ARA-D 6% AIRFOIL (arad6-il)
ARA-D 6% AIRFOIL - Aeronautical Research Association/Bocci-Dowty Rotol ARA-D 6% thick propeller airfoil
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(arad6-il) ARA-D 6% AIRFOIL Aeronautical Research Association/Bocci-Dowty Rotol ARA-D 6% thick propeller airfoil Max thickness 6% at 20% chord. Max camber 5% at 45% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
ARA-D 6% AIRFOIL 26. 26. 0.00000 0.00000 .00300 .009099 .01000 .017152 .02000 .024678 .04000 .035135 .07000 .045809 .10000 .053377 .15000 .062118 .20000 .068235 .25000 .072750 .30000 .076067 .35000 .078178 .40000 .079022 .45000 .078668 .50000 .077173 .55000 .074566 .60000 .070912 .65000 .066260 .70000 .060628 .75000 .054022 .80000 .046416 .85000 .037752 .90000 .028002 .95000 .017193 .97500 .011484 1.00000 .005500 0.00000 0.00000 .00300 -.004658 .01000 -.007411 .02000 -.008934 .04000 -.009318 .07000 -.007339 .10000 -.004076 .15000 .002198 .20000 .007996 .25000 .012750 .30000 .016295 .35000 .018834 .40000 .020553 .45000 .021539 .50000 .021827 .55000 .021435 .60000 .020401 .65000 .018750 .70000 .016501 .75000 .013723 .80000 .010504 .85000 .006940 .90000 .003084 .95000 -.001015 .97500 -.003184 1.00000 -.005500 |
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Similar airfoils
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Polars for ARA-D 6% AIRFOIL (arad6-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| arad6-il | 50,000 | 9 | 46 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| arad6-il | 50,000 | 5 | 45.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| arad6-il | 100,000 | 9 | 68.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| arad6-il | 100,000 | 5 | 66.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| arad6-il | 200,000 | 9 | 93 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| arad6-il | 200,000 | 5 | 86 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| arad6-il | 500,000 | 9 | 122.5 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| arad6-il | 500,000 | 5 | 105.6 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| arad6-il | 1,000,000 | 9 | 139.7 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| arad6-il | 1,000,000 | 5 | 106 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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