BOEING-VERTOL VR-1 AIRFOIL (vr1-il)
BOEING-VERTOL VR-1 AIRFOIL - Boeing-Vertol VR-1 rotorcraft airfoil
| Details | Dat file | Parser | |
|
(vr1-il) BOEING-VERTOL VR-1 AIRFOIL Boeing-Vertol VR-1 rotorcraft airfoil Max thickness 11% at 35.3% chord. Max camber 1.5% at 43.3% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
BOEING-VERTOL VR-1 AIRFOIL 25. 25. 0. 0. .00559 .01673 .01850 .02600 .02943 .03066 .03729 .03336 .05173 .03747 .08439 .04440 .11326 .04935 .15252 .05505 .19215 .05957 .23220 .06329 .31250 .06812 .35269 .06934 .43331 .06947 .51428 .06632 .55468 .06349 .59474 .05991 .63471 .05567 .67453 .05087 .75387 .03984 .83291 .02748 .91183 .01451 .94622 .00881 .98650 .00223 1.0 .0000 0. 0. .00559 -.01001 .01850 -.01570 .02943 -.01910 .03729 -.02120 .05173 -.02430 .08439 -.02965 .11326 -.03270 .15252 -.03580 .19215 -.03795 .23220 -.03985 .31250 -.04045 .35269 -.04040 .43331 -.03880 .51428 -.03580 .55468 -.03395 .59474 -.03180 .63471 -.02920 .67453 -.02650 .75387 -.02050 .83291 -.01382 .91183 -.00695 .94622 -.00395 .98650 -.00083 1.0 .0000 |
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for BOEING-VERTOL VR-1 AIRFOIL (vr1-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| vr1-il | 50,000 | 9 | 30.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr1-il | 50,000 | 5 | 30 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr1-il | 100,000 | 9 | 46.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr1-il | 100,000 | 5 | 44.1 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr1-il | 200,000 | 9 | 63.5 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr1-il | 200,000 | 5 | 53.6 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr1-il | 500,000 | 9 | 72.8 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr1-il | 500,000 | 5 | 61.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr1-il | 1,000,000 | 9 | 77.8 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr1-il | 1,000,000 | 5 | 75.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||