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Study by the Prandtl-Glauert method of compressibility effects and critical Mach number for ellipsoids of various aspect ratios and thickness ratios
From Summary: "By the use of a form of the Prandtl-Glauert method that is valid for three-dimensional flow problems, the value of the maximum incremental velocity for compressible flow about thin ellipsoids at zero angle of attack is calculated as a function of the Mach number for various aspect ratios and thickness ratios. The critical Mach numbers (within the accuracy of the Prandtl-Glauert method) of the various ellipsoids are also determined. The results indicate an increase in critical Mach number with decrease in aspect ratio which is large enough to explain experimental results on low-aspect-ratio wings at zero lift."
Date:
January 1949
Creator:
Hess, Robert V. & Gardner, Clifford S.
System:
The UNT Digital Library
Performance of Hoods for Aircraft Exhaust-Gas Turbines
Report presenting the performance of a turbosupercharger turbine with three types of exhaust hood. The results for conical hoods, flat-nozzle hoods, and short-turning-radius hoods are provided.
Date:
November 1946
Creator:
Turner, L. Richard; Lowdermilk, Warren H. & Lord, Albert M.
System:
The UNT Digital Library
Compressive Strength of 24S-T Aluminum-Alloy Flat Panels With Longitudinal Formed Hat-Section Stiffeners
"Results are presented for a part of a test program on 24S-T aluminum alloy flat compression panels with longitudinal formed hat-section stiffeners. This part of the program is concerned with panels in which the thickness of the stiffener materials is 0.625 times the skin thickness. The results, presented in tabular and graphical form, show the effect of the relative dimensions of the panel on the buckling stress and the average stress at maximum load" (p. 1).
Date:
December 1946
Creator:
Schuette, Evan H.; Barab, Saul & McCracken, Howard L.
System:
The UNT Digital Library
Investigation of Meteorological Conditions Associated with Aircraft Icing in Layer-Type Clouds for 1947-48 Winter
Rotating-cylinder measurements of the icing conditions encountered in flight during the winter of 1947-48 are presented. Liquid water content, drop size, and temperature data are shown to be consistent with previously measured conditions and with proposed maximum icing conditions in supercooled layer-type clouds. Cumulative frequency graphs of meteorological parameters indicate the frequency with which various icing conditions have been encountered in the Great Lakes area and surrounding states.
Date:
January 1949
Creator:
Kline, Dwight B.
System:
The UNT Digital Library
Gust-tunnel investigation of a wing model with semichord line swept back 30 degrees
Report presenting tests in the gust tunnel of the 30 degree sweptback wing model to provide information on some of the problems encountered in the prediction of gust loads for airplanes incorporating swept wings. The results indicate that within the scope of the data and the values of gradient distance investigated, the maximum acceleration increment depends on the slope of the lift curve of an equivalent straight wing multiplied by the cosine of the angle of sweep and on the effect of gradual penetration of the sweptback wing into the gust.
Date:
January 1949
Creator:
Reisert, Thomas D.
System:
The UNT Digital Library
The Synthesis and Purification of Aromatic Hydrocarbons 1: Butylbenzene
"A 13-gallon quantity of butylbenzene was synthesized and purified by large-scale preparation of 4-phenyl-1-butene from benzyl-magnesium chloride and allyl chloride with subsequent hydrogenation of the olefin. The physical constants for pure samples of 4-phenyl-1-butene and butylbenzene were determined and the position of the double bond in the olefin was established" (p. 1).
Date:
January 1946
Creator:
Karabinos, Joseph V. & Lamberti, Joseph M.
System:
The UNT Digital Library
A Relaxation Procedure for the Stress Analysis of a Continuous Beam-Column Elastically Restrained Against Deflection and Rotation at the Supports
Note presenting a method of stress analysis for a continuous beam-column supported by deflectional and rotational springs. The principal feature of the method is the use of a relaxation procedure to determine the deflections and rotations of the supports. The shears and moments at the supports and between the supports can then be calculated with the aid of sample equations and graphs.
Date:
October 1946
Creator:
Hu, Pai C. & Libove, Charles
System:
The UNT Digital Library
Application of Radial-Equilibrium Condition to Axial-Flow Compressor and Turbine Design
Note presenting some of the basic general equations governing the three-dimensional compressible flow of gas through a compressor or a turbine in terms of velocity components, total enthalpy, and entropy. The equations are applied to investigate the maximum compatible number of the radial variations of the gas properties between successive blade rows that a designer is free to specify.
Date:
January 1949
Creator:
Wu, Chung-Hua & Wolfenstein, Lincoln
System:
The UNT Digital Library
Effect of hull length-beam ratio on the hydrodynamic characteristics of flying boats in waves
Report presenting an investigation of the take-off and landing behavior in waves of models of a hypothetical flying boat with hull length-beam ratios of 6 and 15. The flying boat had a design gross weight of 75,000 pounds, a wing loading of 41.1 pounds per square foot, and a power loading of 11.5 pounds per brake horsepower for take-off. Results regarding the landing behavior, spray characteristics, and taxiing and take-off behavior are provided.
Date:
January 1949
Creator:
Carter, Arthur W.
System:
The UNT Digital Library
An analysis of the airspeeds and normal accelerations of Boeing B-247 and B-247D airplanes in commercial transport operation
From Introduction: "The results of analyses of V-G data given in references 1 to 5 have shown that the flight loads of airplanes operated in commercial transport service are influenced by operating speeds and by forecasting and dispatching practices as reflected in differences between operations during the prewar and wartime periods. The available data are summarized and the flight results are compared with the results of analyses made in references 1 to 5."
Date:
December 1948
Creator:
Walker, Walter G. & Hadlock, Ivan K.
System:
The UNT Digital Library
The effect of engine variables on the prediction-limited performance of three fuels
Report presenting preignition-limited performance data for S reference fuel, diisobutylene, and benzene with an engine-heated hot spot on a supercharged CFR engine at 11 sets of engine operating conditions. Results indicated that increases in compression ratio, spark advance, coolant temperature, or inlet-air temperature decreased the preignition-limited indicated mean effective pressure of all three fuels.
Date:
September 1946
Creator:
Male, Donald W.
System:
The UNT Digital Library
Investigation of the Aileron and tab of a spring-tab lateral-control system in the Langley 19-foot pressure tunnel
Report presenting tests of a partial-span model of a large bomber-type airplane, which were conducted to provide data on the aerodynamic characteristics of the aileron-tab arrangement and of the wing. Testing occurred to determine the rolling-moment, yawing-moment, and hinge-moment characteristics of the aileron and tab and the effect of midchord wing slots on the characteristics of the wing and aileron and tab. Results regarding the aerodynamic and stalling characteristics of the wing and aerodynamic characteristics of the aileron and tab are provided.
Date:
September 1947
Creator:
Deters, Owen J. & Russell, Robert T.
System:
The UNT Digital Library
Flight Investigation in Climb and at High Speed of a Two-Blade and a Three-Blade Propeller
Note presenting an investigation of a two-blade and a three-blade propeller on a slender-nose fighter airplane in climb and at high speed.
Date:
January 1949
Creator:
Hammack, Jerome B.
System:
The UNT Digital Library
Flight investigation of the cooling characteristics of a two-row radial engine installation 3: engine temperature distribution
From Summary: "The temperature distribution of a two-row radial engine in a twin-engine airplane has been investigated in a series of flight tests. The test engine was operated over a wide range of conditions at density altitudes of 5000 and 20,000 feet; quantitative results are presented showing the effects of flight and engine variables upon average engine temperature and over-all temperature spread. Discussions of the effect of the variables on the shape of the temperature patterns and on the temperature distribution of individual cylinders are also included."
Date:
October 1946
Creator:
Rennak, Robert M.; Messing, Wesley E. & Morgan, James E.
System:
The UNT Digital Library
Pressure Distributions for Representative Airfoils and Related Profiles
Note presenting selected pressure-distribution diagrams for a number of conventional and special airfoils. The conventional airfoils include the NACA 22, 44, and 230 series airfoils and Clark Y family and the special airfoils consist of circular-arc sections of several thicknesses and a number of synthetic airfoils. The pressure distributions are in most cases given for several lift coefficients including that at the ideal angle of attack.
Date:
February 1946
Creator:
Theodorsen, Theodore & Naiman, Irven
System:
The UNT Digital Library
An Electron Microscope Study of Used Nitrated-Steel Piston Rings
Note presenting a study of the altered surface layers found on nitrided-steel piston rings run in nitrided-steel cylinder barrels in order to determine the physical and chemical characteristics of the altered layers and the mechanism by which the coating layers were formed. An electron and a light microscope were used to study different aspects of the materials.
Date:
September 1946
Creator:
Clark, Thomas P. & Vierthaler, Walter A.
System:
The UNT Digital Library
Investigation of the Stability of the Laminar Boundary Layer
Note presenting an investigation of the stability of two-dimensional laminar flows of a gas by the method of small perturbations. The chief emphasis is placed on the case of the laminar boundary layer.
Date:
September 1946
Creator:
Lees, Lester & Lin, Chia Chiao
System:
The UNT Digital Library
Friction Coefficients in the Inlet Length of Smooth Round Tubes
Note presenting an experimental study of friction coefficients near the inlet of smooth, round tubes with bellmouth entrances. Four different combinations of approach section and bellmouth entry were used. Results regarding the apparent local friction coefficient, integrated friction coefficient, effect of induced turbulence, laminar inlet zone, developed friction coefficient, and application to discharge coefficients for rounded-entrance flow nozzles are provided.
Date:
November 1948
Creator:
Shapiro, Ascher H. & Smith, R. Douglas
System:
The UNT Digital Library
Recommendations for numerical solution of reinforced-panel and fuselage-ring problems
Report presenting procedures for solving the equations of equilibrium of reinforced panels and isolated fuselage rings as represented by the external loads and operations table established according to Southwell's method. By using these equations, the stress distribution can be easily determined.
Date:
December 1948
Creator:
Hoff, N. J. & Libby, Paul A.
System:
The UNT Digital Library
Tests in the gust tunnel of a model of the XBM-1 airplane
Report presenting testing of a dynamically scaled model of a Navy XBM-1 biplane in the gust tunnel to provide data for use in determining the structure of atmospheric gusts from measurements of the motions of the full-scale airplane in rough air. Records for two flights for several gradients were evaluated to give histories of events during passage through the gust.
Date:
October 1939
Creator:
Donely, Philip & Shufflebarger, C. C.
System:
The UNT Digital Library
Notes and Tables for Use in the Analysis of Supersonic Flow
Paper presenting a compilation of formulas, tables, and curves that have been found to be useful in the analysis of supersonic wind-tunnel data.
Date:
December 1947
Creator:
The Staff of the Ames 1- by 3-foot Supersonic Wind-Tunnel Section
System:
The UNT Digital Library
Comparison of the structural efficiency of panels having straight-web and curved-web Y-section stiffeners
Report presenting comparisons of the structural efficiency of panels with straight-web and curved-web Y-section stiffeners. In the high-stress region in which failure is at least in part associated with local buckling, panels with curved-web Y-section stiffeners have higher structural efficiencies than panels with straight-web Y-section stiffeners, which is evidenced by higher average stresses at failure, smaller stiffener heights, or wider average spacing of rivet lines.
Date:
January 1949
Creator:
Dow, Norris F. & Hickman, William A.
System:
The UNT Digital Library
A method for the determination of air infiltration rates in airplane cabins
From Summary: "A method for the experimental determination of the rate of infiltration of air into aircraft cabins during flight has been developed and tested. This method consists of releasing a quantity of gas in the cabin and calculating the infiltration rate from the measured rate of change of the gas concentration. The results of the flight tests indicate that after the infiltration rate is established at one altitude and airspeed, the infiltration rates at other altitudes and airspeeds can be calculated."
Date:
April 1946
Creator:
Stalder, Jackson R. & Zeiller, E. Lewis
System:
The UNT Digital Library
Foaming Volume and Foam Stability
"A method of measuring foaming volume is described and investigated to establish the critical factors in its operation. Data on foaming volumes and foam stabilities are given for a series of hydrocarbons and for a range of concentrations of aqueous ethylene-glycol solutions. It is shown that the amount of foam formed depends on the machinery of its production as well as on properties of the liquid, whereas the stability of the foam produced, within specified mechanical limitations, is primarily a function of the liquid" (p. 1).
Date:
February 1947
Creator:
Ross, Sydney
System:
The UNT Digital Library