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NACA Conference on Aircraft Loads, Structures, and Flutter

Description: "This document contains reproductions of technical papers on some of the most recent research results on aircraft loads, flutter, and structures from the NACA laboratories. These papers were presented by members of the staff of the NACA laboratories at the Conference held at the Langley Aeronautical Laboratory March 5, 6, and 7, 1957. The primary purpose of this Conference was to convey to contractors of the military services and others concerned with the design of aircraft these recent research results and to provide those attending an opportunity to discuss the results" (p. 6).
Date: March 5, 1957
Partner: UNT Libraries Government Documents Department

NACA Conference on Aerodynamics of High Speed Aircraft

Description: "This document contains reproductions of technical papers presented by staff members of the NACA Laboratories at the NACA Conference on Aerodynamics of High-Speed Aircraft held at the Langley Aeronautical Laboratory November 1, 2, and 3, 1955. The primary purpose of the conference was to convey to contractors of the military services and others concerned with the design of aircraft the results of recent research and to provide those attending with an opportunity to discuss these results. The papers in this document are in the same form in which they were orally presented at the conference to facilitate their prompt distribution" (p. vii).
Date: 1955-11-01/1955-11-03
Partner: UNT Libraries Government Documents Department

NACA: University Conference on Aerodynamics: A Compilation of the Papers Presented

Description: This document contains reproductions of the technical papers presented at the NACA - University Conference on Aerodynamics held at the Langley Aeronautical Laboratory on June 21, 22, and 23, 1948. The conference was held in recognition of the difficulties, imposed by security restrictions, in keeping abreast of the rapid advances in aerodynamics. The papers were prepared to review the status of a number of fields of interest, to summarize the more important wartime advances that are no longer classified, and to orient reference material for further study.
Date: 1948-06-21/1948-06-23
Partner: UNT Libraries Government Documents Department

Pressure Distribution Measurements on a Turbine Rotor Blade Passing Behind a Turbine Nozzle Lattice

Description: "As a turbine rotor turns, the blades traverse the wake zones of the nozzle vanes. A periodic fluctuation of the pressure distribution around the circumference of the rotor blade is therefore caused. It was desired to investigate quantitatively this effect. At the same time, the magnitude of the force acting upon one profile of the rotor-blade lattice at various positions of this lattice relative to the nozzle lattice was to be determined" (p. 1).
Date: September 1947
Creator: Hausenblas
Partner: UNT Libraries Government Documents Department

Development and Construction of an Interferometer for Optical Measurements of Density Fields

Description: "A method of interference is described in the present report which promises profitable application in aeronautical research. The physical foundation of the method and a simple method of adjustment are briefly discussed. The special technical construction of the instrument is described which guarantees its use also in the case of vibrations of the surrounding space and permits the investigation of unsteady phenomena" (p. 1).
Date: September 1947
Creator: Zobel
Partner: UNT Libraries Government Documents Department

Supersonic-Area-Rule Design and Rocket-Propelled Flight Investigation of a Zero-Lift Straight-Wing-Body-Nacelle Configuration Between Mach Numbers 0.8 and 1.53

Description: Memorandum presenting an application of the supersonic area rule concept to the deign of a straight-wing-body combination with large symmetrically mounted nacelles located at the 70-percent-semispan station. The pressure drag from the configuration with nacelles was found to be significantly less than that from a corresponding configuration without nacelles throughout the Mach number range.
Date: April 26, 1956
Creator: Hoffman, Sherwood
Partner: UNT Libraries Government Documents Department

Effects of Heat-Capacity Lag in Gas Dynamics

Description: Report presenting an investigation of the existence of energy dissipations in gas dynamics, which must be attributed to a lag in the vibrational heat capacity of the gas, and most specifically the flow about a very small impact tube. A new method of measuring the relaxation time of gases is introduced in which the total-head defects observed with a specially shaped impact tube are compared with theoretical considerations.
Date: January 1944
Creator: Kantrowitz, Arthur
Partner: UNT Libraries Government Documents Department

Supersonic-Tunnel Tests of Projectiles in Germany and Italy

Description: Report presenting tests performed in German and Italian supersonic tunnels to determine the aerodynamic characteristics of projectiles of various shapes. The results show that increasing the relative length of the nose causes the drag coefficient to decrease and the center of pressure to move forward.
Date: October 1945
Creator: Ferri, Antonio
Partner: UNT Libraries Government Documents Department

Investigation for the Development of a High-Speed Antiaircraft Tow Target

Description: Report presenting an investigation for the purpose of developing a target which can be towed satisfactorily at high speeds. Testing included drag measurements and visual observations of the stability characteristics of several full-scale and scale models of sleeve-type tow targets. The drag coefficients obtained for the currently used targets were found to be excessively high.
Date: July 1943
Creator: Migotsky, Eugene
Partner: UNT Libraries Government Documents Department

Force Test of a 1/5-Scale Model of the Type GB-5 Controllable Glide Bomb

Description: Report presenting information regarding the development of a type GB-5 controllable glide bomb equipped with a target-seeking device. The model was tested on the six-component balance in order to measure the stability and control characteristics of the bomb in its original condition and with various modifications. Results regarding the effect of end plates on dihedral parameter, effect of vertical-tail arrangement on directional stability, aileron tests, and glide-path control are provided.
Date: March 27, 1944
Creator: Pitkin, Marvin
Partner: UNT Libraries Government Documents Department

The Effect of the Inlet Mach Number and Inlet-Boundary-Layer Thickness on the Performance of a 23 Degree Conical-Diffuser-Tail-Pipe Combination

Description: An investigation was conducted to determine the effect of the inlet Mach number and entrance-boundary-layer thickness on the performance of a 23 degree 21-inch conical-diffuser - tail-pipe combination with a 2:1 area ratio. The air flows used in this investigation covered an inlet Mach number range from 0.17 to 0.89 and corresponding Reynolds numbers of 1,700,000 to 7,070,000. Results are reported for two inlet-boundary-layer thicknesses.
Date: March 21, 1950
Creator: Persh, Jerome
Partner: UNT Libraries Government Documents Department

Experimental Determination at Subsonic Speeds of the Oscillatory and Static Lateral Stability Derivatives of a Series of Delta Wings With Leading-Edge Sweep From 30 to 86.5 Degrees

Description: Memorandum presenting a determination of the static lateral stability of six delta wings at subsonic speeds. In addition, two of the wings with 82.5 degree and 75 degree sweep of the leading edge were oscillated in yaw about the 50-percent point of the root chord in order to determine the effects of frequency and amplitude on the combination lateral stability derivatives resulting from the motion. Results regarding the static characteristics and oscillatory characteristics are provided.
Date: April 12, 1957
Creator: Letko, William
Partner: UNT Libraries Government Documents Department

Statistical Approach to the Estimation of Loads and Pressures on Seaplane Hulls for Routine Operations

Description: Memorandum presenting a study of the impact loads experienced during full-scale and model tests in order to estimate the repeated loadings of seaplanes for long operating periods. The results indicate that the low landing speeds for antisubmarine-warafare seaplanes reduced the magnitude of the loads but that the more frequent landings and take-offs required for these operations greatly increased the total number of loads.
Date: March 27, 1957
Creator: Steiner, Roy
Partner: UNT Libraries Government Documents Department

The Theory of Propellers 3: The Slipstream Contraction With Numerical Values for Two-Blade and Four-Blade Propeller

Description: Report presenting the magnitude of slipstream contraction, which provides information about the conditions of the ultimate wake. Curves and tables are given for the contraction coefficient of two-blade and four-blade propellers for various values of the advance ratio; the contraction coefficient is defined as the contraction in the diameter of the wake helix in terms of the wake diameter at infinity.
Date: November 1944
Creator: Theodorsen, Theodore
Partner: UNT Libraries Government Documents Department

The Theory of Propellers 4: Thrust, Energy, and Efficiency Formulas for Single- and Dual-Rotating Propellers With Ideal Circulation Distribution

Description: Report presenting simple and exact expressions for the efficiency of single- and dual-rotating propellers with ideal circulation distribution as given by Goldstein functions for single-rotating propellers and by the new functions for dual-rotating propellers from part I of this series. Efficiency is found to depend primarily on a defined load factor and on an axial loss factor. Tables and graphs are included for practical use of the results.
Date: November 1944
Creator: Theodorsen, Theodore
Partner: UNT Libraries Government Documents Department

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
Partner: UNT Libraries Government Documents Department

Effect of Normal Pressure on the Critical Shear Stress of Curved Sheet

Description: "In order to determine the critical stresses caused by an outward acting pressure on the upper surface of a wing due to the difference in internal and external pressures, torsional tests were made on two curved-sheet specimens subjected to an outward acting normal pressure. Results show that an outward acting normal pressure appreciable raises the critical shear stress for an unstiffened curved sheet; the absolute increase in critical shear stress is slightly greater for a 30 in. rib spacing than for a 10 in. rib spacing" (p. 1).
Date: January 1943
Creator: Rafel, Norman
Partner: UNT Libraries Government Documents Department

An Investigation at Transonic Speeds of the Effects of Fences, Drooped Nose, and Vortex Generators on the Aerodynamic Characteristics of a Wing-Fuselage Combination Having a 6-Percent-Thick, 45 Degree Sweptback Wing

Description: Report presenting an investigation at transonic speeds to determine the effects of fences, drooped nose, combination fences and drooped nose, and vortex generators on a 45 degree sweptback wing-fuselage combination. The purpose of undertaking this investigation was due to the pitch-up tendency that results from leading-edge vortex-type flow on thin sweptback wings. The data for each component and their interaction with one another is also provided.
Date: March 31, 1953
Creator: Hieser, Gerald
Partner: UNT Libraries Government Documents Department

The Strength and Stiffness of Shear Webs With and Without Lightening Holes

Description: Report presenting the results of nearly 200 tests made on the strength of shear webs of 24S-T aluminum alloy, with and without lightening holes. The tests were made in a jig of the single-specimen type, in which the specimen is free to collapse completely without developing diagonal tension. Results regarding the strength of the shear webs, stiffness of shear webs, and permanent-set tests are provided.
Date: June 1942
Creator: Kuhn, Paul
Partner: UNT Libraries Government Documents Department

The Design of Cooling Ducts With Special Reference to the Boundary Layer at the Inlet

Description: "A study has been made of underslung cooling ducts with special references to the problems presented by the boundary layer on the fuselage skin. It was found that good flow can be obtained in such ducts by (1) making the inlet opening of such size that the mean inlet velocity is about 0.6 the free-stream velocity and (2) providing vanes behind as well as ahead of the radiator. Tables to facilitate design are included, together with an example " (p. 1).
Date: December 1940
Creator: Katzoff, S.
Partner: UNT Libraries Government Documents Department

The Strength and Stiffness of Shear Webs With Round Lightening Holes Having 45 Degree Flanges

Description: Report presenting tests made of 18 shear webs with round lightening holes having 45 degree flanges. the purpose of the tests was to extend the range of a previous investigation to larger ratios of hole diameter to web depth and of web depth to web thickness. Simple empirical formulas are given for the strength and the stiffness of shear webs.
Date: December 1942
Creator: Kuhn, Paul
Partner: UNT Libraries Government Documents Department

Spinning of Large Airplanes

Description: Report discusses the problem of large airplanes spinning and the fact that they should not be intentionally spun because they are not designed for the loads and speeds that may be encountered in spin and recovery. Stall and spin characteristics for large airplanes are described. Recommended piloting procedures in case of a large airplane spinning event are also provided.
Date: October 1944
Creator: Seidman, Oscar
Partner: UNT Libraries Government Documents Department
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