AG19 (ag19-il)
AG19 - Drela AG19 airfoil
| Details | Dat file | Parser | |
|
(ag19-il) AG19 Drela AG19 airfoil Max thickness 5.4% at 20.6% chord. Max camber 2.2% at 44.2% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
AG19
0.999992 0.000244
0.994067 0.000848
0.982082 0.002113
0.968544 0.003504
0.954708 0.004914
0.940826 0.006276
0.926943 0.007613
0.913056 0.008933
0.899168 0.010245
0.885282 0.011547
0.871396 0.012840
0.857515 0.014123
0.843633 0.015399
0.829754 0.016658
0.815876 0.017909
0.801995 0.019144
0.788118 0.020364
0.774240 0.021567
0.760358 0.022757
0.746480 0.023934
0.732598 0.025098
0.718714 0.026246
0.704832 0.027382
0.690952 0.028505
0.677070 0.029611
0.663191 0.030702
0.649316 0.031769
0.635436 0.032803
0.621559 0.033813
0.607686 0.034792
0.593811 0.035742
0.579936 0.036661
0.566066 0.037549
0.552198 0.038403
0.538328 0.039225
0.524462 0.040010
0.510601 0.040760
0.496741 0.041474
0.482880 0.042149
0.469025 0.042788
0.455177 0.043387
0.441328 0.043948
0.427484 0.044466
0.413649 0.044946
0.399815 0.045383
0.385986 0.045776
0.372169 0.046125
0.358355 0.046428
0.344545 0.046682
0.330750 0.046887
0.316965 0.047037
0.303185 0.047134
0.289421 0.047171
0.275674 0.047146
0.261933 0.047054
0.248213 0.046888
0.234514 0.046643
0.220830 0.046310
0.207177 0.045881
0.193554 0.045344
0.179962 0.044689
0.166424 0.043904
0.152931 0.042974
0.139504 0.041884
0.126159 0.040617
0.112901 0.039151
0.099774 0.037462
0.086793 0.035521
0.074020 0.033292
0.061500 0.030726
0.049351 0.027778
0.037754 0.024395
0.027090 0.020576
0.018069 0.016536
0.011377 0.012750
0.006933 0.009581
0.004065 0.007011
0.002186 0.004880
0.000960 0.003044
0.000235 0.001406
0.000001 -0.000094
0.000368 -0.001552
0.001471 -0.002908
0.003259 -0.004084
0.005777 -0.005206
0.009368 -0.006368
0.014713 -0.007619
0.022632 -0.008896
0.033028 -0.009988
0.044948 -0.010773
0.057612 -0.011265
0.070626 -0.011515
0.083847 -0.011575
0.097208 -0.011488
0.110664 -0.011286
0.124193 -0.010995
0.137773 -0.010634
0.151402 -0.010216
0.165062 -0.009753
0.178754 -0.009253
0.192471 -0.008724
0.206209 -0.008174
0.219965 -0.007607
0.233740 -0.007028
0.247527 -0.006440
0.261333 -0.005847
0.275149 -0.005250
0.288979 -0.004652
0.302827 -0.004054
0.316687 -0.003459
0.330560 -0.002868
0.344449 -0.002282
0.358351 -0.001705
0.372267 -0.001137
0.386195 -0.000582
0.400136 -0.000039
0.414079 0.000487
0.428014 0.000997
0.441936 0.001488
0.455848 0.001958
0.469754 0.002410
0.483648 0.002838
0.497536 0.003246
0.511417 0.003632
0.525297 0.003999
0.539171 0.004338
0.553041 0.004649
0.566907 0.004932
0.580771 0.005183
0.594629 0.005404
0.608483 0.005597
0.622333 0.005758
0.636177 0.005888
0.650015 0.005989
0.663852 0.006060
0.677688 0.006098
0.691521 0.006104
0.705354 0.006082
0.719189 0.006029
0.733027 0.005945
0.746863 0.005833
0.760702 0.005691
0.774544 0.005518
0.788385 0.005316
0.802230 0.005089
0.816081 0.004833
0.829932 0.004550
0.843784 0.004242
0.857640 0.003908
0.871495 0.003551
0.885353 0.003171
0.899212 0.002768
0.913070 0.002347
0.926931 0.001903
0.940790 0.001439
0.954652 0.000956
0.968488 0.000451
0.982076 -0.000064
0.994074 -0.000511
1.000008 -0.000710
|
Dat file parser warnings
|
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for AG19 (ag19-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ag19-il | 50,000 | 9 | 36.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag19-il | 50,000 | 5 | 37.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag19-il | 100,000 | 9 | 51.7 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag19-il | 100,000 | 5 | 48.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag19-il | 200,000 | 9 | 66.1 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag19-il | 200,000 | 5 | 60.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag19-il | 500,000 | 9 | 81.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag19-il | 500,000 | 5 | 77.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag19-il | 1,000,000 | 9 | 95.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag19-il | 1,000,000 | 5 | 90.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||