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

AG24 Bubble Dancer DLG by Mark Drela (ag24-il)

AG24 Bubble Dancer DLG by Mark Drela - Drela AG24 airfoil used on the Bubble Dancer R/C DLG


Airfoil ag24-il
Details Dat file Parser  
(ag24-il) AG24 Bubble Dancer DLG by Mark Drela
Drela AG24 airfoil used on the Bubble Dancer R/C DLG
Max thickness 8.4% at 26% chord.
Max camber 2.2% at 46.9% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
AG24 Bubble Dancer DLG by Mark Drela
     1.000000    0.000312
     0.994048    0.001043
     0.982038    0.002630
     0.968488    0.004486
     0.954647    0.006421
     0.940769    0.008378
     0.926890    0.010328
     0.913006    0.012258
     0.899118    0.014165
     0.885230    0.016048
     0.871339    0.017908
     0.857451    0.019744
     0.843559    0.021562
     0.829670    0.023357
     0.815779    0.025130
     0.801883    0.026879
     0.787989    0.028602
     0.774091    0.030297
     0.760188    0.031964
     0.746285    0.033600
     0.732376    0.035204
     0.718461    0.036776
     0.704547    0.038313
     0.690631    0.039813
     0.676709    0.041277
     0.662788    0.042702
     0.648868    0.044087
     0.634943    0.045432
     0.621017    0.046736
     0.607093    0.047997
     0.593166    0.049214
     0.579236    0.050389
     0.565310    0.051517
     0.551385    0.052600
     0.537456    0.053635
     0.523528    0.054622
     0.509606    0.055558
     0.495682    0.056443
     0.481756    0.057276
     0.467835    0.058053
     0.453918    0.058774
     0.440000    0.059437
     0.426087    0.060040
     0.412180    0.060579
     0.398274    0.061053
     0.384372    0.061458
     0.370481    0.061792
     0.356594    0.062050
     0.342711    0.062231
     0.328841    0.062328
     0.314984    0.062338
     0.301131    0.062254
     0.287296    0.062074
     0.273479    0.061789
     0.259672    0.061394
     0.245889    0.060883
     0.232132    0.060248
     0.218395    0.059480
     0.204696    0.058572
     0.191034    0.057514
     0.177412    0.056295
     0.163854    0.054904
     0.150354    0.053325
     0.136934    0.051545
     0.123613    0.049542
     0.110400    0.047296
     0.097342    0.044784
     0.084457    0.041971
     0.071816    0.038832
     0.059466    0.035323
     0.047533    0.031413
     0.036200    0.027083
     0.025838    0.022393
     0.017129    0.017634
     0.010712    0.013341
     0.006482    0.009857
     0.003763    0.007107
     0.001997    0.004865
     0.000855    0.002963
     0.000198    0.001287
     0.000001   -0.000230
     0.000293   -0.001719
     0.001184   -0.003235
     0.002714   -0.004738
     0.004994   -0.006301
     0.008364   -0.008034
     0.013488   -0.010053
     0.021193   -0.012377
     0.031412   -0.014726
     0.043212   -0.016796
     0.055804   -0.018519
     0.068780   -0.019918
     0.081987   -0.021042
     0.095351   -0.021938
     0.108824   -0.022639
     0.122377   -0.023175
     0.135989   -0.023565
     0.149652   -0.023827
     0.163351   -0.023977
     0.177085   -0.024026
     0.190844   -0.023986
     0.204622   -0.023867
     0.218421   -0.023675
     0.232237   -0.023420
     0.246064   -0.023106
     0.259909   -0.022740
     0.273764   -0.022326
     0.287631   -0.021871
     0.301514   -0.021381
     0.315408   -0.020856
     0.329313   -0.020301
     0.343234   -0.019718
     0.357166   -0.019111
     0.371111   -0.018482
     0.385067   -0.017835
     0.399034   -0.017173
     0.413004   -0.016498
     0.426962   -0.015813
     0.440907   -0.015121
     0.454842   -0.014424
     0.468769   -0.013723
     0.482685   -0.013021
     0.496593   -0.012319
     0.510494   -0.011617
     0.524394   -0.010919
     0.538286   -0.010224
     0.552174   -0.009535
     0.566059   -0.008852
     0.579942   -0.008177
     0.593817   -0.007511
     0.607689   -0.006857
     0.621556   -0.006214
     0.635419   -0.005585
     0.649276   -0.004971
     0.663131   -0.004372
     0.676986   -0.003788
     0.690839   -0.003221
     0.704693   -0.002670
     0.718548   -0.002136
     0.732407   -0.001619
     0.746265   -0.001122
     0.760127   -0.000645
     0.773993   -0.000194
     0.787859    0.000230
     0.801731    0.000622
     0.815611    0.000975
     0.829491    0.001286
     0.843374    0.001550
     0.857263    0.001759
     0.871153    0.001909
     0.885046    0.001991
     0.898943    0.001997
     0.912839    0.001920
     0.926737    0.001758
     0.940634    0.001501
     0.954532    0.001149
     0.968401    0.000707
     0.982019    0.000185
     0.994039   -0.000364
     1.000000   -0.000659

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

MH 32 8.7%PreviewDetails
S9000 (9%)PreviewDetails
GOE 563 AIRFOILPreviewDetails
AG25 Bubble Dancer DLG by Mark DrelaPreviewDetails
GOE 565 AIRFOILPreviewDetails
SD7037-092-88PreviewDetails
GOE 795 AIRFOILPreviewDetails
GOE 795 smoothedPreviewDetails
S4110PreviewDetails
S7075 (9%)PreviewDetails

Polars for AG24 Bubble Dancer DLG by Mark Drela (ag24-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   ag24-il50,000934.7 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   ag24-il50,000538.3 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   ag24-il100,000952.6 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   ag24-il100,000552.7 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   ag24-il200,000970.1 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   ag24-il200,000566.5 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ag24-il500,000992.1 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ag24-il500,000583.9 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   ag24-il1,000,0009107.1 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   ag24-il1,000,000596.8 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit