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Prandtl-D root - NASA Preliminary Research Aerodynamic Design To Lower Drag (prandtl-d-root-ns)

Prandtl-D root - NASA Preliminary Research Aerodynamic Design To Lower Drag - NASA Preliminary Research Aerodynamic Design To Lower Drag (PRANDTL-D) glider root airfoil


Airfoil prandtl-d-root-ns
Details Dat file Parser  
(prandtl-d-root-ns) Prandtl-D root - NASA Preliminary Research Aerodynamic Design To Lower Drag
NASA Preliminary Research Aerodynamic Design To Lower Drag (PRANDTL-D) glider root airfoil
Max thickness 12% at 30.9% chord.
Max camber 3.5% at 37.1% chord
Source NASA
Source dat file
The dat file is in Selig format
Prandtl-D root - NASA Preliminary Research Aerodynamic Design To Lower Drag
0.99839 0.01595
0.98664 0.01580
0.95215 0.01710
0.89696 0.02355
0.82387 0.03690
0.80438 0.04073
0.77779 0.04590
0.75000 0.05124
0.72114 0.05668
0.69134 0.06218
0.66072 0.06768
0.62941 0.07312
0.59755 0.07840
0.56526 0.08341
0.53270 0.08800
0.50000 0.09201
0.46730 0.09530
0.43474 0.09777
0.40245 0.09936
0.37059 0.10000
0.33928 0.09971
0.30866 0.09846
0.27886 0.09632
0.25000 0.09339
0.22221 0.08978
0.19562 0.08553
0.17033 0.08072
0.14645 0.07539
0.12408 0.06963
0.10332 0.06345
0.08427 0.05691
0.06699 0.05017
0.05156 0.04318
0.03806 0.03575
0.02653 0.02897
0.01704 0.02201
0.00961 0.01424
0.00428 0.00784
0.00107 0.00353
0.00000 0.00000
0.00107 -0.00520
0.00428 -0.00882
0.00961 -0.01205
0.01704 -0.01502
0.02653 -0.01800
0.03806 -0.02062
0.05156 -0.02237
0.06699 -0.02406
0.08427 -0.02524
0.10332 -0.02598
0.12408 -0.02642
0.14645 -0.02653
0.17033 -0.02631
0.19562 -0.02584
0.22221 -0.02512
0.25000 -0.02419
0.27886 -0.02308
0.30866 -0.02184
0.33928 -0.02047
0.37059 -0.01904
0.40245 -0.01754
0.43474 -0.01602
0.46730 -0.01451
0.50000 -0.01301
0.53270 -0.01156
0.56526 -0.01017
0.59755 -0.00885
0.62941 -0.00761
0.66072 -0.00646
0.69134 -0.00542
0.72114 -0.00448
0.75000 -0.00364
0.77779 -0.00291
0.80438 -0.00227
0.82005 -0.00194
0.89553 0.00255
0.95184 0.00908
0.98662 0.01411
0.99839 0.01595
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Polars for Prandtl-D root - NASA Preliminary Research Aerodynamic Design To Lower Drag (prandtl-d-root-ns)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   prandtl-d-root-ns50,000922.8 at α=12.75°Mach=0 Ncrit=9Xfoil predictionDetails
   prandtl-d-root-ns100,000951.4 at α=9.5°Mach=0 Ncrit=9Xfoil predictionDetails
   prandtl-d-root-ns200,000976.5 at α=8.25°Mach=0 Ncrit=9Xfoil predictionDetails
   prandtl-d-root-ns500,0009102.5 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   prandtl-d-root-ns1,000,0009117.9 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   prandtl-d-root-ns2,000,0009119.4 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   prandtl-d-root-ns5,000,0009128.8 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
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