Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

AG26 Bubble Dancer DLG by Mark Drela (ag26-il)

AG26 Bubble Dancer DLG by Mark Drela - Drela AG26 airfoil used on the Bubble Dancer R/C DLG


Airfoil ag26-il
Details Dat file Parser  
(ag26-il) AG26 Bubble Dancer DLG by Mark Drela
Drela AG26 airfoil used on the Bubble Dancer R/C DLG
Max thickness 6.8% at 23.3% chord.
Max camber 2.5% at 45.5% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
AG26 Bubble Dancer DLG by Mark Drela
     1.000000    0.000283
     0.994061    0.000999
     0.982066    0.002505
     0.968526    0.004228
     0.954693    0.006008
     0.940816    0.007759
     0.926936    0.009469
     0.913054    0.011174
     0.899169    0.012856
     0.885285    0.014530
     0.871402    0.016190
     0.857523    0.017832
     0.843640    0.019461
     0.829761    0.021064
     0.815882    0.022652
     0.801998    0.024219
     0.788119    0.025763
     0.774238    0.027291
     0.760352    0.028789
     0.746468    0.030268
     0.732578    0.031719
     0.718685    0.033151
     0.704794    0.034552
     0.690902    0.035926
     0.677007    0.037275
     0.663114    0.038591
     0.649222    0.039874
     0.635327    0.041126
     0.621434    0.042343
     0.607542    0.043523
     0.593649    0.044668
     0.579754    0.045771
     0.565865    0.046837
     0.551976    0.047861
     0.538085    0.048847
     0.524196    0.049789
     0.510314    0.050690
     0.496430    0.051538
     0.482545    0.052336
     0.468664    0.053082
     0.454789    0.053772
     0.440913    0.054407
     0.427041    0.054983
     0.413176    0.055498
     0.399313    0.055953
     0.385454    0.056345
     0.371607    0.056669
     0.357762    0.056927
     0.343921    0.057113
     0.330095    0.057226
     0.316280    0.057262
     0.302471    0.057219
     0.288679    0.057095
     0.274904    0.056884
     0.261136    0.056581
     0.247392    0.056182
     0.233671    0.055680
     0.219967    0.055067
     0.206299    0.054334
     0.192663    0.053472
     0.179063    0.052469
     0.165520    0.051314
     0.152029    0.049989
     0.138611    0.048479
     0.125281    0.046761
     0.112050    0.044812
     0.098958    0.042616
     0.086022    0.040147
     0.073305    0.037380
     0.060851    0.034267
     0.048780    0.030758
     0.037275    0.026799
     0.026717    0.022411
     0.017800    0.017854
     0.011195    0.013657
     0.006815    0.010190
     0.003988    0.007407
     0.002136    0.005117
     0.000931    0.003155
     0.000227    0.001419
     0.000002   -0.000157
     0.000342   -0.001683
     0.001369   -0.003136
     0.003059   -0.004457
     0.005487   -0.005761
     0.008992   -0.007149
     0.014252   -0.008701
     0.022090   -0.010375
     0.032419   -0.011934
     0.044295   -0.013185
     0.056934   -0.014106
     0.069936   -0.014742
     0.083154   -0.015148
     0.096518   -0.015373
     0.109982   -0.015460
     0.123522   -0.015438
     0.137115   -0.015327
     0.150759   -0.015139
     0.164436   -0.014883
     0.178145   -0.014564
     0.191880   -0.014188
     0.205634   -0.013764
     0.219407   -0.013295
     0.233197   -0.012787
     0.247000   -0.012246
     0.260819   -0.011674
     0.274650   -0.011077
     0.288493   -0.010462
     0.302352   -0.009830
     0.316224   -0.009187
     0.330108   -0.008536
     0.344007   -0.007882
     0.357919   -0.007225
     0.371844   -0.006569
     0.385781   -0.005919
     0.399730   -0.005270
     0.413682   -0.004629
     0.427624   -0.004000
     0.441553   -0.003380
     0.455472   -0.002772
     0.469385   -0.002184
     0.483287   -0.001615
     0.497181   -0.001064
     0.511069   -0.000532
     0.524956   -0.000023
     0.538837    0.000463
     0.552713    0.000926
     0.566586    0.001366
     0.580457    0.001780
     0.594321    0.002166
     0.608182    0.002528
     0.622038    0.002860
     0.635889    0.003166
     0.649734    0.003442
     0.663579    0.003691
     0.677422    0.003909
     0.691263    0.004098
     0.705104    0.004259
     0.718947    0.004390
     0.732793    0.004493
     0.746637    0.004565
     0.760486    0.004608
     0.774336    0.004619
     0.788187    0.004597
     0.802043    0.004544
     0.815905    0.004455
     0.829767    0.004330
     0.843631    0.004169
     0.857499    0.003966
     0.871368    0.003725
     0.885239    0.003440
     0.899112    0.003111
     0.912984    0.002735
     0.926859    0.002311
     0.940732    0.001837
     0.954608    0.001313
     0.968456    0.000739
     0.982055    0.000127
     0.994062   -0.000442
     1.000000   -0.000716

The AG2x airfoils are intended to be used on composite versions of the 
Bubble Dancer and the Allegro-Lite.
Dat file parser warnings
  • Line 162 - Invalid characters : The AG2x airfoils are intended to be used on composite versions of the
  • Line 163 - Invalid characters : Bubble Dancer and the Allegro-Lite.
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

AG17PreviewDetails
AG16PreviewDetails
AG27 Bubble Dancer DLG by Mark DrelaPreviewDetails
AG25 Bubble Dancer DLG by Mark DrelaPreviewDetails
USA 46 AIRFOILPreviewDetails
GOE 344 (PFALZ 71) AIRFOILPreviewDetails
GOE 488 AIRFOILPreviewDetails
MA409 (smoothed)PreviewDetails
SA7024PreviewDetails
MA409 (original) (modified line 7)PreviewDetails

Polars for AG26 Bubble Dancer DLG by Mark Drela (ag26-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   ag26-il50,000936.8 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ag26-il50,000539.4 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   ag26-il100,000954.5 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ag26-il100,000553.2 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   ag26-il200,000971.6 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   ag26-il200,000565.9 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   ag26-il500,000991.8 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ag26-il500,000583 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   ag26-il1,000,0009104.7 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ag26-il1,000,000596 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit