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An Investigation of Aileron Oscillations at Transonic Speeds on NACA 23012 and NACA 65-212 Airfoils by the Wing-Flow Method
An investigation is being conducted to determine the feasibility of studying aileron buzz by means of the wing-flow method. Two semispan models which had an aspect ratio of 6 and a taper ratio of 2 with quarter-chord half-span mass-balanced ailerons have been used. One had an NACA 23012 airfoil section and the second, an NACA 65-212 airfoil section. The ailerons on both models were subject to buzz over a small range of Mach number near 0.9. Data obtained by wing-flow testing agreed reasonably well with full-scale flight results.
Date:
December 29, 1948
Creator:
Crane, Harold L.
System:
The UNT Digital Library
An analytical method of estimating turbine performance
From Introduction: "An analytical method for estimating turbine performance from the blade angle8 and flow areas was therefore developed at the NACA Lewis laboratory and is described herein."
Date:
December 29, 1948
Creator:
Kochendorfer, Fred D. & Nettles, J. Cary
System:
The UNT Digital Library
An analytical method of estimating turbine performance
From Introduction: "An analytical method for estimating turbine performance from angles and flow areas was therefore developed at the NACA Lewis laboratory in 1947 and is described herein."
Date:
December 29, 1948
Creator:
Kochendorfer, Fred D. & Nettles, J. Cary
System:
The UNT Digital Library