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1,074
Flight Results from a 1/10-Scale Rocket Model of the Lockheed XF-104 Airplane at Transonic Mach Numbers
"A 1/10-scale rocket model of the Lockheed XF-104 with faired inlets has been flown over a Mach number range from 0.80 to 1.45 to determine low-lift drag and a limited amount of stability data. The center-of-gravity locations were 4.0 and 1.5 percent of the mean aerodynamic chord before and after sustainer firing, respectively. Oscillations induced by pulse rockets were used to determine stability data. The external transonic drag coefficient increased from a value of 0.0160 at Mach number 0.80 to a maximum of 0.0432 near Mach number 1-13, with a drag rise Mach number of about 0.93. At Mach numbers where it could be determined, the model exhibited stable dynamic and static stability characteristics at low lift" (p. 1).
Date:
May 14, 1954
Creator:
Kehlet, Alan B.
System:
The UNT Digital Library
Wheel Brakes and Their Application to Aircraft
"The advantages to be gained from braking have not been ignored, and in the search for a suitable method many schemes have been suggested and tried. Some of the methods discussed in this paper include: 1) increasing the height of the landing gear; 2) air brakes of various forms; 3) sprags on tail skid and axle; and 4) wheel brakes. This report focuses on the design of wheel brakes and wheel brake controls" (p. 1).
Date:
May 1928
Creator:
Dowty, G. H.
System:
The UNT Digital Library
Preliminary Results of the Determination of Inlet-Pressure Distortion Effects on Compressor Stall and Altitude Operating Limits of the J57-P-1 Turbojet Engine
"During an investigation of the J57-P-1 turbojet engine in the Lewis altitude wind tunnel, effects of inlet-flow distortion on engine stall characteristics and operating limits were determined. In addition to a uniform inlet-flow profile, the inlet-pressure distortions imposed included two radial, two circumferential, and one combined radial-circumferential profile. Data were obtained over a range of compressor speeds at an altitude of 50,000 and a flight Mach number of 0.8; in addition, the high- and low-speed engine operating limits were investigated up to the maximum operable altitude" (p. 1).
Date:
May 23, 1955
Creator:
Wallner, L. E.; Lubick, R. J. & Chelko, L. J.
System:
The UNT Digital Library
On the Strength of Box Type Fuselages
The present investigation relates to a box-type fuselage with sides consisting of thin smooth sheet metal, stiffened by longitudinal members riveted to the flanged channel-section bulkheads or transverse frames and to the semicircular corrugated corner stiffenings. The results obtained in this particular case can be applied to a great number of similar structures.
Date:
May 1929
Creator:
Mathar, J.
System:
The UNT Digital Library
Materials and Methods of Construction in Light Structures
Different methods of constructing light airplanes are presented with a view toward increasing production and efficiency.
Date:
May 1929
Creator:
Rohrbach, Adolf
System:
The UNT Digital Library
An investigation of aircraft heaters 12: performance of a formed-plate crossflow exhaust gas and air heat exchanger
Report presenting performance data on a Trane exhaust gas and air heat exchanger. Heat transfer rates were measured using specified exhaust gas rates and ventilating-air rates. The measured thermal outputs and static pressure drops are compared with predicted magnitudes.
Date:
May 1943
Creator:
Boelter, L. M. K.; Dennison, H. G.; Guibert, A. G. & Morrin, E. H.
System:
The UNT Digital Library
Investigations on Laminar Boundary-Layer Stability and Transition on Curved Boundaries
Report presenting an investigation of the transition of the boundary layer from the laminar to the turbulent region on a flat plate, on the concave and convex side of a plate with a 20-foot radius of curvature, and on the convex side of a plate with a 30-inch radius of curvature.
Date:
May 1946
Creator:
Liepmann, Hans W.
System:
The UNT Digital Library
Extended operation of turbojet engine with pentaborane
A full-scale turbojet engine was operated with pentaborane fuel continuously for 22 minutes at conditions simulating flight at a Mach number of 0.8 at an altitude of 50,000 feet. This period of operation is approximately three times longer than previously reported operation times. Although the specific fuel consumption was reduced from 1.3 with JP-4 fuel to 0.98 with pentaborane, a 13.2-percent reduction in net thrust was also encountered. A portion of this thrust loss is potentially recoverable with proper design of the engine components. The boron oxide deposition and erosion processes within the engine approached an equilibrium condition after approximately 22 minutes of operation with pentaborane.
Date:
May 22, 1957
Creator:
Useller, James W. & Jones, William L.
System:
The UNT Digital Library
Wind-Tunnel Tests of a Hall High-Life Wing
"Wind-tunnel tests have been made to find the lift, drag, and center-of-pressure characteristics of a Hall high-lift wing model. The Hall wing is essentially a split-flap airfoil with an internal air passage. Air enters the passage through an opening in the lower surface somewhat back of and parallel to the leading edge, and flows out through an opening made by deflecting the rear portion of the under surface downward as a flap. For ordinary flight conditions the front opening and the rear flap can be closed, providing in effect a conventional airfoil (the Clark Y in this case)" (p. 1).
Date:
May 1932
Creator:
Weick, Fred E. & Sanders, Robert
System:
The UNT Digital Library
Aerodynamic characteristics of several 6-percent-thick airfoils at angles of attack from 0 degrees to 20 degrees at high subsonic speeds
Report presenting two-dimensional tests of eight 6-percent-thick symmetrical airfoils of the supersonic and subsonic types. Static pressures along the surfaces of each airfoil measured over a range of Mach numbers and angles of attack. Results regarding lift coefficient, drag coefficient, quarter-chord pitching-moment coefficient, and schileren photographs of the pressure distributions are provided.
Date:
May 1955
Creator:
Daley, Bernard N. & Lord, Douglas R.
System:
The UNT Digital Library
Plastic Mountings for Aircraft Windshields
Note presenting an investigation of several laminated glass windshields to determine their suitability for use in airplanes with pressurized cabins. The various constructions of the extended portions of the windshields which serve for mounting purposes included plastic alone, plastic and one sheet of glass extended, plastic extension reinforced with an aluminum strip, and plastic extension reinforced with a steel strip. The results indicated that the laminated windshields with plastic-mounting extensions reinforced by aluminum or steel were resistant to creep and bursting at pressures of the order that will be encountered in service.
Date:
May 1944
Creator:
Bradley, Kathryn H. & Axilrod, B. M.
System:
The UNT Digital Library
The numerical solution of compressible fluid flow problems
Numerical methods have been developed for obtaining the steady, adiabatic flow field of a frictionless, perfect gas about arbitrary two-dimensional bodies. The solutions include the subsonic velocity regions, the supersonic velocity regions, and the transition compression shocks, if required. Furthermore, the rotational motion and entropy changes following shocks are taken into account. Extensive use is made of the relaxation method. In this report the details of the methods of solution are emphasized so as to permit others to solve similar problems. Solutions already obtained are mentioned only by way of illustrating the possibilities of the methods described. The methods can be applied directly to wind tunnel and free air tests of arbitrary airfoil shapes at subsonic, sonic, and supersonic speeds.
Date:
May 1944
Creator:
Emmons, Howard W.
System:
The UNT Digital Library
Charts for rapid analysis of 45 degree strain-rosette data
From Summary: "Charts are presented for rapidly determining the principal strains and stresses, the maximum shear strain and stress, and the orientation of principal axes from data on 45 degree strain rosettes. The charts may be used for analyzing the conventional data consisting of strains measured along three gage lines 45 degrees apart, but their application is more direct if the rosette data are obtained by means of special circuits that require the use of four gages 45 degrees apart."
Date:
May 1944
Creator:
Manson, S. S.
System:
The UNT Digital Library
An automatic electrical analyzer for 45 degree strain-rosette data
Report presenting a device that automatically analyses the data from a 45 degree strain rosette. The rosette strains are properly combined by means of an electric circuit to yield a direct meter reading of maximum shear strain and major and minor principal strains.
Date:
May 1944
Creator:
Manson, S. S.
System:
The UNT Digital Library
Two-Dimensional Irrotational Mixed Subsonic and Supersonic Flow of a Compressible Fluid and the Upper Critical Mach Number
Note presenting the use of the hodograph method to investigate the problem of flow of a compressible fluid past a body with subsonic flow at infinity. Explicit formulas for numerical calculations are given for the flow about a body, such as an elliptical cylinder, and for the periodic flow such as would exist over a wavy surface.
Date:
May 1946
Creator:
Tsien, Hsue-Shen & Kuo, Yung-Huai
System:
The UNT Digital Library
Lightning Discharges to Aircraft and Associated Meteorological Conditions
A summary is given of information on atmospheric electrical discharges to aircraft and associated meteorological conditions. Information is given that is designed to give a fairly comprehensive view of the underlying principles of meteorology and atmospheric electricity. Of special interest to pilots are lists of procedures of flight conduct and aircraft maintenance recommended foe avoiding or minimizing the hazards of disruptive electrical discharges and other severe conditions near thunderstorms.
Date:
May 1946
Creator:
Harrison, L. P.
System:
The UNT Digital Library
The theoretical flow of a frictionless, adiabatic, perfect gas inside of a two-dimensional hyperbolic nozzle
Report presenting a study of the two-dimensional flow of a frictionless, adiabatic, perfect gas inside of a two-dimensional hyperbolic nozzle by using numerical methods.
Date:
May 1946
Creator:
Emmons, Howard W.
System:
The UNT Digital Library
Design and calibration of a total-temperature probe for use at supersonic speeds
Report presenting a study of the factors involved in the design of total-temperature probes for use at supersonic speeds as applied to the design of an instrument to be used in wind-tunnel calibrations. Tests of the probe showed that the calibration factor required in the conversion of the measured temperature to the true total temperature was 0.992 for a range of Mach numbers.
Date:
May 1949
Creator:
Goldstein, David L. & Scherrer, Richard
System:
The UNT Digital Library