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

ONERA OA209 AIRFOIL (oa209-il)

ONERA OA209 AIRFOIL - ONERA/Aerospatiale OA209 rotorcraft airfoil (Constructed from patent and smoothed)


Airfoil oa209-il
Details Dat file Parser  
(oa209-il) ONERA OA209 AIRFOIL
ONERA/Aerospatiale OA209 rotorcraft airfoil (Constructed from patent and smoothed)
Max thickness 9% at 29.3% chord.
Max camber 1.6% at 17.1% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
 ONERA OA209 AIRFOIL
       57.       57.

 0.0000000 0.0000000
 0.0002924 0.0028551
 0.0007810 0.0047471
 0.0017586 0.0072243
 0.0048866 0.0121590
 0.0070371 0.0145844
 0.0097746 0.0171549
 0.0156407 0.0216181
 0.0224839 0.0258454
 0.0293282 0.0294448
 0.0351946 0.0321729
 0.0391053 0.0338387
 0.0449719 0.0361378
 0.0537712 0.0391946
 0.0635487 0.0421315
 0.0733262 0.0446694
 0.0831038 0.0468743
 0.0928814 0.0487973
 0.1222146 0.0532210
 0.1466590 0.0557137
 0.1711047 0.0573865
 0.1955495 0.0584144
 0.2199944 0.0589332
 0.2444394 0.0590590
 0.2688844 0.0588899
 0.2933294 0.0585127
 0.3177745 0.0580034
 0.3422197 0.0574183
 0.3666649 0.0567851
 0.3911100 0.0560989
 0.4155561 0.0553337
 0.4400013 0.0544535
 0.4644465 0.0534314
 0.4888917 0.0522542
 0.5133371 0.0509200
 0.5377824 0.0494348
 0.5622277 0.0478067
 0.5866730 0.0460385
 0.6111183 0.0441303
 0.6355637 0.0420791
 0.6600091 0.0398820
 0.6844547 0.0375358
 0.7089013 0.0350436
 0.7333468 0.0324094
 0.7577922 0.0296382
 0.7822378 0.0267311
 0.8066834 0.0236749
 0.8311290 0.0204437
 0.8506855 0.0177115
 0.8702421 0.0148404
 0.8800204 0.0133593
 0.8995770 0.0103632
 0.9191335 0.0074690
 0.9386901 0.0049059
 0.9511083 0.0035814
 0.9778036 0.0019806
 1.0000000 0.0025150

 0.0000000 0.0000000
 0.0002934 -.0025969
 0.0007827 -.0040758
 0.0017611 -.0057866
 0.0048906 -.0086200
 0.0070419 -.0097936
 0.0097801 -.0109121
 0.0156475 -.0126099
 0.0224917 -.0140076
 0.0293369 -.0150912
 0.0352041 -.0158681
 0.0391152 -.0163313
 0.0449823 -.0169601
 0.0537825 -.0177994
 0.0635607 -.0186385
 0.0733388 -.0194185
 0.0831169 -.0201646
 0.0928951 -.0208907
 0.1222295 -.0229909
 0.1466749 -.0246691
 0.1711212 -.0262593
 0.1955665 -.0277175
 0.2200117 -.0289996
 0.2444569 -.0300718
 0.2689021 -.0309240
 0.2933472 -.0315792
 0.3177923 -.0320834
 0.3422375 -.0324905
 0.3666825 -.0328357
 0.3911275 -.0331239
 0.4155736 -.0333301
 0.4400187 -.0334213
 0.4644636 -.0333685
 0.4889086 -.0331596
 0.5133536 -.0327928
 0.5377985 -.0322740
 0.5622433 -.0316132
 0.5866882 -.0308134
 0.6111330 -.0298756
 0.6355777 -.0287947
 0.6600226 -.0275679
 0.6844673 -.0261931
 0.7089130 -.0246733
 0.7333577 -.0230135
 0.7578022 -.0212177
 0.7822468 -.0192799
 0.8066914 -.0171821
 0.8311360 -.0148962
 0.8506916 -.0129154
 0.8702472 -.0108045
 0.8800250 -.0097146
 0.8995805 -.0075468
 0.9191361 -.0055509
 0.9386918 -.0039291
 0.9511096 -.0031806
 0.9778045 -.0024304
 1.0000000 -.0025080
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

BOEING VERTOL V(1.95)3009-1.25PreviewDetails
PW75PreviewDetails
BOEING 707 .40 SPAN AIRFOILPreviewDetails
SIKORSKY SC1094R8 AIRFOILPreviewDetails
SIKORSKY SC1094 R8 AIRFOILPreviewDetails
GIII BL450 AIRFOILPreviewDetails
PMC19 SmoothedPreviewDetails
EH 1.5/9.0PreviewDetails
BELL/WORTMANN FX 69-H-098 AIRFOILPreviewDetails
EH 1.0/9.0PreviewDetails

Polars for ONERA OA209 AIRFOIL (oa209-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   oa209-il50,000925.8 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   oa209-il50,000528.6 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   oa209-il100,000936 at α=7.75°Mach=0 Ncrit=9Xfoil predictionDetails
   oa209-il100,000541.5 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
   oa209-il200,000952.7 at α=8°Mach=0 Ncrit=9Xfoil predictionDetails
   oa209-il200,000555.3 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
   oa209-il500,000975.1 at α=8°Mach=0 Ncrit=9Xfoil predictionDetails
   oa209-il500,000573.3 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   oa209-il1,000,000990.5 at α=7.75°Mach=0 Ncrit=9Xfoil predictionDetails
   oa209-il1,000,000585.2 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit