UNT Libraries Government Documents Department - 113 Matching Results

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Aerodynamic Characteristics and Flap Loads of the Brake-Flap Installation on the 0.40-Scale Model of the F4F-3 Left Wing Panel

Description: "The data are presented in coefficient form and include lift, drag, and pitching-moment coefficients of the airfoil-flap comoinations and the normal-force, chord-force, and hinge-moment coefficients of the upper (perforated split) flap and lower (slotted) flap" (p. 1).
Date: October 1942
Creator: Purser, Paul E. & Liddell, Robert B.
Item Type: Refine your search to only Report
open access

Aerodynamic Characteristics for Internal-Balance and Frise Type Ailerons on an NACA 6 Series Low-Drag Tip Section of the Wing for the XP-63 Airplane

Description: Report presenting testing in the two-dimensional turbulence tunnel of a model of the tip section of the wing of the XP-63 airplane. Several alterations of the skirts and balance on the internal-balance aileron were tested to obtain various aerodynamic characteristics of the aileron.
Date: October 1942
Creator: Underwood, William J.
Item Type: Refine your search to only Report
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Aerodynamic Characteristics of a 1/8-Scale Powered Model of a High-Speed Bomber With a Dual Pusher Propeller Aft of the Empennage

Description: Report presenting wind-tunnel tests made to determine the aerodynamic characteristics of a scale model of a high-speed bomber with a dual pusher propeller aft of the empennage. Some of the results discussed include longitudinal, lateral, and directional stability and control, the empennage design, and ground effects on the aerodynamic characteristics. The results indicate that this particular airplane has several advantages with regard to stability and control over the conventional-type single-… more
Date: October 12, 1945
Creator: Weiberg, James A. & Schnurbusch, Alfred W.
Item Type: Refine your search to only Report
open access

Aerodynamic Factors Affecting the Ability of a Pilot to Return an Airplane to Level From a Banked Attitude by Use of the Rudder Alone and Without Change of Heading

Description: Report presenting a study of the aerodynamic factors upon which the ability to perform the maneuver depends in an attempt to obtain a better understanding of the conditions involved and, if possible, to evolve criterions that may be used during design.
Date: October 1941
Creator: Harmon, S. M.
Item Type: Refine your search to only Report
open access

Analysis of Wind-Tunnel Stability and Control Tests in Terms of Flying Qualities in Full-Scale Airplanes

Description: From Summary: "The analysis of results of wind-tunnel stability and control tests of powered airplane models in terms of the flying qualities of full-scale airplanes is advocated. In order to indicate the topics upon which comments are considered desirable in the report of a wind-tunnel stability and control investigation and to demonstrate the nature of the suggested analysis, the present NACA flying-qualities requirements are discussed in relation to wind-tunnel tests. General procedures for … more
Date: October 1943
Creator: Kayten, Gerald G.
Item Type: Refine your search to only Report
open access

Application of Spring Tabs to Elevator Controls

Description: Report presenting equations for calculating the stick-force characteristics obtained with a spring-tab type of elevator control. The main problems encountered in the design of the satisfactory elevator spring tab are to provide stick forces in the desired range, to maintain the force per g sufficiently constant throughout the speed range, to avoid undesirable "feel" of the control in ground handling, and to prevent flutter.
Date: October 1944
Creator: Phillips, William H.
Item Type: Refine your search to only Report
open access

Column and Plate Compressive Strengths of Aircraft Structural Materials: Extruded R303-T Aluminum Alloy

Description: "Column and plate compressive strengths of extruded R303-T aluminum alloy were determined both within and beyond the elastic range form tests of thin-strip columns and 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 aircraft structure… more
Date: October 1945
Creator: Heimerl, George J. & Fay, Douglas P.
Item Type: Refine your search to only Report
open access

Comparison between calculated and measured loads on wing and horizontal tail in pull-up maneuvers

Description: Report presenting comparisons of measured and calculated loads on the wing and horizontal tail in pull-up maneuvers for six airplanes over a range of weights. Good agreement was obtained between calculated and measured loads under certain circumstances, but the agreement in some cases was only fair, which may be attributed to poor quantitative knowledge of the aerodynamic parameters or to violation of the assumptions on which the method is based.
Date: October 1945
Creator: Matheny, Cloyce E.
Item Type: Refine your search to only Report
open access

Comparison of fixed-stabilizer, adjustable- stabilizer and all-movable horizontal tails

Description: Report presenting an analysis to compare longitudinal stability and control characteristics obtained with a conventional fixed-stabilizer, an adjustable-stabilizer, and an all-movable horizontal tail. The tail-area requirements, control forces required in the critical landing condition, static margin, control-force gradients in a dive recovery, and elevator-free stability are investigated.
Date: October 1945
Creator: Harmon, Sidney M.
Item Type: Refine your search to only Report
open access

Comparison of the Energy Method With the Accelerometer Method of Computing Drag Coefficients From Flight Data

Description: "A comparison was made between the energy and the accelerometer methods of computing drag coefficients from flight tests of the P-51B and the P-39N airplanes. The energy method was found to be unreliable with the present types of instrumentation except under the practically unattainable conditions of very steady flight at constant indicated airspeed within a vertically stationary air mass" (p. 1).
Date: October 1945
Creator: Keller, Thomas L. & Keuper, Robert F.
Item Type: Refine your search to only Report
open access

Compressibility Effects on Heat Transfer and Pressure Drop in Smooth Cylindrical Tubes

Description: "An analysis is made to simplify pressure-drop calculations for nonadiabatic and adiabatic friction flow of air in smooth cylindrical tubes when the density changes due to heat transfer and pressure drop are appreciable. Solutions of the equation of motion are obtained by the use of Reynolds' analogy between heat transfer and skin friction. Charts of the solutions are presented for making pressure-drop calculations" (p. 1).
Date: October 1944
Creator: Nielsen, Jack N.
Item Type: Refine your search to only Report
open access

Correlation of exhaust-valve temperatures with engine operating conditions and valve design

Description: Report presenting a theory regarding engine-cooling variables from a previous report, which was used as a basis for the development of a semi-empirical equation to correlate exhaust-valve temperature with engine conditions. Results regarding the determination of constants, influences of operating variables on mean effective gas temperatures, thermal-resistance factor, and accuracy of correlating equation are provided.
Date: October 1945
Creator: Zipkin, M. A. & Sanders, J. C.
Item Type: Refine your search to only Report
open access

Correlation of the Characteristics of Single-Cylinder and Flight Engines in Tests of High-Performance Fuels in an Air-Cooled Engine 1 - Cooling Characteristics

Description: Variable charge-air flow, cooling-air pressure drop, and fuel-air ration investigations were conducted to determine the cooling characteristics of a full-scale air-cooled single cylinder on a CUE setup. The data are compared with similar data that were available for the same model multicylinder engine tested in flight in a four-engine airplane. The cylinder-head cooling correlations were the same for both the single-cylinder and the flight engine. The cooling correlations for the barrels differ… more
Date: October 4, 1945
Creator: Wilson, Robert W.; Richard, Paul H. & Brown, Kenneth D.
Item Type: Refine your search to only Report
open access

Correlation of the Characteristics of Single-Cylinder and Flight Engines in Tests of High-Performance Fuels in an Air-Cooled Engine 2 - Knock-Limited Charge-Air Flow and Cylinder Temperatures

Description: An investigation was conducted to correlate the knock limited performance of flight and single-cylinder engines under a variety of operating conditions.
Date: October 12, 1945
Creator: Brown, Kenneth D.; Richard, Paul H. & Wilson, Robert W.
Item Type: Refine your search to only Report
open access

Critical Stresses for Plates

Description: Report presenting the basic methods of theoretically calculating the critical stress for plates with elastically restrained edges. Design charts for various types of sections and columns and critical stress for flat plates and curved sheets are provided.
Date: October 1943
Creator: Lundquist, Eugene E. & Schuette, Evan H.
Item Type: Refine your search to only Report
open access

Cylinder Temperatures of Two Liquid-Cooled Aircraft Cylinders for Various Engine and Coolant Conditions

Description: Report presenting tests conducted with two liquid-cooled cylinders in order to isolate the effects of the various engine and coolant variables on cylinder temperatures and to obtain engine-cooling data required for a fundamental study of the heat-transfer processes in liquid-cooled engines. Cylinder temperatures were obtained for a large range of engine speeds, manifold pressures, carburetor-air temperatures, fuel-air ratios, spark advances, coolant-flow rates, average coolant temperatures, and… more
Date: October 1945
Creator: Manganiello, Eugene J. & Bernardo, Everett
Item Type: Refine your search to only Report
open access

Data for Design of Entrance Vanes from Two-Dimensional Tests of Airfoils in Cascade

Description: "As a part of a program of the NACA directed toward increasing the efficiency of compressors and turbines, data were obtained for application to the design of entrance vanes for axial-flow compressors or turbines. A series of blower-blade sections with relatively high critical speeds have been developed for turning air efficiently from 0 deg to 80 deg starting with an axial direction. Tests were made of five NACA 65-series blower blades (modified NACA 65(216)-010 airfoils) and of four experimen… more
Date: October 1945
Creator: Zimmey, Charles M. & Lappi, Viola M.
Item Type: Refine your search to only Report
open access

Determination of desirable lengths of Z- and channel-section columns for local-instability tests

Description: From Summary: "Local-instability tests of 24S-T aluminum-alloy formed Z- and channel-section columns were made in order to determine a length of test specimen that would avoid the increased strength associated with short lengths and also permit the occurrence of a convenient buckling pattern. The effect of column length on the critical compressive stress, on the average stress at maximum load, and on the number of half-waves of the buckling pattern is shown."
Date: October 1944
Creator: Heimerl, George J. & Roy, J. Albert
Item Type: Refine your search to only Report
open access

Development of Cowling for Long-Nose Air-Cooled Engine in the NACA Full-Scale Wind Tunnel

Description: "An investigation of cowlings for long-nose radial engines was made on the Curtiss XP-42 fighter in the NACA full-scale wind tunnel. The unsatisfactory aerodynamic characteristics of all the cowlings with scoop inlets tested led to the development of the annular high-velocity inlet cowlings. Tests showed that ratio of cooling-air velocity at cowling inlet to stream velocity should not be less than 0.5 for this type of cowling and that critical compressibility speed can be extended to more than … more
Date: October 1941
Creator: Silverstein, Abe & Guryansky, Eugene R.
Item Type: Refine your search to only Report
open access

Ditching tests with a 1/11-size model of the Army B-25 airplane in NACA tank number 2 and on an outdoor catapult

Description: Report presenting testing to determine the best way to land the B-25 airplane in calm and rough water and to determine its probable ditching performance. By landing with flaps down in a tail-down attitude at as slow a speed as possible, smooth straight landing runs will probably result in calm water. Results regarding the effect of attitude, effect of flap setting, effect of simulated damage, effect of propellers, and effect of seaway are provided.
Date: October 1944
Creator: Jarvis, George A. & Steiner, Margaret F.
Item Type: Refine your search to only Report
open access

Drag Analysis of Single-Engine Military Airplanes Tested in the NACA Full-Scale Wind Tunnel

Description: Report presenting tests in the full-scale wind tunnel on 11 single-engine military airplanes to investigate methods for increasing their high speed. Results regarding the power-plant installation, flow characteristics, wings, cockpit canopies, landing gear, and air leakage are provided.
Date: October 1940
Creator: Dearborn, C. H. & Silverstein, Abe
Item Type: Refine your search to only Report
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