2.250 -0.0162 0.00996 0.00433 -0.0592 0.9899 0.5296
-2.000 0.0260 0.00966 0.00429 -0.0622 0.9834 0.6182
-1.750 0.0638 0.00938 0.00427 -0.0639 0.9751 0.7005
-1.500 0.1036 0.00911 0.00421 -0.0658 0.9690 0.7817
-1.250 0.1337 0.00888 0.00413 -0.0654 0.9584 0.8551
-1.000 0.1665 0.00862 0.00394 -0.0653 0.9486 0.9413
-0.750 0.2113 0.00845 0.00367 -0.0686 0.9393 1.0000
-0.500 0.2456 0.00838 0.00348 -0.0696 0.9272 1.0000
-0.250 0.2756 0.00833 0.00334 -0.0697 0.9129 1.0000
0.000 0.3031 0.00830 0.00322 -0.0693 0.8970 1.0000
0.250 0.3299 0.00828 0.00312 -0.0686 0.8802 1.0000
0.500 0.3563 0.00828 0.00303 -0.0678 0.8628 1.0000
0.750 0.3826 0.00829 0.00294 -0.0670 0.8452 1.0000
1.000 0.4087 0.00833 0.00290 -0.0663 0.8257 1.0000
1.250 0.4350 0.00839 0.00288 -0.0655 0.8053 1.0000
1.500 0.4613 0.00847 0.00286 -0.0648 0.7842 1.0000
1.750 0.4877 0.00857 0.00286 -0.0642 0.7619 1.0000
2.000 0.5142 0.00869 0.00289 -0.0636 0.7381 1.0000
2.250 0.5407 0.00883 0.00295 -0.0630 0.7138 1.0000
2.500 0.5672 0.00900 0.00301 -0.0625 0.6888 1.0000
2.750 0.5937 0.00918 0.00309 -0.0620 0.6625 1.0000
3.000 0.6201 0.00939 0.00321 -0.0615 0.6352 1.0000
3.250 0.6465 0.00962 0.00336 -0.0610 0.6075 1.0000
3.500 0.6728 0.00988 0.00352 -0.0606 0.5793 1.0000
3.750 0.6990 0.01015 0.00371 -0.0602 0.5508 1.0000
4.000 0.7252 0.01045 0.00392 -0.0598 0.5217 1.0000
4.250 0.7512 0.01076 0.00415 -0.0594 0.4922 1.0000
4.500 0.7771 0.01109 0.00444 -0.0590 0.4625 1.0000
4.750 0.8029 0.01145 0.00473 -0.0586 0.4322 1.0000
5.000 0.8284 0.01184 0.00504 -0.0582 0.4014 1.0000
5.250 0.8537 0.01226 0.00538 -0.0578 0.3704 1.0000
5.500 0.8789 0.01270 0.00579 -0.0574 0.3383 1.0000
5.750 0.9038 0.01317 0.00620 -0.0570 0.3052 1.0000
6.000 0.9282 0.01372 0.00664 -0.0566 0.2723 1.0000
6.250 0.9527 0.01428 0.00714 -0.0561 0.2380 1.0000
6.500 0.9763 0.01495 0.00769 -0.0557 0.2038 1.0000
6.750 0.9999 0.01565 0.00834 -0.0552 0.1678 1.0000
7.000 1.0225 0.01650 0.00905 -0.0547 0.1311 1.0000
7.250 1.0437 0.01761 0.00997 -0.0540 0.0948 1.0000
7.500 1.0636 0.01896 0.01117 -0.0531 0.0634 1.0000
7.750 1.0812 0.02067 0.01282 -0.0517 0.0451 1.0000
8.000 1.0983 0.02241 0.01458 -0.0503 0.0351 1.0000
8.250 1.1174 0.02384 0.01614 -0.0490 0.0298 1.0000
8.500 1.1308 0.02638 0.01871 -0.0472 0.0257 1.0000
8.750 1.1511 0.02761 0.02018 -0.0461 0.0230 1.0000
9.000 1.1689 0.02953 0.02226 -0.0447 0.0213 1.0000
9.250 1.1858 0.03162 0.02451 -0.0434 0.0200 1.0000
9.500 1.2011 0.03418 0.02725 -0.0420 0.0191 1.0000
9.750 1.2140 0.03744 0.03079 -0.0404 0.0186 1.0000
10.000 1.2233 0.04106 0.03476 -0.0386 0.0184 1.0000
10.250 1.2290 0.04463 0.03871 -0.0366 0.0184 1.0000
10.500 1.2297 0.04830 0.04274 -0.0344 0.0184 1.0000
10.750 1.2239 0.05224 0.04702 -0.0321 0.0183 1.0000
11.000 1.2107 0.05598 0.05104 -0.0294 0.0182 1.0000
11.250 1.1961 0.05961 0.05492 -0.0275 0.0181 1.0000
11.500 1.1796 0.06368 0.05924 -0.0268 0.0181 1.0000
11.750 1.1625 0.06824 0.06403 -0.0274 0.0181 1.0000
12.000 1.1460 0.07324 0.06923 -0.0293 0.0182 1.0000
12.250 1.1297 0.07882 0.07501 -0.0323 0.0183 1.0000
12.500 1.1119 0.08543 0.08183 -0.0368 0.0185 1.0000
12.750 1.0338 0.10934 0.10632 -0.0557 0.0219 1.0000
13.000 0.9976 0.12535 0.12239 -0.0659 0.0228 1.0000
13.250 0.9724 0.13892 0.13588 -0.0726 0.0241 1.0000
13.500 0.9612 0.14739 0.14431 -0.0764 0.0250 1.0000
13.750 0.7877 0.13187 0.12899 -0.0510 0.0243 1.0000
14.000 0.7667 0.13870 0.13579 -0.0537 0.0252 1.0000
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Polar data table (+)
Polar graphs
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