DSMA-523B AIRFOIL (dsma523b-il)
DSMA-523B AIRFOIL - McDonnell/Douglas DSMA-523 transonic airfoil with blunt trailing edge
| 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
|
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for DSMA-523B AIRFOIL (dsma523b-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| dsma523b-il | 50,000 | 9 | 20.9 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dsma523b-il | 50,000 | 5 | 20.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dsma523b-il | 100,000 | 9 | 23.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dsma523b-il | 100,000 | 5 | 27.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dsma523b-il | 200,000 | 9 | 29.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dsma523b-il | 200,000 | 5 | 39.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dsma523b-il | 500,000 | 9 | 49.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dsma523b-il | 500,000 | 5 | 60 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dsma523b-il | 1,000,000 | 9 | 73.2 at α=-1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dsma523b-il | 1,000,000 | 5 | 77.3 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||