TH 25816 HALE AIRFOIL (th25816-il)
TH 25816 HALE AIRFOIL - Naval Air Development Center/Doug Hall high altitude
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(th25816-il) TH 25816 HALE AIRFOIL Naval Air Development Center/Doug Hall high altitude Max thickness 25.7% at 48.3% chord. Max camber 4% at 52.9% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
TH 25816 HALE AIRFOIL
33. 29.
0.000010 -0.000740
0.002750 0.011590
0.010080 0.025520
0.021730 0.040160
0.037800 0.054880
0.058370 0.069480
0.083180 0.083880
0.111890 0.097850
0.144150 0.111140
0.179630 0.123520
0.217930 0.134760
0.258650 0.144680
0.301370 0.153090
0.345630 0.159820
0.390970 0.164730
0.436900 0.167650
0.482910 0.168380
0.528670 0.166630
0.574070 0.162320
0.618900 0.155590
0.662880 0.146610
0.705870 0.135610
0.747610 0.123140
0.787540 0.109780
0.824940 0.095910
0.859000 0.081630
0.889310 0.066520
0.916380 0.050420
0.940920 0.034190
0.963070 0.019490
0.981880 0.008260
0.995120 0.001880
1.000000 0.000000
0.000010 -0.000740
0.003550 -0.010760
0.014230 -0.019690
0.031030 -0.028760
0.053260 -0.037740
0.080440 -0.046450
0.112140 -0.054710
0.147910 -0.062390
0.187300 -0.069360
0.229810 -0.075480
0.274900 -0.080640
0.322030 -0.084720
0.370630 -0.087580
0.420110 -0.089100
0.469860 -0.089060
0.519410 -0.087140
0.568570 -0.083110
0.617240 -0.077050
0.665200 -0.069250
0.712070 -0.060130
0.757220 -0.049950
0.800320 -0.038620
0.841700 -0.026450
0.881490 -0.014670
0.919160 -0.005020
0.952730 0.000520
0.978740 0.001710
0.994690 0.000710
1.000000 0.000000
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Polars for TH 25816 HALE AIRFOIL (th25816-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| th25816-il | 50,000 | 9 | 2.4 at α=13.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| th25816-il | 50,000 | 5 | 7.1 at α=19° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| th25816-il | 100,000 | 9 | 15.1 at α=17.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| th25816-il | 100,000 | 5 | 12.2 at α=16° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| th25816-il | 200,000 | 9 | 21.5 at α=14.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| th25816-il | 200,000 | 5 | 19.1 at α=13.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| th25816-il | 500,000 | 9 | 54.7 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| th25816-il | 500,000 | 5 | 47.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| th25816-il | 1,000,000 | 9 | 74.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| th25816-il | 1,000,000 | 5 | 59.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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