Technical Report Archive & Image Library (TRAIL) - 43 Matching Results

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Jet Propulsion with Special Reference to Thrust Augmenters

Description: An investigation of the possibility of using thrust augmented jets as prime movers was carried out. The augmentation was to be effected by allowing the jet to mix with the surrounding air in the presence of bodies which deflect the air set in motion by the jet. Six augmentation schemes were tested experimentally with compressed air at room temperature at jet speeds up to 1240 feet per second.
Date: January 1933
Creator: Schubauer, G. B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Rolling, yawing, and hinge moments produced by rectangular ailerons

Description: Ailerons described in references 1, 2, and 3, are summarized in the form of empirical equations which relate the aileron dimensions and displacements to the rolling, yawing, and hinge moments for pitch angles of 0 and 12 degrees, corresponding to angles of attack of the wings of 4 and 16 degrees, respectively.
Date: January 1933
Creator: Heald, R. H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind Tunnel Research Concerning Lateral Control Devices, Particularly at High Angles of Attack 7: Handley Page Tip and Full-Span Slots With Ailerons and Spoilers

Description: Tests were made with ordinary ailerons and different sizes of spoilers on rectangular Clark Y wing models with Handley Page tip and full span slots. The tests showed the effect of the control devices on the general performance of the wings as well as on the lateral control and lateral stability characteristics.
Date: January 1933
Creator: Weick, Fred E. & Wenzinger, Carl J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Working charts for the stress analysis of elliptic rings

Description: This report presents charts which reduce the stress analysis of circular and elliptic rings of uniform cross section subjected to balanced systems of concentrated loads from a statically indeterminate problem to a statically determinate one. To demonstrate the use of the charts in the stress analysis of elliptic rings, an illustrative problem is included.
Date: January 1933
Creator: Burke, Walter F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of aileron displacement on wing characteristics

Description: The effect of aileron displacement on wing characteristics has been investigated for the Clark Y and the U.S.A. 27 wing sections equipped with rectangular ailerons. The airfoils, rectangular in plan, and having a 10 inch chord and 60 inch span, were mounted on a model fuselage.
Date: February 1933
Creator: Heald, R. H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Mercerization of Cotton for Strength With Special Reference to Aircraft Cloth

Description: The object of the present investigation was to determine the conditions for mercerizing cotton yarn to obtain the maximum strength for a given weight. Apparatus for controlling the variables was built and yarns were mercerized with it under systematically varied conditions of tension, time, temperature, and concentration of caustic soda. The strongest conclusion to be drawn from this work is that the strongest mercerized yarn of a given count from a given quality of cotton is obtained under cer… more
Date: February 1933
Creator: Wilkie, J. B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind Tunnel Research Comparing Lateral Control Devices, Particularly at High Angles of Attack 8: Straight and Skewed Ailerons on Wings With Rounded Tips

Description: Tests showed the effect of the ailerons and the tip shapes on the general performance of the wing, as well as on the lateral control and stability characteristics. The hinge moments were not measured but the approximate values are given in the first report of the series.
Date: February 1933
Creator: Weick, Fred E. & Shortal, Joseph A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Research Comparing Lateral Control Devices, Particularly at High Angles of Attack 9: Tapered Wings With Ordinary Ailerons

Description: Tests were made with ordinary flap-type ailerons on two wings with different amounts of taper, one medium and the other extreme. On each wing both medium sized tapered ailerons and short wide tapered ailerons were tested.
Date: February 1933
Creator: Weick, Fred E. & Wenzinger, Carl J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Aerodynamic Effect of a Retractable Landing Gear

Description: "Tests were conducted in the N.A.C.A. full scale wind tunnel at the request of the Army Air Corps to determine the effect of retractable landing gear openings in the bottom surface of a wing upon the characteristics of a Lockheed Altair airplane. The tests were extended to include the determination of the lift and drag characteristics throughout the angle-of-attack range with the landing gear both retracted and extended. Covering the wheel openings in the wing with sheet metal when the wheels w… more
Date: March 1933
Creator: DeFrance, Smith J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Comparison of Three Methods for Calculating the Compressive Strength of Flat and Slightly Curved Sheet and Stiffener Combinations

Description: "This report gives a comparison of the accuracy of the three methods for calculating the compressive strength of flat sheet and stiffener combinations such as occur in stressed-skin or monocoque structures for aircraft. Of the three methods based upon various assumptions with regard to the interaction of sheet and stiffener, the method based upon mutual action of the stiffener and an effective width as a column gave the best agreement with the results of the tests. An investigation of the effec… more
Date: March 1933
Creator: Lundquist, Eugene E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experiments With a Counter-Propeller

Description: This note describes tests made at Stanford University on a four-blade fixed counter-propeller in combination with a two-blade rotating propeller. It is shown that the efficiency of the normal form, well-designed air propeller can be increased about two percent over the full working range by the addition of fixed counter-propeller blades.
Date: March 1933
Creator: Lesley, E. P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The importance of auto-ignition lag in knocking

Description: Report presenting an examination of the phenomenon of knocking, which is often accompanied by an apparently simultaneous reaction of the last part of the charge to burn. Several hypotheses regarding the burning of fuel and an exploration of current literature regarding the phenomena are provided.
Date: March 1933
Creator: Taylor, E. S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The N.A.C.A. Combustion Chamber Gas-Sampling Valve and Some Preliminary Test Results

Description: "A gas sampling valve of the inertia-operated type was designed for procuring samples of the gases in the combustion chamber of internal combustion engines at identical points in successive cycles so that the analysis of the gas samples thus procured may aid in the study of the process of combustion. The operation of the valve is described. The valve was used to investigate the CO2 content of gases taken from the quiescent combustion chamber of a high speed compression-ignition engine when oper… more
Date: March 1933
Creator: Spanogle, J. A. & Buckley, E. C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind tunnel research comparing lateral control devices, particularly at high angles of attack 10: various control devices on a wing with a fixed auxiliary airfoil

Description: Results are given of a series of systemic tests comparing lateral control devices with particular reference to their effectiveness at high angles of attack. These tests were made with two sizes of ordinary ailerons and different sizes of spoilers on a Clark Y wing model having a narrow auxiliary airfoil fixed ahead and above the leading edge, the chords of the main and auxiliary airfoils being parallel. In addition, the auxiliary airfoil itself was given angular deflection. The purpose was to p… more
Date: March 1933
Creator: Weick, Fred E. & Noyes, Richard W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Aerodynamic Characteristics of Airfoils as Affected by Surface Roughness

Description: "The effect on airfoil characteristics of surface roughness of varying degrees and types at different locations on an airfoil was investigated at high values of the Reynolds number in a variable density wind tunnel. Tests were made on a number of National Advisory Committee for Aeronautics (NACA) 0012 airfoil models on which the nature of the surface was varied from a rough to a very smooth finish. The effect on the airfoil characteristics of varying the location of a rough area in the region o… more
Date: April 1933
Creator: Hooker, Ray W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Effect of Rivet Heads on the Characteristics of a 6 by 36 Foot Clark Y Metal Airfoil

Description: "An investigation was conducted in the N.A.C.A. full-scale wind tunnel to determine the effects of exposed rivet heads on the aerodynamic characteristics of a metal-covered 6 by 36 foot Clark Y airfoil. Lead punching simulating 1/8 inch rivet heads were attached in full-span rows at a pitch of 1 inch at various chord positions. Tests were made at velocities varying from 40 to 120 miles per hour to investigate the scale effect" (p. 1).
Date: May 1933
Creator: Dearborn, Clinton H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Full-Scale Wind-Tunnel Research on Tail Buffeting and Wing-Fuselage Interference of a Low-Wing Monoplane

Description: Some preliminary results of full scale wind tunnel testing to determine the best means of reducing the tail buffeting and wing-fuselage interference of a low-wing monoplane are given. Data indicating the effects of an engine cowling, fillets, auxiliary airfoils of short span, reflexes trailing edge, propeller slipstream, and various combinations of these features are included. The best all-round results were obtained by the use of fillets together with the National Advisory Committee for Aerona… more
Date: May 1933
Creator: Hood, Manley J. & White, James A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind tunnel research comparing lateral control devices, particularly at high angles of attack 11: various floating tip ailerons on both rectangular and tapered wings

Description: Discussed here are a series of systematic tests being conducted to compare different lateral control devices with particular reference to their effectiveness at high angles of attack. The present tests were made with six different forms of floating tip ailerons of symmetrical section. The tests showed the effect of the various ailerons on the general performance characteristics of the wing, and on the lateral controllability and stability characteristics. In addition, the hinge moments were mea… more
Date: May 1933
Creator: Weick, Fred E. & Harris, Thomas A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-tunnel tests on model wing with Fowler flap and specially developed leading-edge slot

Description: From Summary: "An investigation was made in the NACA 7 by 10 foot wind tunnel to find the increase in maximum lift coefficient which could be obtained by providing a model wing with both a Fowler trailing-edge extension flap and a Handley Page type leading-edge slot. A conventional Handley page slot proportioned to operate on the plain wing without a flap gave but a slight increase with the flap; so a special form of slot was developed to work more effectively with the flap. With the best combi… more
Date: May 1933
Creator: Weick, Fred E. & Platt, Robert C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic tests of a low aspect ratio tapered wing with various flaps, for use on tailless airplanes

Description: From Introduction: "The tests described in this report are the first in an investigation by N.A.C.A. of the aerodynamic characteristics of possible tailless arrangements. The investigations will be extended to include whatever range is through most desirable and may include, among other things, variations in aspect ratio, taper, sweepback, washout, air-foil section, dihedral, and also control flaps or other control devices of different forms and proportions."
Date: June 1933
Creator: Weick, Fred E. & Sanders, Robert
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Formulas for the Stress Analysis of Circular Rings in a Monocoque Fuselage

Description: "The formulas given in this report provide a simplified method for the stress-analysis of fuselage bulkheads that are approximately circular rings of uniform cross section. Complicated load systems acting on a ring can usually be resolved into simplified load systems; and formulas for moment, axial force, and shear for such simplified load systems are given in this report. Illustrative examples showing the use of this method in practical stress-analysis work are also included" (p. 1).
Date: June 1933
Creator: Miller, Roy A. & Wood, Karl D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A complete tank test of a model of a flying-boat hull - N.A.C.A. Model No. 11

Description: "This note discusses the limitations of the conventional tank test of a seaplane model. The advantages of a complete test, giving the characteristics of the model at all speeds, loads, and trim angles in the useful range are pointed out. The data on N.A.C.A. Model No.11, obtained from a complete test, are presented and discussed. The results are analyzed to determine the best trim angle for each speed and load. The data for the best angles are reduced to non-dimensional form for ease of compari… more
Date: July 1933
Creator: Shoemaker, James M. & Parkinson, John B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Complete Tank Test of a Model of a Flying-Boat Hull - N.A.C.A. Model No.11

Description: "This note discusses the limitations of the conventional tank test of a seaplane model. The advantages of a complete test, giving the characteristics of the model at all speeds, loads, and trim angles in the useful range are pointed out. The data on N.A.C.A. Model No.11, obtained from a complete test, are presented and discussed. The results are analyzed to determine the best trim angle for each speed and load. The data for the best angles are reduced to non-dimensional form for ease of compari… more
Date: July 1933
Creator: Shoemaker, James M. & Parkinson, John B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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