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HQ 0/9 AIRFOIL (hq09-il)

HQ 0/9 AIRFOIL - Quabeck HQ 0/9 R/C sailplane airfoil


Airfoil hq09-il
Details Dat file Parser  
(hq09-il) HQ 0/9 AIRFOIL
Quabeck HQ 0/9 R/C sailplane airfoil
Max thickness 8.1% at 33.9% chord.
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
HQ 0/9 AIRFOIL
       49.       49.

 0.0000000 0.0000000
 0.0011100 0.0026500
 0.0043300 0.0061300
 0.0095600 0.0094600
 0.0170000 0.0127400
 0.0265600 0.0159600
 0.0381100 0.0190400
 0.0515600 0.0219500
 0.0670000 0.0247100
 0.0842200 0.0273200
 0.1033300 0.0298000
 0.1241100 0.0321400
 0.1464400 0.0342300
 0.1703300 0.0358900
 0.1956700 0.0370400
 0.2222200 0.0381000
 0.2500000 0.0390500
 0.2788900 0.0397600
 0.3086700 0.0402700
 0.3393300 0.0405600
 0.3705600 0.0404100
 0.4024400 0.0398400
 0.4347800 0.0390400
 0.4673300 0.0380700
 0.5000000 0.0368300
 0.5326700 0.0352400
 0.5652200 0.0333100
 0.5975600 0.0311000
 0.6294400 0.0286700
 0.6606700 0.0261000
 0.6913300 0.0235000
 0.7211100 0.0209300
 0.7500000 0.0184300
 0.7777800 0.0160100
 0.8043300 0.0137000
 0.8296700 0.0115500
 0.8535600 0.0096200
 0.8758900 0.0079500
 0.8966700 0.0064600
 0.9157800 0.0050800
 0.9330000 0.0038500
 0.9484400 0.0028100
 0.9618900 0.0019900
 0.9734400 0.0013500
 0.9830000 0.0008600
 0.9904400 0.0004800
 0.9956700 0.0002100
 0.9988900 0.0000500
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0011100 -.0026500
 0.0043300 -.0061300
 0.0095600 -.0094600
 0.0170000 -.0127400
 0.0265600 -.0159600
 0.0381100 -.0190400
 0.0515600 -.0219500
 0.0670000 -.0247100
 0.0842200 -.0273200
 0.1033300 -.0298000
 0.1241100 -.0321400
 0.1464400 -.0342300
 0.1703300 -.0358900
 0.1956700 -.0370400
 0.2222200 -.0381000
 0.2500000 -.0390500
 0.2788900 -.0397600
 0.3086700 -.0402700
 0.3393300 -.0405600
 0.3705600 -.0404100
 0.4024400 -.0398400
 0.4347800 -.0390400
 0.4673300 -.0380700
 0.5000000 -.0368300
 0.5326700 -.0352400
 0.5652200 -.0333100
 0.5975600 -.0311000
 0.6294400 -.0286700
 0.6606700 -.0261000
 0.6913300 -.0235000
 0.7211100 -.0209300
 0.7500000 -.0184300
 0.7777800 -.0160100
 0.8043300 -.0137000
 0.8296700 -.0115500
 0.8535600 -.0096200
 0.8758900 -.0079500
 0.8966700 -.0064600
 0.9157800 -.0050800
 0.9330000 -.0038500
 0.9484400 -.0028100
 0.9618900 -.0019900
 0.9734400 -.0013500
 0.9830000 -.0008600
 0.9904400 -.0004800
 0.9956700 -.0002100
 0.9988900 -.0000500
 1.0000000 0.0000000
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Polars for HQ 0/9 AIRFOIL (hq09-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   hq09-il50,000927.3 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   hq09-il50,000526 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   hq09-il100,000936.8 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   hq09-il100,000533.4 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   hq09-il200,000946.3 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   hq09-il200,000538.6 at α=3°Mach=0 Ncrit=5Xfoil predictionDetails
   hq09-il500,000951.8 at α=3°Mach=0 Ncrit=9Xfoil predictionDetails
   hq09-il500,000553.4 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   hq09-il1,000,000964.9 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   hq09-il1,000,000563.4 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
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