National Advisory Committee for Aeronautics (NACA) - 192 Matching Results

Search Results

Tests of a gust-alleviating wing in the gust tunnel

Description: Tests were made in the NACA gust tunnel to determine the effectiveness of a torsionally flexible wing with the torsion axis ahead of the locus of the section aerodynamic centers in reducing airplane accelerations due to atmospheric gusts. For three gust shapes, a series of flights was made with the airplane model equipped with either a torsionally flexible or a rigid wing. The results indicated that the torsionally flexible wing reduced the maximum acceleration increment 5 percent for the sharp-edge gust and about 17 percent for gust shapes with gradient distances of 6.8 and 15 chord lengths. The analysis indicated that the effectiveness of this method of gust alleviation was independent of the gust velocity and that, for the same total load increment, the torsionally flexible wing would have 10 percent less bending-moment increment at the root section of the wing than a rigid wing in all but the sharpest gusts. The results also indicated that the torsionally flexible wing slightly increased the longitudinal stability of the airplane model in a gust.
Date: April 1, 1941
Creator: Shufflebarger, C C
Partner: UNT Libraries Government Documents Department

Some effects of rainfall on flight of airplanes and on instrument indications

Description: Several possible effects of heavy rain on the aerodynamic performance of an airplane and of heavy rain and associated atmospheric phenomena on the indications of flight instruments are briefly considered. It is concluded that the effects of heavy rain on the performance of an airplane are not so great as to force the airplane down from moderate altitudes. Serious malfunctioning of the air-speed indicator may occur, however, as a result of flooding of the pitot-static head and subsequent accumulation of water in the air-speed pressure line. In strong convective situations, like thunderstorms, the rate-of-climb indicator may also be seriously in error owing to rapid variations of atmospheric pressure when entering and emerging from the convection currents.
Date: April 1, 1941
Creator: Rhode, Richard V
Partner: UNT Libraries Government Documents Department

Effect of aging on mechanical properties of aluminum-alloy rivets

Description: Curves and tabular data present the results of strength tests made during and after 2 1/2 years of aging on rivets and rivet wire of 3/16-inch nominal diameter. The specimens were of aluminum alloy: 24S, 17S, and A17S of the duralumin type and 53S of the magnesium-silicide type.
Date: April 1941
Creator: Roop, Frederick C
Partner: UNT Libraries Government Documents Department

Tests of round and flat spoilers on a tapered wing in the NACA 19-foot pressure wind tunnel

Description: Several arrangements of round and flat spanwise spoilers attached to the upper surface of a tapered wing were tested in the NACA 19-foot pressure wind tunnel to determine the most effective type, location, and size of spoiler necessary to reduce greatly the lift on the wings of large flying boats when moored. The effect of the various spoilers on the lift, the drag, and the pitching-moment characteristics of the tapered wing was measured over a range of angles of attack from zero to maximum lift. The most effective type of spoiler was found to be the flat type with no space between it and the wing surface. The chordwise location of such a spoiler was not critical within the range investigated, from 5 to 20 percent of the wing chord from the leading edge.
Date: March 1, 1941
Creator: Wenzinger, Carl J. & Bowen, John D.
Partner: UNT Libraries Government Documents Department

Tests on stiffened circular cylinders

Description: Compressive tests were made of two series of stiffened circular cylindrical shells under axial load. All the shells were 16 inches in diameter by 24 inches in length and were made of aluminum-alloy sheet curved to the proper radius and welded with one longitudinal weld. The ratios of diameter to thickness of shell wall in the two series of specimens were 258 and 572. Strains were measured with Huggenberger tensometers at a number of gage lines on the stiffeners and shell. The results of these tests indicate that a spacing of circumferential stiffeners equal to 0.67 times the radius is too great to strengthen the shell wall appreciably. The results are not inclusive enough to show the optimum in stiffeners. Plain cylinders without stiffeners developed ultimate strengths approximately half as great as the buckling strengths computed by the equation resulting from the classical theory and slightly greater than those computed by Donnell's large deflection theory.
Date: March 1, 1941
Creator: Holt, Marshall
Partner: UNT Libraries Government Documents Department

Hydrodynamic tests of a 1/10-size model of the hull of the Latecoere 521 flying boat : NACA model 83

Description: A 1/10-size model of the hull of the French flying boat Latecoere 521 was tested in the NACA tank. This model is one of a series of models of the hulls of actual flying boats of both foreign and domestic type that are being tested in the NACA tank to provide information regarding the water characteristics of a variety of forms of hull and to illustrate the development of present-day types of flying boat. The lines and the offsets of the hull were obtained from the manufacturer through the Paris office of the NACA. The form of the stub-wing stabilizers was not furnished and, therefore, the model was tested without them. The model was tested free to trim at the design initial load (initial load coefficient of 0.428) and by the general method at load coefficients from 0.025 to 0.6. The spray characteristics of the model are good. The form of the bow would be particularly desirable for rough water use. The interference of the afterbody and the tail extension is excessive, causing very high resistance at high speeds. A violent vertical instability is present at trims of 4 degrees and 6 degrees with light loads and high speeds.
Date: December 1, 1941
Creator: Olson, Roland E & Lina, Lindsay J
Partner: UNT Libraries Government Documents Department

Velocity gained and altitude lost in recoveries from inclined flight paths

Description: A series of charts is given showing the variation of the velocity gained and the altitude lost in dive pullouts with the initial indicated air speed and the dive angle. The effects of the maximum load factor, the drag parameter K, the initial altitude, and the type of recovery on the velocity gained and the altitude lost are also considered. The results were obtained from a step-by-step solution of the equations of motion in which mean values of the air density and the airplane drag coefficient were used. The load-factor variation with time is arbitrarily specified in various ways to simulate pull-out procedures, some of which might be encountered in flight.
Date: October 1, 1941
Creator: Pearson, H A & Garvin, J B
Partner: UNT Libraries Government Documents Department

Ultimate stresses developed by 24S-T sheet in incomplete diagonal tension

Description: Tests were made on 18 shear panels of 24S-T aluminum alloy to verify the dependence of the ultimate stress on the degree of development of the diagonal-tension field. Tests were made on two thicknesses of sheet with the sheet either clamped between the flange angle or riveted to the outside of the angles.
Date: December 1, 1941
Creator: Kuhn, Paul
Partner: UNT Libraries Government Documents Department

Relief of residual stress in streamline tie rods by heat treatment

Description: About two-thirds of the residual stress in cold-worked SAE 1050 steel tie rods was relieved by heating 30 minutes at 600 degrees Fahrenheit. Cold-worked austenitic stainless-steel tie rods could be heated at temperatures up to 1000 degrees Fahrenheit without lowering the important physical properties. The corrosion resistance, in laboratory corrosion test, of straight 18:8 and titanium-treated 18:8 materials appeared to be impaired after heating at temperatures above 800 degrees or 900 degrees fahrenheit. Columbium-treated and molybdenum-treated 18:8 steel exhibited improved stability over a wide range of temperatures. Tie rods of either material could be heated 30 minutes with safety at any temperature up to 1000 degrees Fahrenheit. At this temperature most of the residual stress would be relieved.
Date: November 1, 1941
Creator: Pollard, R E & Reinhart, Fred M
Partner: UNT Libraries Government Documents Department

Two-stage supercharging

Description: The arrangement of the parts and the installation and control problems of the two-stage mechanically driven superchargers for aircraft engines are discussed. Unless an entirely new form of supercharging is developed, there will be a definite need for a two-stage centrifugal supercharger. It is shown that the two-stage mechanically driven supercharger itself is a comparatively simple device; the complications arise from the addition of inter-coolers and controls.
Date: February 1, 1941
Creator: Buck, Richard S
Partner: UNT Libraries Government Documents Department

Effect of alternately high and low repeated stresses upon the fatigue strength of 25S-T aluminum alloy

Description: Fatigue tests were made on one lot of 3/4 inch diameter rolled-and-drawn 25S-T aluminum-alloy rod normal in composition and tensile properties. The specimens were tested at 3500 cycles per second in a rotating-beam fatigue test machine. Tests were made for three ratios (20:1, 50:1, and 200:1) of the number of cycles applied at low stress to the number applied at high stress. In general, failure occurred when the number of cycles at either the low or the high stress approached the ordinary fatigue curve for the material, regardless of the sequence in which the stresses were applied.
Date: January 1, 1941
Creator: Stickley, G W
Partner: UNT Libraries Government Documents Department