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An Approximate Determination of the Power Required to Move Control Surfaces as Related to Control-Booster Design

Description: "As a part of a general investigation of control boosters, preliminary calculations were made to indicate the sizes of control boosters necessary to move the controls of airplanes of various sizes. The analysis was based on the assumption that the controls were moved with a rapidity and amplitude equal to that measured with a fighter airplane in simulated combat. A corollary purpose consisted in determining the effect on reducing booster-power unit size of incorporating an energy accumulator in… more
Date: September 1945
Creator: Johnson, Harold I.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Variation of Hydrodynamic Impact Loads With Flight-Path Angle for a Prismatic Float at 3 Degree Trim and With a 22 1/2 Degree Angle of Dead Rise

Description: Report discusses the results of testing "to determine the relationship between impact normal acceleration and flight-path angle for seaplanes landing on smooth water" (from Summary). The testing was done with a model at high and low forward speeds at 3 degrees trim, a dead-angle rise of 22.5 degrees, and consistent weight.
Date: February 1945
Creator: Batterson, Sidney A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

XC-35 Gust Research Project Operation in Cumulus Congestus Cloud on July 31, 1941 Maximum Gust Intensities

Description: "On July 31, 1941 a turbulence survey was made with the XC-35 airplane of a large cumulus congestus cloud near Langley Field, Va. This bulletin presents a general description of conditions and the maximum gust intensities recorded during the flight" (p. 1).
Date: April 1942
Creator: Flight Research Loads Section
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

NACA Procedure for Flight Tests of Aileron Characteristics of Airplanes

Description: Report describes the standard procedure that NACA used for evaluating the aileron characteristics of airplanes. The variables measured in the testing are rolling velocity, aileron positions, aileron stick forces or tangential wheel force, indicated airspeed, altitude, free-air temperature, and rudder position. The step-by-step flight procedure is described and information regarding evaluation of the control data and general suggestions is included.
Date: July 1943
Creator: Johnson, Harold I.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The NACA Balanced-Diaphragm Dynamometer-Torque Indicator

Description: Report describes a balanced-diaphragm device for measuring dynamometer torque of single-cylinder or multicylinder engines that was developed for laboratory use. Design variables are described, included desired torque-measuring device characteristics, diaphragm design, pilot valve, the torque-indicating instrument, the capacity range, ability of reversed operation, and double-acting operation. The accuracy is described as satisfactory and effects of other variables are negligible.
Date: March 1944
Creator: Moore, Charles S.; Biermann, Arnold E. & Voss, Fred
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Maximum Rates of Control Motion Obtained From Ground Tests

Description: Report discusses the results of testing to determine the maximum rates of control stick (elevator) motion and corresponding maximum stick forces that could be exerted based on experiments with several pilots. The main topics explored were the comparison of the maximum rates of push and pull, maximum rates of push and pull when a mental restriction was placed on the pilot, and maximum rates at which the pilot though he would apply the elevator control forces versus the actual application of forc… more
Date: May 1944
Creator: Beeler, De E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Theoretical and Experimental Dynamic Loads for a Prismatic Float Having an Angle of Dead Rise of 22-1/2 Degrees

Description: Report discusses the maximum load, time to reach maximum load, and variation of load with time for prismatic floats in order to improve understanding of hydrodynamic theory for the landing impact of seaplane floats. Comparison of theoretical and experimental results and their applicability to flight impact are provided.
Date: July 1945
Creator: Mayo, Wilbur L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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