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Theoretical study of the lateral frequency response to gusts of a fighter airplane, both with controls fixed and with several types of autopilots
Report presenting a theoretical approach to determine the lateral frequency response of a fighter airplane to side gusts and rolling gusts at a Mach number of 0.7 and an altitude of 30,000 feet. Frequency response and power spectral density were determined with the controls fixed and in combination with three different basic types of attitude autopilots.
Date:
March 1956
Creator:
Adams, James J. & Mathews, Charles W.
System:
The UNT Digital Library
Effect of thickness, camber, and thickness distribution on airfoil characteristics at Mach numbers up to 1.0
Report presenting tests of a group of related NACA airfoil sections varying in maximum thickness, design lift coefficient, and thickness distribution in a two-dimensional open-throat wind tunnel at a range of Mach numbers. Normal-force, drag, and pitching-moment coefficients are presented with representative schileren photographs and pressure-distribution diagrams.
Date:
March 1956
Creator:
Daley, Bernard N. & Dick, Richard S.
System:
The UNT Digital Library