Collection
Technical Report Archive and Image Library
431
National Advisory Committee for Aeronautics Collection
366
Texas Attorney General Opinions
258
Office of Scientific & Technical Information Technical Reports
93
TRAIL Microcard Collection
44
World War Two Collection
24
Government Documents A to Z Digitization Project
23
World War Two Newsmaps
18
Texas State Publications
15
USDA Farmers' Bulletins
4
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841 Matching Results
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Wind-tunnel investigation of the NACA 654-421 airfoil section with a double slotted flap and boundary layer control by suction
Report presenting an investigation in the two-dimensional low-turbulence tunnel to find the effects of boundary-layer control on the aerodynamic characteristics of the NACA 65(sub 4)-421 airfoil section with a boundary-layer-control suction slot at 0.45 airfoil chord and a 0.32-airfoil-chord double slotted flap. The airfoil is designed primarily to obtain a high maximum lift coefficient. Results regarding lift and drag characteristics are provided.
Date:
July 1947
Creator:
Quinn, John H., Jr.
Object Type:
Report
System:
The UNT Digital Library
High-speed tests of an airfoil section cambered to have critical Mach numbers higher than those attainable with a uniform-load mean line
Report presenting high-speed wind-tunnel tests to determine the aerodynamic characteristics of an NACA 6-series airfoil section cambered to have critical Mach numbers higher than those for an airfoil with the same design lift coefficient with a uniform-load type of mean camber line. Comparisons are made between the characteristics of the modified airfoil and those of the NACA 66-210 airfoil with a uniform-load type of mean camber line.
Date:
July 1947
Creator:
Graham, Donald J.
Object Type:
Report
System:
The UNT Digital Library
The Effects of Aerodynamic Heating and Heat Transfer on the Surface Temperature of a Body of Revolution in Steady Supersonic Flight
Note presenting an approximate method for determining the convective cooling requirement in the laminar boundary layer region of a body of revolution in high-speed flight that was developed and applied to a sample body. The convective cooling requirements were found to be small for the range of Mach numbers considered, but increased rapidly with increasing Mach number.
Date:
July 1947
Creator:
Scherrer, Richard
Object Type:
Report
System:
The UNT Digital Library
A Method for Calculating the Heat Required for the Prevention of Fog Formations on the Inside Surfaces of Single-Panel Bullet-Resisting Windshields During Diving Flight
Note presenting an investigation to provide a means for calculating the heat required for the prevention of fog formations on the inside surfaces of single-panel bullet-resisting windshields during diving flight. An analysis was made to provide relationships for the heat required considering the transient heating of the windshield during diving flight.
Date:
July 1947
Creator:
Selna, James & Zerbe, John E.
Object Type:
Report
System:
The UNT Digital Library
Effect of Variables in Welding Technique on the Strength of Direct-Current Metal-Arc-Welded Joints in Aircraft Steel 1 - Static Tension and Bending Fatigue Tests of Joints in SAE 4130 Steel Sheet
Report presenting testing of arc-welded butt joints in a 1/8-inch SAE 4130 steel sheet of aircraft quality under various conditions of welding and heat treatment in order to evaluate the effects of specific welding-technique factors on the strength of the joints. Results regarding static tension tests and fatigue tests are provided.
Date:
July 1947
Creator:
Voldrich, C. B. & Armstrong, E. T.
Object Type:
Report
System:
The UNT Digital Library
Wind-Tunnel Investigation of the Effect of Power and Flaps on the Static Longitudinal Stability and Control Characteristics of a Single-Engine High-Wing Airplane Model.
Note presenting an investigation conducted to determine the effect of power and full-span slotted flaps on the longitudinal stability and control characteristics of a single-engine high-wing airplane. The model was tested at three power conditions: propeller off, propeller windmilling, and power on, and with the flap neutral, single slotted flap, and double slotted flap. The results indicated that deflection of the double slotted flap produced almost twice as much lift increment as did the deflection of the single slotted flap.
Date:
July 1947
Creator:
Hagerman, John R.
Object Type:
Report
System:
The UNT Digital Library
The One-Dimensional Theory of Steady Compressible Fluid Flow in Ducts With Friction and Heat Addition
"Steady, diabatic (nonadiabatic), frictional, variable-area flow of a compressible fluid is treated in differential form on the basis of the one-dimensional approximation. The basic equations are first stated in terms of pressure, temperature, density, and velocity of the fluid. Considerable simplification and unification of the equations are then achieved by choosing the square of the local Mach number as one of the variables to describe the flow" (p. 1).
Date:
July 1947
Creator:
Hicks, Bruce L.; Montgomery, Donald J. & Wasserman, Robert H.
Object Type:
Report
System:
The UNT Digital Library
Experimental Verification of the Rudder-Free Stability Theory for an Airplane Model Equipped With a Rudder Having Positive Floating Tendencies and Various Amounts of Friction
Note presenting an investigation in the free-flight tunnel to obtain an experimental verification of the theoretical rudder-free dynamic stability characteristics of an airplane model equipped with a rudder with positive floating tendencies and various amounts of friction in the rudder system. Results regarding the rudder-free stability without friction and with friction are provided.
Date:
July 1947
Creator:
Maggin, Bernard
Object Type:
Report
System:
The UNT Digital Library
Deformation Analysis of Wing Structures
Note presenting theories of bending and torsion as applied to the problem of calculating the deflections in aircraft shell structures, particularly of wings. Bending as well as torsional deflections are discussed for wings without or with cut-outs.
Date:
July 1947
Creator:
Kuhn, Paul
Object Type:
Report
System:
The UNT Digital Library
Tests to determine the effect of heat on the pressure drop through radiator tubes
Report presenting tests to determine the effect of heat on the pressure drop through radiator tubes made to establish the adequacy of previously developed theory. Results regarding the evaluation of incompressible pressure drop, tubes with smooth entrances, and tubes with transition fixed are provided.
Date:
July 1947
Creator:
Habel, Louis W. & Gallagher, James J.
Object Type:
Report
System:
The UNT Digital Library
A Theoretical Investigation of Hydrodynamic Impact Loads on Scalloped-Bottom Seaplanes and Comparisons With Experiment
Note presenting an analytical method for calculating the hydrodynamic impact loads and motions experienced by seaplane floats and hulls with scalloped (fluted) bottoms. The analysis, which is applicable to floats with cross sections of any shape, considers that the flow about an immersing planing bottom occurs largely in transverse flow planes which are normal to the keel.
Date:
July 1947
Creator:
Milwitzky, Benjamin
Object Type:
Report
System:
The UNT Digital Library
Strength Analysis of Stiffened Beam Webs
Note presenting a method for strength analysis of stiffened shear webs, which has been revised and extended from a previous report. A set of formulas and graphs which cover all aspects of strength analysis is given, experimental data are presented, and the accuracy of the formulas as judged by comparison with the data is discussed.
Date:
July 1947
Creator:
Kuhn, Paul & Peterson, James P.
Object Type:
Report
System:
The UNT Digital Library
Performance Tests of Wire Strain Gages 5: Error in Indicated Bending Strains in Thin Sheet Metal Due to Thickness and Rigidity of Gage
Note presenting the results of tests to determine the combined effects of rigidity and thickness of wire strain gages on indicated bending strains in thin sheet metal for 15 types of single-element multistrand wire strain gages. In most cases, the indicated extreme-fiber bending strain was greater than the actual strain. The positive error caused by the finite thickness of the gage predominated over the negative error caused by the rigidity of the gage.
Date:
July 1947
Creator:
Campbell, W. R. & Medbery, A. F.
Object Type:
Report
System:
The UNT Digital Library
Performance of an axial-flow compressor rotor designed for a pitch-section lift coefficient of 1.20
Report presenting the performance of a set of axial-flow fan and compressor rotor blades with high design loading in a low-speed test blower. The efficiency curve, efficiency contours, comparison of pitch-section turning angles, and simulated blade roughness are provided.
Date:
July 1947
Creator:
Herrig, L. Joseph & Bogdonoff, Seymour M.
Object Type:
Report
System:
The UNT Digital Library
Effect of Compressibility on the Distribution of Pressures Over a Tapered Wing of NACA 230-Series Airfoil Sections
Note presenting the results of pressure-distribution measurements made during high-speed wind-tunnel tests of a tapered wing of NACA 230-series airfoil sections for a range of angles of attack and free-stream Mach numbers. The peak values of minimum pressure coefficient attained were found to correspond to local Mach numbers of 1.2 to 1.4 except at angles of attack near the low-speed stall. Results regarding the wing lift characteristics, pressure coefficients and section normal-force coefficients, and a comparison of theoretical and experimental chordwise pressure distributions are provided.
Date:
July 1947
Creator:
Pearson, E. O., Jr.
Object Type:
Report
System:
The UNT Digital Library
Wake studies of eight model propellers
Report presenting an investigation of the influences of shank form and pitch distribution on the characteristics of constant-speed propellers as determine from the wakes of eight model propellers. The experiments show that an improvement in efficiency occurs from the substitution of faired shanks for round ones, which is caused by disproportionate local augmentations of thrust and torque. Results regarding a comparison with force tests, method of comparing performance characteristics, effects of shank form, effects of pitch distribution, independence of blade elements, and section lift characteristics are provided.
Date:
July 1946
Creator:
Reid, Elliott G.
Object Type:
Report
System:
The UNT Digital Library
Effect of simulated service conditions on plastics
Report presenting an investigation of the effects of simulated surface conditions, which involved exposure to various combinations of moisture, heat, and ultraviolet light, on the weight, dimensional stability, and flexural properties of reinforced plastics.
Date:
July 1947
Creator:
Crouse, W. A.; Caudill, D. C. & Reinhart, F. W.
Object Type:
Report
System:
The UNT Digital Library
The Effect of Compressibility on the Growth of the Laminar Boundary Layer on Low-Drag Wings and Bodies
Report presenting a consideration of the development of the laminar boundary layer in a compressible fluid. Formulas are given for determining the boundary-layer thickness and the boundary-layer Reynolds number, which is a measure of the boundary-layer stability, for airfoils and bodies of revolution.
Date:
July 1947
Creator:
Allen, H. Julian & Nitzberg, Gerald E.
Object Type:
Report
System:
The UNT Digital Library
Wind-tunnel investigation of unshielded horn balances on a horizontal tail surface
Report presenting a wind-tunnel investigation to determine the aerodynamic characteristics of a horizontal tail surface with various amounts of unshielded horn balance and with the surface condition similar to that of a typical fabric-covered elevator.
Date:
July 1947
Creator:
Lowry, John G. & Crandall, Stewart M.
Object Type:
Report
System:
The UNT Digital Library
Preliminary investigation at low speed of downwash characteristics of small-scale sweptback wings
Report presenting an investigation at low speed of the downwash behind various small-scale sweptback wings. The wing configurations used in the testing ranged from aspect ratios of 2.5 to 4.0, sweepback angles from 32.5 degrees to 40 degrees, and ratios of root chord to tip chord of 0.62 to 2.06. Results regarding the effect of aspect ratio, effect of taper ratio, effect of tail span and position, and effect of high-lift devices are provided.
Date:
July 1947
Creator:
Purser, Paul E.; Spearman, M. Leroy & Bates, William R.
Object Type:
Report
System:
The UNT Digital Library
Wind-Tunnel Investigation of the Effect of Power and Flaps on the Static Lateral Stability and Control Characteristics of a Single-Engine High-Wing Airplane Model
Note presenting an investigation conducted to determine the effect of power and of full-span slotted flaps on the static lateral stability and control characteristics of a single-engine high-wing airplane with tail on and tail off. The model combinations investigated included three power conditions, including with the propeller off, propeller windmilling, and power on, and tested with the flap neutral, single slotted flap, and double slotted flap.
Date:
July 1947
Creator:
Hagerman, John R.
Object Type:
Report
System:
The UNT Digital Library
Distribution of wave drag and lift in the vicinity of wing tips at supersonic speeds
From Summary: "The point-source-distribution method of calculating the aerodynamic coefficients of thin wings at supersonic speeds was extended to include the effect of the region between the wing boundary and the foremost Mach wave from the wing leading edge. The effect of this region on the surface velocity potential has been determined by an equivalent function, which is evaluated over a portion of the wing surface. In this manner, the effect of angles of attack and yaw as well as the asymmetry of top and bottom wing surfaces may be calculated."
Date:
July 1947
Creator:
Evvard, John C.
Object Type:
Report
System:
The UNT Digital Library
A Review of Boundary-Layer Literature
"A concise nonmathematical review of the subject of boundary layers is presented. The contents, although insufficient for the solution of specific problems, are sufficient for an introduction to the subject. A list of reference papers is given from which the detailed knowledge necessary for the solution of specific problems can be obtained" (p. 1).
Date:
July 1947
Creator:
Tetervin, Neal
Object Type:
Report
System:
The UNT Digital Library
Comparison between the measured and theoretical span loadings on a moderately swept-forward and a moderately swept-back semispan wing
Report presenting an investigation in the stability tunnel on two semispan swept-wing models to determine experimentally the span-load distributions and to compare the experimental and theoretical results. Lift, drag, pitching moment, and stalling characteristics are provided.
Date:
July 1947
Creator:
Mendelsohn, Robert A. & Brewer, Jack D.
Object Type:
Report
System:
The UNT Digital Library