Technical Report Archive & Image Library (TRAIL) - 47 Matching Results

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An analytical study of wing and tail loads associated with an elevator deflection

Description: From Introduction: "The present paper covers step 1 of the outlined investigation, includes methods of computing the variation of wing and tail loads, and gives numerical results of the application of the theory to the BT-9B airplane. Finally, theoretical formulas are developed and charts are given for computing the maximum increments of wing load, the down-tail load, and the up-tail load following a given elevator displacement."
Date: June 1941
Creator: Pearson, H. A. & Garvin, J. B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Bending and Shear Stresses Developed by the Instantaneous Arrest of the Root of a Cantilever Beam Rotating With Constant Angular Velocity About a Transverse Axis Through the Root

Description: From Summary: "A theoretical investigation was made of the behavior of a cantilever beam in rotational motion about a transverse axis through the root determining the stresses, the deflections, and the accelerations that occur in the beam as a result of the arrest of motion. The equations for bending and shear stress reveal that, at a given percentage of the distance from root to tip and at a given trip velocity, the bending stresses for a particular mode are independent of the length of the be… more
Date: June 1945
Creator: Stowell, Elbridge Z.; Schwartz, Edward B. & Houbolt, John C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Characteristics of Two Model Six-Blade Counterrotating Pusher Propellers of Conventional and Improved Aerodynamic Design

Description: Two airfoil plans were used for propeller blades. One is modified Clark Y section designed for structural reliability and the second an NACA 16 airfoil section designed to produce minimum aerodynamic losses. At low air speeds, the propeller designed for aerodynamic effects showed a gain of from 1.5 to 4.0 percent in propulsive efficiency over the conventional type depending on the pitch. Because of the numerous variables involved, the effect of each one on the aerodynamic characteristics of the… more
Date: June 1942
Creator: McHugh, James G. & Pepper, Edward
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Column and plate compressive strengths of aircraft structural materials: 17S-T aluminum-alloy sheet

Description: From Summary: "Column and plate compressive strengths of 17S-T aluminum-alloy sheet were determined both within and beyond the elastic range from tests of thin-strip columns and from local-instability tests of formed Z- and channel-section columns. These tests are part of an extensive research investigation to provide data on the structural strengths of various aircraft materials. Results are presented in the form of curves and charts that may be used in the design and analysis of aircraft stru… more
Date: June 1945
Creator: Heimerl, George J. & Roy, J. Albert
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Column and Plate Compressive Strengths of Aircraft Structural Materials: 24S-T Aluminum-Alloy Sheet

Description: "Column and plate compressive strengths of 24S-T aluminum-alloy sheet were determined both within and beyond the elastic range from tests of thin-strip columns and from local-instability tests of formed Z-end channel-section columns. These tests are the first of a series in an extensive research investigation to provide data on the structural strength of various aircraft materials. The results, which are presented in the form of curves and charts that may be used in the design and analysis of a… more
Date: June 1945
Creator: Lundquist, Eugene E.; Schuette, Evan H.; Heimerl, George J. & Roy, J. Albert
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Comparison of the Effects of Four-Blade Dual- and Single-Rotation Propellers on the Stability and Control Characteristics of a High-Powered Single-Engine Airplane

Description: Report presenting a scale powered model of the Douglas XSB2D-1 airplane tested with a four-blade dual-rotation propeller and a four-blade single-rotation propeller. To make the results more directly comparable, no other changes were made to the model. Results regarding longitudinal stability, directional characteristics, and lateral stability are provided.
Date: June 1944
Creator: Harper, Charles W. & Wick, Bradford H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Compressive Strength of Flat Panels with Z- and Hat-Section Stiffeners

Description: Compression tests were conducted on 247 panels with Z-section stiffeners and 304 panels with hat-section stiffeners. Specimens were constructed from artificially aged Alclad 24S aluminum alloy with minimum guaranteed yield strengths of 64 and 57 ksi for stiffeners and sheet materials, respectively. Height, thickness, and spacing of stiffeners, sheet thickness, and length of specimens were varied systematically to show effects of changes in these dimensions on panel strength. Results show averag… more
Date: June 1944
Creator: Kotanchik, Joseph N.; Weinberger, Robert A.; Zender, George W. & Neff, John, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A correlation of loadings and afterbody length-beam ratios of various flying-boat hulls

Description: "The gross weight, beam, and afterbody length of 12 contemporary flying boats and amphibians with pointed afterbodies are tabulated and correlated. For most of the hulls considered, the afterbody length-beam ratios are shown to be directly proportion to the gross-load coefficients" (p. 1).
Date: June 1946
Creator: Parkinson, John B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Correlation of the Effects of Compression Ratio and Inlet-Air Temperature on the Knock Limits of Aviation Fuels in a CFR Engine 2

Description: Report presenting the knock-limited performance of nine fuels comprising isolated members of four classes of hydrocarbons in the form of three-dimensional plots of fuel-air ratio, compression temperature, and compression-air density.
Date: June 1946
Creator: Alquist, Henry E.; O'Dell, Leon & Evvard, John C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Design of power-plant installations pressure-loss characteristics of duct components

Description: "A correlation of what are believed to be the most reliable data available on duct components of aircraft power-plant installations is presented. The information is given in a convenient form and is offered as an aid in designing duct systems and, subject to certain qualifications, as a guide in estimating their performance. The design and performance data include those for straight ducts; simple bends of square, circular, and elliptical cross sections; compound bends; diverging and converging … more
Date: June 1944
Creator: Henry, John R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The determination of effective column length from strain measurements

Description: From Summary: "A method is presented for the experimental determination of the effective length of a column for which the end conditions are unknown by establishing the points of zero curvature from readings of strain gages distributed along the length of the column. Tests of four columns of different cross sections indicated that the proposed method gives satisfactory results even when there is considerable scatter in the strain-gage readings."
Date: June 1944
Creator: Schuette, Evan H. & Roy, J. Albert
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of an aromatic mixture added to two 100-octane fuels on engine temperatures and fuel consumption

Description: Report presenting tests conducted with an air-cooled cylinder on two fuels rated at approximately 100-octane number by the C.F.R. aviation method with and without a 40-percent addition of an aromatic mixture. The aromatic mixture consisted of 50 percent toluene, 37.5 percent xylene, and 12.5 percent benzene. Results regarding engine performance and engine temperature are provided.
Date: June 1942
Creator: Krsek, Alois, Jr. & Jones, Anthony W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The effect of dead rise upon the high-angle porpoising characteristics of two planing surfaces in tandem

Description: Report presenting porpoising tests of three rudimentary models composed of two V-bottom planing surfaces in tandem and fitted with a tail plane. The upper and lower branches of the upper trim limit of stability were determined for three angles of dead rise and two depths of step.
Date: June 1943
Creator: Benson, James M. & Klein, Milton M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of fabric deflection at high speeds on the aerodynamic characteristics of the horizontal tail surface of an SB2D-1 airplane

Description: Report presenting an investigation of a full-scale horizontal tail surface to determine the elevator-fabric deflection at high speeds and the aerodynamic effects of the fabric deflection. Two fabric-covered elevators differing only in rib spacing and a solid wooden elevator were tested. Results regarding fabric deflection and aerodynamic characteristics are provided.
Date: June 1945
Creator: Schueller, Carl F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The effect of pitch on force and moment characteristics of full-scale propellers of five solidities

Description: Report presenting an investigation in the 20-foot propeller-research tunnel to determine the effect of variations in angle of pitch on the aerodynamic characteristics of several propeller combinations. The combinations investigated included two-, three-, four-, and six-blade single-rotating propellers and a six-blade dual-rotating propeller on a nacelle with four angles of thrust axis. The propulsive efficiency was found to decrease as the angle of pitch increased.
Date: June 1942
Creator: Runckel, Jack F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of various carburetor throttle settings on the flow characteristics at the outlet of a supercharger inlet elbow

Description: Report presenting an investigation to determine the effect of varying the carburetor throttle settings on the flow characteristics at the outlet of the supercharger inlet elbow. Air flow tests were made at several carburetor throttle settings ranging from open to closed. Results regarding distortion and turbulence are provided.
Date: June 1945
Creator: Moses, Jason J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of wing loading and altitude on lateral stability and control characteristics of an airplane as determined by tests of a model in the free-flight tunnel

Description: Report presenting an investigation to determine the effects of wing loading and altitude on lateral stability and control in the free-flight tunnel. The results of flight tests of the model were correlated with calculated stability boundaries, and an effort was made to determine for each loading condition the airplane configuration that gave the best flight characteristics. Results regarding the lateral stability, lateral control, and general flight behavior are provided.
Date: June 1943
Creator: Campbell, John P. & Seacord, Charles L., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The effects of an increase in the concentration of ethylene dibromide in a leaded fuel on lead deposition, corrosion of exhaust valves, and knock-limited power

Description: Report presenting an investigation of the use of ethylene dibromide to leaded fuel in order to prevent lead deposits within the cylinder. It is meant to react with lead to form volatile compounds that will be scavenged with exhaust gases. Results regarding the lead deposits, knock-limited effective pressures, performance, and temperatures are provided.
Date: June 1945
Creator: Mulcahy, B. A. & Zipkin, M. A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Effects of Static Margin and Rotational Damping in Pitch on the Longitudinal Stability Characteristics of an Airplane as Determined by Tests of a Model in the NACA Free-Flight Tunnel

Description: Report presenting the determination of the effects of static margin and rotational damping in pitch on the longitudinal stability characteristics of an airplane by flight tests of a model in the NACA free-flight tunnel. The rotational damping in pitch was varied over a wide range by using horizontal tails that varied in area from 0 to 24 percent of the wing area. Results regarding the effect of variation of static margin and effect of variation of rotational damping are provided.
Date: June 1944
Creator: Campbell, John P. & Paulson, John W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Evaluation of the Induced-Velocity Field of an Idealized Helicopter Rotor

Description: Report presenting a concept of a simplified vortex system of a rotor wake in order to obtain a formula for the normal component of induced velocity along the fore-and-aft diameter of the rotor disk of a helicopter rotors.
Date: June 1945
Creator: Coleman, Robert P.; Feingold, Arnold M. & Stempin, Carl W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental Determination of the Yawing Moment Due to Yawing Contributed by the Wing, Fuselage, and Vertical Tail of a Midwing Airplane Model

Description: Report presenting values of the lateral-stability derivative, the rate of change of yawing-moment coefficient with yawing angular velocity, contributed by the wing, the fuselage, and the vertical tail, which have been determined for a midwing airplane model by the free-oscillation method.
Date: June 1943
Creator: Campbell, John P. & Mathews, Ward O.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Fatigue Characteristics of Spot-Welded 24S-T Aluminum Alloy

Description: Report presenting the results of an investigation of the fatigue characteristics of spot-welded 24S-T aluminum alloy. The static shear strength of spot welds in lap joints of 24S-T alclad increases with increasing sheet thickness for thicknesses in the range of 0.025 inch to 0.032 inch.
Date: June 1943
Creator: Russell, H. W.; Jackson, L. R.; Grover, H. J. & Beaver, W. W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Flight Investigation of the Thermal Properties of an Exhaust Heated Wing De-Icing System on a Lockheed 12-A Airplane

Description: "The thermal properties are presented for the exhaust heated wing de-icing system of a Lockheed 12-A airplane which has successfully prevented a wing icing in 25 hours of flying in various icing conditions. The quantities of heat supplied for de-icing of the wings under various conditions were measured and are presented. The distribution of temperatures above the ambient air temperature for the wing surface under various operating conditions are given" (p. 1).
Date: June 1941
Creator: Rodert, Lewis A. & Clousing, Lawrence A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Studies of the Horizontal-Tail Loads Experienced by a Fighter Airplane in Abrupt Maneuvers

Description: Report presenting flight measurements made on a modern pursuit airplane to determine the approximate magnitude of the horizontal tail loads in accelerated flight. Pressures at a few points were used as an index of the tail loads by correlating these pressures with complete pressure-distribution data obtained in the NACA full-scale tunnel.
Date: June 1944
Creator: Flight Research Maneuvers Section
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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