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Wind tunnel tests of ailerons at various speeds i : ailerons of 0.20 airfoil chord and true contour with 0.35 aileron-chord extreme blunt nose balance on the naca 66,2-216 airfoil
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1943 |
| Description | Hinge-moment, lift, and pressure-distribution measurements were made in the two-dimensional test section of the NACA stability tunnel on a blunt-nose balance-type aileron on an NACA 66,2-216 airfoil at speeds up to 360 miles per hour corresponding to a Mach number of 0.475. The tests were made primarily to determine the effect of speed on the action of this type of aileron. The balance-nose radii of the aileron were varied from 0 to 0.02 of the airfoil chord and the gap width was varied from 0.0005 to 0.0107 of the airfoil chord. Tests were also made with the gap sealed. |
| File Size | 27944800 |
| Page Count | 77 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19930092929 |
| Archival Resource Key | ark:/13960/t7mp88011 |
| Language | English |
| Publisher Date | 1943-01-01 |
| Access Restriction | Open |
| Subject Keyword | Flying, High-speed Control Sticks-forces Ailerons, Balanced - Sealed-gap Ailerons - Wind Tunnel Tests Ailerons, Balanced - Hinge Moments Pressure Distribution-airfoils-naca 66,2-216 Airfoils-naca 66,2-216-char , Moments & Ordinates Low-drag Mach Number Wind Tunnel Tests-naca-stability Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
