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open access

Column and Plate Compressive Strengths of Aircraft Structural Materials: Extruded 14S-T Aluminum Alloy

Description: "Column and plate compressive strengths of extruded 14S-T aluminum alloy were determined both within and beyond the elastic range from tests of flat-end H-section columns and from local-instability tests of H-, Z-, and channel-section columns. These tests are part of an extensive research investigation to provide data on the structural strength of various aircraft materials. The results are presented in the form of curves and charts that are suitable for use in the design and analysis of aircra… more
Date: May 1946
Creator: Heimerl, George J. & Niles, Donald E.
open access

Effect of additions of aromatics on the knocking characteristics of several 100-octane fuels at two engine speeds

Description: Report presenting testing at two engine speeds on six representative fuels rated at 100-octane number by the C.F.R. aviation method. Blends of the fuels with benzene, toluene, xylene, and isopropyl comprise nine other fuels, leading to testing on 15 fuels. Results regarding the tests at 2000 rpm and 250 degrees Fahrenheit inlet-air temperature, at 3100 rpm and 250 degrees Fahrenheit inlet-air temperature, 2000 rpm and 150 degrees Fahrenheit inlet-air temperature, and 3100 rpm and 150 degrees Fa… more
Date: May 1942
Creator: Biermann, Arnold E.; Corrington, Lester C. & Harries, Myron L.
open access

The effect of compressibility on two-dimensional tunnel-wall interference for a symmetrical airfoil

Description: Summary: The effective change in the velocity of flow past a wing section, caused by the presence of wind-tunnel walls, is known for potential flow. This theory is extended by investigation of the two-dimensional compressible flow past a thin Rankine Oval. It is shown that for a symmetrical section at zero angle of attack the velocity increment due to the tunnel walls in the incompressible case must be multiplied by the factor 1/1-M^2 to take account of compressibility effects. The Mach numb… more
Date: May 1943
Creator: Nitzberg, Gerald E.
open access

Effect of inlet-air velocity distribution on the metering pressure of an injection-type aircraft carburetor

Description: Report presenting tests of a three-barrel pressure carburetor to determine the effect of nonuniformity of the air flow in the intake duct on the metering of the carburetor. Measurements were made in the air side of the metering system and in the carburetor barrels for a variety of flow distributions. Results regarding the metering pressure, altitude compensation, effect of throttle on the metering characteristics, and flow of air around the bends are provided
Date: May 1942
Creator: Kinghorn, George F.
open access

The Effect of Internal Pressure on the Buckling Stress of Thin-Walled Circular Cylinders Under Torsion

Description: "The results of a series of tests to determine the effect of internal pressure on the buckling load of a thin cylinder under an applied torque indicated that internal pressure raises the shear buckling stress. The experimental results were analyzed with the aid of previously developed theory and a simple interaction formula was derived" (p. 1).
Date: May 1944
Creator: Crate, Harold; Batdorf, S. B. & Baab, George W.
open access

Effect of Oil Flow to Piston on Piston-Ring Sticking and Oil Consumption in a Single-Cylinder Engine

Description: Report presenting an investigation to determine the effect of the amount of oil flow to the piston on the ring-sticking characteristics of a piston and ring assembly and on the engine oil consumption. Results regarding the blow-by, lubrication, oil consumption, and method of supplying oil are provided.
Date: May 1945
Creator: Tauschek, Max J.; Corrington, Lester C. & Meigs, John B.
open access

An Electromagnetic-Analogy Method of Solving Lifting-Surface-Theory Problems

Description: Report presenting a method for making lifting-surface calculations by means of magnetic measurements of an electromagnetic-analogy model. The method is based on the perfect analogy between the strength of the magnetic field around a conductor and the strength of the induced-velocity field around a vortex.
Date: May 1945
Creator: Swanson, Robert S. & Crandall, Stewart M.
open access

Engine Tests of Pressurized Shunt-Type Cooling Systems for a Liquid-Cooled Engine

Description: Report presenting tests conducted to determine the performance of two pressurized shunt-type cooling systems for liquid-cooled aircraft engines using a mixture of 30 percent AN-E-2 ethylene glycol and 70 percent water as the coolant. Results regarding effect of engine speed on coolant-flow rate, effect of expansion-tank pressure on coolant-flow rate, relation between pump-inlet pressure and expansion-tank pressure, variation of coolant-flow rate with pump-inlet pressure, flow rate through the s… more
Date: May 1945
Creator: Manganiello, Eugene J.; Lundin, Bruce T. & Povolny, John H.
open access

An Experimental Investigation of Rectangular Exhaust-Gas Ejectors Applicable for Engine Cooling

Description: Report presenting an experimental investigation of rectangular exhaust-gas ejector pump to provide data that would serve as a guide to the design of ejector applications for aircraft engines with marginal cooling. With a decrease in the quantity of air pumped and an increase in the length of an ejector, the ejector pressure rise increases to optimum values. Results regarding straight ejectors, diffuser ejectors, curved ejectors, ejector aspect ratio, divided ejectors, multistage ejectors, and n… more
Date: May 1945
Creator: Manganiello, Eugene J. & Bogatsky, Donald
open access

Fatigue strength and related characteristics of joints in 24S-T Alclad sheet

Description: Report includes tension fatigue test results on the following types of samples of 0.040-inch alclad 24s-t: (1) monoblock sheet samples as received and after a post-aging heat treatment, (2) "sheet efficiency" samples (two equally stressed sheets joined by a single transverse row of spot welds) both as received and after post-aging, (3) spot-welded lap-joint samples as received and after post-aging, and (4) roll-welded lap-joint samples. (author).
Date: May 1944
Creator: Russell, H. W.; Jackson, L. R.; Grover, H. J. & Beaver, W. W.
open access

A flight investigation of internally balanced sealed ailerons in the presence of a balanced split flap

Description: Report presenting flight tests made with a modified Ryan ST airplane to determine the effect on aileron characteristics of various arrangements of balanced split flaps covering that portion of the wing span occupied by the ailerons. With the flaps fully extended, the aileron effectiveness was reduced by approximately 18 percent of the effectiveness measured with ailerons alone.
Date: May 1942
Creator: Williams, W. C.
open access

A flight investigation of short-period longitudinal oscillations of an airplane with free elevator

Description: Report presenting a flight investigation to check the results of a theoretical analysis of longitudinal stability of an airplane with free controls. Tests used a Fairchild XR2K-1 airplane on which the weight moment and the aerodynamic balance of the elevator were varied to bring it into a condition where unstable short-period oscillations were encountered.
Date: May 1942
Creator: Phillips, William H.
open access

Formulas for propellers in yaw and charts of the side-force derivative

Description: Report presenting formulas for propellers for the rate of change of side-force coefficient with angle of yaw and for the rate of change of pitching-moment coefficient with angle of yaw. Charts of side-force derivatives are given for two propellers of different plan forms.
Date: May 1943
Creator: Ribner, Herbert S.
open access

Free-spinning-tunnel tests of a model of a canard airplane

Description: Report presenting a series of tests made in the 15-foot free-spinning tunnel to study the spin characteristics of a model of a hypothetical canard airplane, which was designed to be about the same size and have the same general aerodynamic characteristics as a Boeing B-247 airplane. The model spun normally and had excellent recovery characteristics.
Date: May 1943
Creator: Pepoon, Philip W.
open access

Full-scale tunnel investigation of the pressure distribution over the tail of the P-47B airplane

Description: Report presenting measurements made of the pressures of the tail surfaces of the Republic Aviation Corporation P-47B airplane in the full-scale tunnel. Pressures were measured over the horizontal and vertical tail surfaces for several angles of attack and angles of yaw with numerous control-surface deflections to provide a check on the design loads. Results regarding the normal-force coefficients and predictions of forces on horizontal tail surfaces are provided.
Date: May 1943
Creator: Dingeldein, Richard C.
open access

The Influence of Bulkhead Spacing on Bending Stresses Due to Torsion

Description: Report presenting the reasons for the existence of bending stresses due to torsion and the theoretical formulas applying to rectangular boxes with finite bulkhead spacing. Tests are described which were made to verify the theory, strains being measured on a rectangular torsion box with four bulkhead spacings. Results regarding normal stresses are provided.
Date: May 1942
Creator: Kuhn, Paul
open access

An Instrument for the Determination of Rain Densities in Flight

Description: Report presenting an investigation to develop an instrument for the determination of rain densities in this range in flight. The major requirements for the instrument are ease of operation, minimum weight and bulk, rapid response, and simplicity of installation.
Date: May 1943
Creator: Bemis, John R. & Houghton, Henry G., Jr.
open access

An Investigation of a Thermal Ice-Prevention System for a C-46 Cargo Airplane 5: Effect of Thermal System on Airplane Cruise Performance

Description: Report presenting flight tests conducted to evaluate the effect of a thermal ice prevention system on the aerodynamic performance of a C-46 cargo airplane. The installation of the thermal ice-prevention system was found to reduce the indicated airspeed by about 6 miles per hour. Results regarding the overall performance change resulting from the installation of the thermal system, reduction of power attributed to heat-exchanger exhaust-gas back pressure, reduction of power attributed to the int… more
Date: May 1945
Creator: Selna, James
open access

An Investigation of a Thermal Ice-Prevention System for a C-46 Cargo Airplane 6: Dry-Air Performance of Thermal System at Several Twin- and Single-Engine Operating Conditions at Various Altitudes

Description: Report presenting flight tests to establish the dry-air-performance characteristics of a thermal ice-prevention system at various operating conditions and altitudes. Results regarding twin-engine tests and single-engine tests of characteristics such as skin temperatures and location of heating are provided.
Date: May 1945
Creator: Selna, James & Kees, Harold L.
open access

An investigation of aircraft heaters 12: performance of a formed-plate crossflow exhaust gas and air heat exchanger

Description: Report presenting performance data on a Trane exhaust gas and air heat exchanger. Heat transfer rates were measured using specified exhaust gas rates and ventilating-air rates. The measured thermal outputs and static pressure drops are compared with predicted magnitudes.
Date: May 1943
Creator: Boelter, L. M. K.; Dennison, H. G.; Guibert, A. G. & Morrin, E. H.
open access

Investigation of Effect of Sideslip on Lateral Stability Characteristics 1: Circular Fuselage with Variations in Vertical-Tail Area and Tail Length With and Without Horizontal Tail Surface

Description: Report presenting the results of tests of a circular fuselage with various combinations of tail lengths and vertical tail surfaces with and without the horizontal tail surface in the 6- by 6-foot test section of the stability tunnel in the form of diagrams of variation of coefficients of lateral force and yawing moment with angle of yaw and angle of attack.
Date: May 1944
Creator: Fehlner, Leo F. & MacLachlan, Robert
open access

Jet-boundary corrections for reflection-plane models in rectangular wind tunnels

Description: Report presenting a detailed method for determining the jet-boundary corrections for reflection-plane models in rectangular wind tunnels. The principal effects of aerodynamic induction and boundary-induced curvature of the streamlines are considered. An example is included to illustrate the method.
Date: May 1943
Creator: Swanson, Robert S. & Toll, Thomas A.
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