Serial/Series Title
Country
States
346 Matching Results
Results open in a new window/tab.
Results:
1 - 24 of
346
next
Visual Studies of Cylinder Lubrication [Part] 1: The Lubrication of the Piston Skirt
Report describes the lubrication characteristics of an aircraft-type piston as visually studied in a V-type engine with a glass cylinder. Information about the movement of the piston, the piston rings, and the oil-control rings and their effect on lubrication is included.
Date:
September 1945
Creator:
Shaw, Milton C. & Nussdorfer, Theodore
System:
The UNT Digital Library
Analysis of Heat and Compressibility Effects in Internal Flow Systems and High-Speed Tests of a Ram-Jet System
Report presenting an analysis of the effects of heat and compressibility in the flow through the internal systems of aircraft. Equations and charts are developed whereby the flow characteristics at key stations in a typical internal system may be readily obtained.
Date:
September 1942
Creator:
Becker, John V. & Baals, Donald D.
System:
The UNT Digital Library
The Propeller and Cooling-Air-Flow Characteristics of a Twin-Engine Airplane Model Equipped With NACA D(Sub S)-Type Cowlings and With Propellers of NACA 16-Series Airfoil Sections
Report presenting an investigation in the 19-foot pressure tunnel to determine the nacelle drag, the cowling-air flow, and the propeller characteristics of a model of a high-performance military airplane. The model is fitted with NACA D(sub S)-type engine cowlings and with propellers embodying NACA 16-series airfoil sections. Results regarding the propeller characteristics, drag and cowling-air flow with the propeller removed, the effect of propeller on flow through cowling, and the influence of cooling requirements on airplane performance are provided.
Date:
September 1944
Creator:
McHugh, James G. & Pepper, Edward
System:
The UNT Digital Library
Notes on the Effect of Surface Distortions on the Drag and Critical Mach Number of Airfoils
"The effect of two-dimensional bumps and surface waviness on the pressure distribution over airfoils is considered. It is shown that the results of the analysis may be useful in evaluating the effects of accidental or intended surface distortions on the drag and critical Mach number of airfoils" (p. 1).
Date:
September 1943
Creator:
Allen, H. Julian
System:
The UNT Digital Library
Air-consumption parameters for automatic mixture control of aircraft engines
From Introduction: "The purpose of this analysis was to investigate the use of function of intake-manifold temperature and pressure, exhaust back pressure, and engine speed in place of a ventri as a means of measuring engine air consumption and to determine if this function is suitable for automatic mixture control."
Date:
September 1944
Creator:
Shames, Sidney J.
System:
The UNT Digital Library
A Discussion of the Application of the Prandtl-Glauert Method to Subsonic Compressible Flow Over a Slender Body of Revolution
Note presenting an analysis of the use of the Prandtl-Glauert method for subsonic potential flow of a compressible fluid. This paper specifically focuses on the difference between the two- and three-dimensional flow when using this method.
Date:
September 1946
Creator:
Lees, Lester
System:
The UNT Digital Library
Methods for Determination and Computation of Flow Patterns of a Compressible Fluid
Note presenting a well-known method of generating stream functions of an incompressible fluid flow, which involves taking the imaginary part of an analytic function of a complex variable. This paper is specifically devoted to a detailed discussion of performing computations related to obtaining flow patterns of compressible fluid from analytic functions of a compressible fluid. An example is also provided to illustrate the method.
Date:
September 1946
Creator:
Bergman, Stefan
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
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
Stress Rupture of Heat Resisting Alloys as a Rate Process
Note presenting the application of the equations of the theory of rate processes to stress rupture in order to predict the experimental stress and temperature dependence of the time for rupture for three heat-resisting alloys. Results regarding stress dependence, temperature dependence of slope factor, and temperature dependence of apparent free energy of activation are provided.
Date:
September 1946
Creator:
Machlin, E. S. & Nowick, A. S.
System:
The UNT Digital Library
Effect of a Trailing-Edge Extension on the Characteristics of a Propeller Section
Report presenting a convenient technical method to evaluate changes in the airfoil characteristics resulting from an extension of the chord at the trailing edge of a propeller blade section. The method determines the change in the angle of zero lift, the ideal angle of attack, and the difference in these angles as a function of the angle and length of the trailing-edge extension.
Date:
September 1944
Creator:
Theodorsen, Theodore & Stickle, George W.
System:
The UNT Digital Library
Wind-Tunnel Investigation of Control-Surface Characteristics 4: A Medium Aerodynamic Balance of Various Nose Shapes Used With a 30-Percent-Chord Flap on an NACA 0009 Airfoil
Report presenting tests made in the 4- by 6-foot vertical wind tunnel of an NACA 0009 airfoil with a 30-percent-chord flap with a medium amount of aerodynamic overhanging balance. In this investigation, the effects of the shape of the flap-nose overhang and the gap at the nose of the flap have been determined. The results indicate that, generally, the lift effectiveness of the aerodynamically balanced flap was increased slightly over that of a plain flap when a blunt or medium flap nose was used on the balanced flap.
Date:
September 1941
Creator:
Ames, Milton B., Jr. & Eastman, Donald R., Jr.
System:
The UNT Digital Library
Flutter tests of B-34 fin-rudder-tab system
From Summary: "Tests on the B-34 fin-rudder-tab assembly were performed in the NACA 8-foot high-speed tunnel. Two cases of tab flutter were studied. It was shown conclusively that the frequency of the original or heavy tab was too low and caused coupling with one of the lower bending frequencies. A general conclusion was made that the tab frequency should be considerably higher than the lower modes of the fin-rudder assembly because there is generally a weaker coupling between the tab and the higher mode responses."
Date:
September 1944
Creator:
Theodorsen, Theodore
System:
The UNT Digital Library
Wind tunnel investigation of control-surface characteristics 10: a 30-percent-chord plain flap with straight contour on the NACA 0015 airfoil
Report presenting force-test measurements in two-dimensional flow in the 4- by 6-foot vertical tunnel to determine the characteristics of an NACA 0015 airfoil equipped with a straight-contour plain flap with a chord 30 percent of the airfoil chord. Results regarding the lift, hinge moment of flap, pitching moment, and drag are provided.
Date:
September 1942
Creator:
Hoggard, H. Page, Jr.
System:
The UNT Digital Library
Airfoil Section Data From Tests of 10 Practical-Construction Sections of Helicopter Rotor Blades Submitted by the Sikorsky Aircraft Division, United Aircraft Corporation
Report presenting 10 practical-construction models of sections of helicopter rotor blades tested in the NACA two-dimensional low-turbulence pressure tunnel at atmospheric pressure. Lift, drag, and pitching-moment characteristics of blades representing the present method of construction of the YR-4A helicopter were determined.
Date:
September 1944
Creator:
Tetervin, Neal
System:
The UNT Digital Library
Aerodynamic Characteristics of the NACA 747A315 and 747A415 Airfoils From Tests in the NACA Two-Dimensional Low-Turbulence Pressure Tunnel
Report presenting two low-drag airfoils, the NACA 747A315 and the NACA 747A415, which are designed to have reduced pitching moments about the quarter-chord point and moderately high values of the design lift coefficient and are tested in the tow-dimensional low-turbulence pressure tunnel.
Date:
September 1944
Creator:
von Doenhoff, Albert E. & Stivers, Louis S., Jr.
System:
The UNT Digital Library
A method for predicting the elevator deflection required to land
Report presenting a method for predicting from basic airplane characteristics the elevator deflection required to maintain optimum landing attitude. Charts for evaluating the components of the equation for elevator deflection and a comparison of computed and measured values for 15 airplanes are included. The computed deflection is considered the minimum value required to maintain landing attitude due to variations in piloting technique.
Date:
September 1944
Creator:
Goranson, R. Fabian
System:
The UNT Digital Library
Wind-Tunnel Tests of Ailerons at Various Speeds 3: Ailerons of 0.20 Airfoil Chord and True Contour With 0.35-Aileron-Chord Frise Balance on the NACA 23012 Airfoil
Report presenting hinge moment, lift, and pressure-distribution measurements made on a Frise aileron on an NACA 23012 airfoil in the two-dimensional test section of the stability tunnel. Speeds up to 360 miles per hour corresponding to a Mach number of about 0.470 were used.
Date:
September 1943
Creator:
Letko, W. & Kemp, W. B.
System:
The UNT Digital Library
Aerodynamic and Hydrodynamic Tests of a Family of Models of Flying-Boat Hulls Derived From a Streamline Body: NACA Model 84 Series
Report presenting a series of related flying-boat hull forms with various combinations of aerodynamic and hydrodynamic requirements that were tested in an NACA tank and high-speed tunnel. Effects explored included varying the height of the bow, varying the height of the stern, increasing the angle of dead rise at the bow, decreasing the angle of dead rise on the afterbody, increasing the depth of step, increasing the angle of afterbody keel, adding chine flare, adding a third planing surface, and rounded chines at the bow.
Date:
September 1943
Creator:
Parkinson, John B.; Olson, Roland E.; Draley, Eugene C. & Luoma, Arvo A.
System:
The UNT Digital Library
Preliminary Tests in the NACA Tank to Investigate the Fundamental Characteristics of Hydrofoils
A preliminary investigation made to study the hydrodynamic properties and general behavior of simple hydrofoils. Six plain, rectangular hydrofoils were tested in a tank at various speeds, angles of attack, and depths below the water surface. The results are presented as curves of the lift and drag coefficients plotted against speed for various angles of attack and depths for which the hydrofoils were tested.
Date:
September 1940
Creator:
Ward, Kenneth E. & Land, Norman S.
System:
The UNT Digital Library
An investigation of aircraft heaters 24: the heat meter in the transient state for unidirectional heat transfer
Report describing the behavior of the heat meter when it is used in thermal circuits which are under the influence of transient potentials. Three scenarios are considered: a heat meter suddenly placed on a hot surface, a heat meter mounted on the interior surface of the cabin wall of an uninsulated airplane climbing through air of decreasing temperature, and a heat meter mounted on the interior surface of the composite cabin wall of an airplane climbing through air of decreasing temperature.
Date:
September 1944
Creator:
Boelter, L. M. K.; Poppendiek, H. F.; Dunkle, R. V. & Gier, J. T.
System:
The UNT Digital Library
Wind Tunnel Investigation of Control-Surface Characteristics 23: A 0.25-Airfoil-Chord Flap With Tab Having a Chord Twice the Flap Chord on an NACA 0009 Airfoil
Report presenting wind-tunnel tests to determine the aerodynamic section characteristics of an NACA 0009 airfoil with a plain flap with a chord 25 percent of the airfoil chord and a balancing tab with a chord 50 percent of the airfoil chord or 200 percent of the flap chord so linked that the tab would deflect at a given rate with respect to the flap. Three linkage ratios were tested on the model. Results regarding theory and test results including lift and hinge moments are provided.
Date:
September 1945
Creator:
Spearman, M. Leroy
System:
The UNT Digital Library