AG38 (ag38-il)
AG38 - Drela AG38 airfoil
| Details | Dat file | Parser | |
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(ag38-il) AG38 Drela AG38 airfoil Max thickness 7% at 27.7% chord. Max camber 2% at 36.7% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
AG38
0.999999 0.004704
0.993621 0.005696
0.983682 0.007241
0.972066 0.009047
0.959633 0.010981
0.946835 0.012971
0.933981 0.014969
0.921234 0.016952
0.908447 0.018940
0.895764 0.020914
0.882852 0.022914
0.870677 0.024564
0.857810 0.026064
0.844779 0.027481
0.831613 0.028913
0.818263 0.030364
0.804818 0.031827
0.791388 0.033286
0.777951 0.034747
0.764549 0.036205
0.751106 0.037667
0.737702 0.039124
0.724342 0.040577
0.711051 0.042022
0.697928 0.043448
0.685186 0.044836
0.672293 0.046199
0.658783 0.047537
0.647516 0.048556
0.635011 0.049622
0.622485 0.050624
0.609531 0.051627
0.596533 0.052634
0.583312 0.053658
0.569976 0.054692
0.556633 0.055727
0.543315 0.056758
0.530000 0.057791
0.516728 0.058820
0.503472 0.059846
0.490290 0.060869
0.477236 0.061880
0.464539 0.062866
0.452148 0.063819
0.439870 0.064696
0.427640 0.065505
0.415386 0.066252
0.403250 0.066927
0.391172 0.067542
0.379063 0.068100
0.366729 0.068612
0.354113 0.069073
0.341333 0.069479
0.328488 0.069821
0.315654 0.070095
0.302897 0.070294
0.290182 0.070419
0.277486 0.070467
0.264739 0.070440
0.251950 0.070331
0.239044 0.070136
0.226021 0.069844
0.212912 0.069446
0.199800 0.068938
0.186742 0.068312
0.173780 0.067562
0.160907 0.066679
0.148128 0.065652
0.135369 0.064462
0.122667 0.063091
0.110044 0.061522
0.097563 0.059738
0.086115 0.057868
0.075071 0.055815
0.064507 0.053584
0.054572 0.051199
0.045308 0.048667
0.036786 0.046008
0.029161 0.043281
0.022616 0.040585
0.017243 0.038018
0.012940 0.035620
0.009579 0.033433
0.007013 0.031471
0.005102 0.029742
0.003685 0.028228
0.002589 0.026840
0.001700 0.025486
0.000978 0.024106
0.000451 0.022746
0.000094 0.021225
0.000009 0.019745
0.000172 0.018622
0.000581 0.017457
0.001293 0.016280
0.002383 0.015135
0.003836 0.014081
0.005649 0.013115
0.007886 0.012203
0.010612 0.011326
0.013931 0.010463
0.018027 0.009582
0.023174 0.008665
0.029676 0.007708
0.037756 0.006738
0.047349 0.005792
0.058120 0.004930
0.069666 0.004170
0.081678 0.003507
0.093975 0.002937
0.106461 0.002451
0.119072 0.002040
0.131774 0.001694
0.144550 0.001399
0.157380 0.001147
0.170260 0.000929
0.183177 0.000744
0.196137 0.000585
0.209128 0.000450
0.222152 0.000335
0.235196 0.000245
0.248262 0.000172
0.261351 0.000117
0.274460 0.000077
0.287589 0.000040
0.300735 0.000018
0.313898 0.000004
0.327086 -0.000005
0.340287 -0.000003
0.353486 -0.000003
0.366689 -0.000003
0.379895 -0.000001
0.393109 -0.000003
0.406322 -0.000002
0.419532 0.000001
0.432737 -0.000003
0.445943 0.000001
0.459157 0.000002
0.472370 -0.000001
0.485577 0.000002
0.498782 0.000001
0.511992 0.000000
0.525205 0.000001
0.538418 -0.000001
0.551625 -0.000001
0.564826 0.000001
0.578028 -0.000001
0.591236 -0.000002
0.604443 0.000000
0.617649 0.000000
0.630860 -0.000001
0.644076 0.000000
0.657286 0.000000
0.670495 0.000002
0.683700 0.000000
0.696909 0.000001
0.710122 -0.000001
0.723334 0.000000
0.736542 -0.000002
0.749746 -0.000002
0.762958 -0.000001
0.776172 0.000000
0.789383 0.000000
0.802589 0.000001
0.815788 0.000001
0.828992 0.000001
0.842199 0.000002
0.855403 -0.000002
0.868602 -0.000002
0.881798 -0.000002
0.895001 -0.000002
0.908208 -0.000001
0.921420 0.000000
0.934616 0.000001
0.947766 0.000002
0.960776 0.000000
0.973384 0.000000
0.984990 0.000000
0.994806 0.000000
1.000000 0.000001
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Polars for AG38 (ag38-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ag38-il | 50,000 | 9 | 34.2 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag38-il | 50,000 | 5 | 36 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag38-il | 100,000 | 9 | 49.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag38-il | 100,000 | 5 | 48.4 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag38-il | 200,000 | 9 | 64 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag38-il | 200,000 | 5 | 59.3 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag38-il | 500,000 | 9 | 81.3 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag38-il | 500,000 | 5 | 73.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag38-il | 1,000,000 | 9 | 92 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag38-il | 1,000,000 | 5 | 85.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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