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DSMA-523B AIRFOIL (dsma523b-il)

DSMA-523B AIRFOIL - McDonnell/Douglas DSMA-523 transonic airfoil with blunt trailing edge


Airfoil dsma523b-il
Details Dat file Parser  
(dsma523b-il) DSMA-523B AIRFOIL
McDonnell/Douglas DSMA-523 transonic airfoil with blunt trailing edge
Max thickness 11% at 36% chord.
Max camber 2.4% at 82% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
 DSMA-523B AIRFOIL
       60.       60.

 0.0       0.0
 0.000500  0.005069
 0.001000  0.007096
 0.002500  0.011063
 0.005090  0.015320
 0.007500  0.018417
 0.010000  0.020716
 0.012500  0.022651
 0.015000  0.024267
 0.020000  0.026918
 0.030000  0.030729
 0.040000  0.033459
 0.060000  0.037407
 0.080000  0.040367
 0.100000  0.042987
 0.120000  0.045198
 0.140000  0.047017
 0.160000  0.048543
 0.180000  0.049828
 0.200000  0.050902
 0.220000  0.051802
 0.240000  0.052563
 0.260000  0.053199
 0.280000  0.053729
 0.300000  0.054161
 0.320000  0.054513
 0.340000  0.054788
 0.360000  0.054998
 0.380000  0.055149
 0.400000  0.055240
 0.420000  0.055272
 0.440000  0.055247
 0.460000  0.055146
 0.480000  0.054973
 0.500000  0.054723
 0.520000  0.054390
 0.540000  0.053976
 0.560000  0.053486
 0.580000  0.052917
 0.600000  0.052269
 0.620000  0.051540
 0.640000  0.050726
 0.660000  0.049826
 0.680000  0.048832
 0.700000  0.047725
 0.720000  0.046494
 0.740000  0.045130
 0.760000  0.043625
 0.780000  0.041942
 0.800000  0.040043
 0.820000  0.037907
 0.840000  0.035502
 0.860000  0.032780
 0.880000  0.029666
 0.900000  0.026155
 0.920000  0.022185
 0.950000  0.017708
 0.960000  0.012642
 0.980000  0.006842
 1.000000  0.000308

 0.0       0.0
 0.000500 -0.005096
 0.001000 -0.007128
 0.002500 -0.011078
 0.005090 -0.015320
 0.007500 -0.018417
 0.010000 -0.020671
 0.012500 -0.022548
 0.015000 -0.024135
 0.020000 -0.026744
 0.030000 -0.030667
 0.040000 -0.033607
 0.060000 -0.037087
 0.080000 -0.041739
 0.100000 -0.044648
 0.120000 -0.046796
 0.140000 -0.048616
 0.160000 -0.050114
 0.180000 -0.051348
 0.200000 -0.052370
 0.220000 -0.053207
 0.240000 -0.053890
 0.260000 -0.054423
 0.280000 -0.054808
 0.300000 -0.055056
 0.320000 -0.055163
 0.340000 -0.055137
 0.360000 -0.054978
 0.380000 -0.054701
 0.400000 -0.054283
 0.420000 -0.053719
 0.440000 -0.053009
 0.460000 -0.052143
 0.480000 -0.051136
 0.500000 -0.049915
 0.520000 -0.048483
 0.540000 -0.046780
 0.560000 -0.044613
 0.580000 -0.042006
 0.600000 -0.038885
 0.620000 -0.035181
 0.640000 -0.030940
 0.660000 -0.026390
 0.680000 -0.021541
 0.700000 -0.016958
 0.720000 -0.012692
 0.740000 -0.008750
 0.760000 -0.005200
 0.780000 -0.002041
 0.800000  0.000686
 0.820000  0.002965
 0.840000  0.004757
 0.860000  0.006021
 0.880000  0.006687
 0.900000  0.006606
 0.920000  0.005630
 0.950000  0.003566
 0.960000  0.000348
 0.980000 -0.004210
 1.000000 -0.010109
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Polars for DSMA-523B AIRFOIL (dsma523b-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   dsma523b-il50,000920.9 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   dsma523b-il50,000520.6 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   dsma523b-il100,000923.3 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   dsma523b-il100,000527.9 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   dsma523b-il200,000929.8 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   dsma523b-il200,000539.3 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   dsma523b-il500,000949.6 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   dsma523b-il500,000560 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   dsma523b-il1,000,000973.2 at α=-1.25°Mach=0 Ncrit=9Xfoil predictionDetails
   dsma523b-il1,000,000577.3 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
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