DSMA-523A AIRFOIL (dsma523a-il)
DSMA-523A AIRFOIL - McDonnell/Douglas DSMA-523 transonic airfoil with sharp trailing edge
| Details | Dat file | Parser | |
|
(dsma523a-il) DSMA-523A AIRFOIL McDonnell/Douglas DSMA-523 transonic airfoil with sharp trailing edge Max thickness 11% at 36% chord. Max camber 2.3% at 82% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
DSMA-523A 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 -0.026087
0.680000 -0.020633
0.700000 -0.015445
0.720000 -0.010574
0.740000 -0.006027
0.760000 -0.001872
0.780000 0.001892
0.800000 0.005224
0.820000 0.008108
0.840000 0.010505
0.860000 0.012374
0.880000 0.013645
0.900000 0.014169
0.920000 0.013798
0.950000 0.012338
0.960000 0.009726
0.980000 0.005773
1.000000 0.000498
|
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for DSMA-523A AIRFOIL (dsma523a-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| dsma523a-il | 50,000 | 9 | 20.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dsma523a-il | 50,000 | 5 | 18.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dsma523a-il | 100,000 | 9 | 20.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dsma523a-il | 100,000 | 5 | 25.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dsma523a-il | 200,000 | 9 | 27.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dsma523a-il | 200,000 | 5 | 37.4 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dsma523a-il | 500,000 | 9 | 47.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dsma523a-il | 500,000 | 5 | 59.3 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dsma523a-il | 1,000,000 | 9 | 70.3 at α=-0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dsma523a-il | 1,000,000 | 5 | 77.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||