Serial/Series Title
Month
345 Matching Results
Results open in a new window/tab.
Results:
1 - 24 of
345
next
The 300 H.P. Benz Aircraft Engine
This report provides a description of the Benz 300 H.P. aircraft engine containing 12 cylinders placed at a 60° angle. It includes a detailed description of the development of the constructional points, particularly the cylinders, pistons, and connecting rods, as well as the engine fitting, lubrication, oil pumps, bearings, oil tank, fuel pump, carburetors, and cooling system. There are seven pages of illustrative figures at the end of the report.
Date:
January 1921
Creator:
Heller, A.
System:
The UNT Digital Library
N.A.C.A. Langley field wind tunnel apparatus: The tilting manometer
A description is given of a tilting manometer designed to meet the requirements of a manometer for use in the wind tunnel at the Langley Memorial Aeronautical Laboratory. This gauge was designed to meet the requirements of a manometer in use in connection with a static pressure plate to indicate the wind speed in the tunnel. The requirements are noted. The sensitivity of the gauge must be made inversely proportional to the pressure to be measured. The gauge must be accurately and quickly set for any desired pressure.
Date:
January 1921
Creator:
Norton, F. H. & Bacon, D. L.
System:
The UNT Digital Library
Absolute Dimensions of Karman Vortex Motion
Note presenting an investigation of the Karman vortex street, which is a flow arrangement occurring behind a plate. The equations governing the flow and some of the hypotheses behind it are provided.
Date:
January 1923
Creator:
Heisenberg, Werner
System:
The UNT Digital Library
Achievement of Continuous Wall Curvature in Design of Two-Dimensional Symmetrical Supersonic Nozzles
"Auxiliary boundary conditions are derived to assure continuity of wall curvature in applying the method of characteristics to the design of two-dimensional symmetrical supersonic nozzles. An illustrative example is included" (p. 1).
Date:
January 1952
Creator:
Evvard, J. C. & Marcus, Lawrence R.
System:
The UNT Digital Library
Aerodynamic Characteristics of a Circular Cylinder at Mach Number 6.86 and Angles of Attack Up to 90 Degrees
"Pressure-distribution and force tests of a circular cylinder have been made in the Langley 11-inch hypersonic tunnel at a Mach number of 6.88, a Reynolds number of 129,000, and angles of attack up to 90 degrees. The results are compared with the hypersonic approximation of Grimminger, Williams, and Young and a simple modification of the Newtonian flow theory. An evaluation of the crossflow theory is made through comparison of present results with available crossflow Mach number drag coefficients" (p. 1).
Date:
January 1957
Creator:
Penland, Jim A.
System:
The UNT Digital Library
Aerodynamic characteristics of a two-blade NACA 10-(3)(062)-045 propeller and of a two-blade NACA 10-(3)(08)-045 propeller
Report discussing characteristics are given for the two-blade NACA 10-(3)(062)-045 propeller and for the two-blade NACA 10-(3)(08)-045 propeller over a range of advance ratio from 0.5 to 3.8, through a blade-angle range from 20 degrees to 55 degrees measured at the 0.75 radius. Maximum efficiencies of the order of 91.5 to 92 percent were obtained for the propellers. The propeller with the thinner airfoil sections over the outboard portion of the blades, the NACA 10-(3)(062)-045 propeller, had lower losses at high tip speeds, the difference amounting to about 5 percent at a helical tip Mach number of 1.10.
Date:
January 1953
Creator:
Solomon, William
System:
The UNT Digital Library
Aerodynamic Characteristics of Damping Screens
From Summary: "The experimental investigation of damping screens described herein was undertaken primarily to test theories of the effects of damping screens and to obtain information on the performance of screens in oblique flow. The characteristics investigated include the damping of longitudinal and lateral components of turbulence, the effect of screens on scale, the conditions for the production of turbulence and eddies by screens, and the damping of spatial variations of mean speed."
Date:
January 1950
Creator:
Schubauer, G. B.; Spangenberg, W. G. & Klebanoff, P. S.
System:
The UNT Digital Library
Aerodynamic characteristics of NACA 0012 airfoil section at angles of attack from 0 degrees to 180 degrees
Report presenting the aerodynamic characteristics of the NACA 0012 airfoil section at a range of angles of attack from 0 to 180 degrees. Data were obtained at two different Reynolds numbers depending on whether the airfoil surfaces were smooth or had roughness applied at the leading and trailing edges. After the stall with the rounded edge of the airfoil foremost, a second lift-coefficient peak was obtained at an angle of attack of about 45 degrees.
Date:
January 1955
Creator:
Critzos, Chris C.; Heyson, Harry H. & Boswinkle, Robert W., Jr.
System:
The UNT Digital Library
Aerodynamic interference of slender wing-tail combinations
From Introduction: "In the present paper, the emphasis is placed on calculating the variations of total forces and moments with angles of attack and sideslip for a number of slender plane and cruciform wing-tail combinations and for some airplane-type arrangements of a plane wing and a horizontal and vertical tail."
Date:
January 1957
Creator:
Sacks, Alvin H.
System:
The UNT Digital Library
Aircraft Engine Design
From Introduction: "The subject of this paper is so broad in scope that a large volume might be devoted to it. In a short paper of this kind it is possible simply to sketch in the high lights of aircraft engine design showing the development to date, the possibilities of the future, and the underlying fundamental principles. Summarizing this development and referring to the graph (Fig.1), we that there is now a water-cooled engine in every power from 150 to 800 HP. and an air-cooled engine in the 200 to 400 HP. classes."
Date:
January 1925
Creator:
Wilson, E. E.
System:
The UNT Digital Library
Airplanes in horizontal curvilinear flight
The report discussing single and two-seater airplanes as well as larger airplanes.
Date:
January 1924
Creator:
Kann, Heinrich
System:
The UNT Digital Library
The Ames 10- by 14-Inch Supersonic Wind Tunnel
"The purpose of the present report is to describe the 10- by 14-inch supersonic wind tunnel and its operational characteristics over the nominal Mach number range from 2.7 to 6.3. Rather complete calibration data on characteristics of flow in the test section are presented and briefly discussed" (p. 2).
Date:
January 1954
Creator:
Eggers, A. J., Jr. & Nothwang, George J.
System:
The UNT Digital Library
Analysis of Laminar Forced-Convection Heat Transfer in Entrance Region of Flat Rectangular Ducts
From Introduction: "Beyond the position where the boundary layer treatment can no longer be used, curves have been faired to connect the Nusselt number results of the present analysis with those of reference 3, in which a parabolic velocity profile is assumed throughout the entire duct length. So that a comparison could be made with the results of reference 3, the boundary layer analysis was used to study the development of the temperature profile associated with a parabolic velocity profile throughout."
Date:
January 1955
Creator:
Sparrow, E. M.
System:
The UNT Digital Library
Analysis of Straight Multicell Wings on Cal-Tech Analog Computer
Note presenting structural analyses made for four straight multicell wings. Wings with aspect ratios of 2 and 4 with rectangular and biconvex cross sections have been considered. The results indicated that under bending loads, all of the wings show fairly good agreement with beam theory.
Date:
January 1954
Creator:
Benscoter, Stanley U. & MacNeal, Richard H.
System:
The UNT Digital Library
Analysis of Sweptback Wings on Cal-Tech Analog Computer
Note presenting structural analyses made of two 45 degree swept wings of aspect ratio 3. One has a constant depth and the other had a constant biconvex cross section in planes parallel to the air stream. Deflections, all internal forces, and vibration modes have been calculated for concentrated static loads.
Date:
January 1954
Creator:
MacNeal, Richard H. & Benscoter, Stanley U.
System:
The UNT Digital Library
Analytical investigation of acceleration restriction in a fighter airplane with an automatic control system
From Introduction: "In the present report, consideration is given to certain features intended to improve the accleration-limiting characteristics of a normal-accleration control system."
Date:
January 1958
Creator:
Matthews, James T., Jr.
System:
The UNT Digital Library
Analytical investigation of icing limit for diamond-shaped airfoil in transonic and supersonic flow
From Introduction: "The results presented herein were calculated for a symmetrical diamond airfoil at zero angle of attack for a range of airfoil-thickness ratios from 0.02 to 0.10, pressure altitude from sea level to 45,000 feet, and free-stream static temperatures to -.40^o F."
Date:
January 1953
Creator:
Callaghan, Edmund E. & Serafini, John S.
System:
The UNT Digital Library
Analytical Investigation of Icing Limit for Diamond-Shaped Airfoil in Transonic and Supersonic Flow
Calculations have been made for the icing limit of a diamond airfoil at zero angle of attack in terms of the stream Mach number, stream temperature, and pressure altitude. The icing limit is defined as a wetted-surface temperature of 320 F and is related to the stream conditions by the method of Hardy. The results show that the point most likely to ice on the airfoil lies immediately behind the shoulder and is subject to possible icing at Mach numbers as high as 1.4.
Date:
January 1953
Creator:
Callaghan, Edmund E. & Serafini, John S.
System:
The UNT Digital Library
Analytical investigation of the effect of water injection on supersonic turbojet-engine - inlet matching and thrust augmentation
From Introduction: "In order to provide engine-inlet matching to prevent such mass flow spillage and the attendant drags, much mechanical complication has been introduced. References 1 and 2 propose employing this principle at subsonic and supersonic speeds to achieve thrust augmentation. The merits of the system for supersonic engine-inlet airflow matching, as well as thrust augmentation, appear considerable; and a comparative study with existing fixed- and variable-geometry inlets was therefore undertaken."
Date:
January 1957
Creator:
Beke, Andrew
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
Application of the Laplace Transformation to the Solution of the Lateral and Longitudinal Stability Equations
Note presenting the application of the Laplace transformation to the solution of the lateral and longitudinal stability equations. The expressions for the time history of the motion in response to a sinusoidal control motion are derived for the general case in which all initial measurements are assumed different from zero.
Date:
January 1950
Creator:
Mokrzycki, G. A.
System:
The UNT Digital Library
Base pressure at supersonic speeds on two-dimensional airfoils and on bodies of revolution with and without fins having turbulent boundary layers
From Summary: "An analysis has been made of available experimental data to show the effects of most of the variables that are more predominant in determining base pressure at supersonic speeds. The analysis covers base pressures for two-dimensional airfoils and for bodies of revolution with and without stabilizing fins and is restricted to turbulent boundary layers. The present status of available experimental information is summarized as are the existing methods for predicting base pressure."
Date:
January 1957
Creator:
Love, Eugene S.
System:
The UNT Digital Library
Bearing Strengths of Some 75S-T6 and 14S-T6 Aluminum-Alloy Hand Forgings
Note presenting results from an investigation of bearing properties of some 75S-T6 and 14S-T6 aluminum-alloy hand forgings in the longitudinal and long transverse directions and in surface and center locations.
Date:
January 1953
Creator:
Finley, E. M.
System:
The UNT Digital Library
Behavior in pure bending of a long monocoque beam of circular-arc cross section
From Summary: "An analysis is made of the behavior under a loading of pure bending moment of a thin, infinitely long, pure-monocoque beam having a constant, doubly symmetric, circular-arc cross section. Bending moments, deflections, and stresses are obtained. The analysis shows a nonlinear behavior in bending which leads ultimately to a maximum amount and instability."
Date:
January 1953
Creator:
Fralich, Robert W.; Mayers, J. & Reissner, Eric
System:
The UNT Digital Library