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Vaporization rates and heat-transfer coefficients for pure liquid drops
Report presenting an investigation to determine the vaporization rates of pure liquid drops vaporizing under conditions similar to those encountered in aircraft combustion systems using a heat-balance equation. Results regarding the analysis and experimental results are provided.
Date:
July 1951
Creator:
Ingebo, Robert D.
System:
The UNT Digital Library
Variation of Local Liquid-Water Concentration About and Ellipsoid of Fineness Ratio 5 Moving in a Droplet Field
From Summary: "Trajectories of water droplets about an ellipsoid of revolution with a fineness ratio of 5 (which often approximates the shape of an aircraft fuselage or missile) were computed with the aid of a differential analyzer. Analyses of these trajectories indicate that the local concentration of liquid water at various points about an ellipsoid in flight through a droplet field varies considerably and under some conditions may be several times the free-stream concentration."
Date:
July 1954
Creator:
Dorsch, Robert G. & Brun, Rinaldo J.
System:
The UNT Digital Library
Vibration survey of four representative types of air-cooled turbine blades
Report presenting an investigation conducted in a turbojet engine mounted in a sea-level test stand to determine the vibrational characteristics of four representative types of air-cooled turbine blades.Two were standard-span blades and two were long-span blades for high mass-flow turbines. Results regarding the coolant-flow rate, vibratory stresses, vibrational characteristics, and failures are provided.
Date:
July 1958
Creator:
Calvert, Howard F. & Smith, Gordon T.
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.
System:
The UNT Digital Library
A warning concerning the take-off with heavy load
"A successful take-off can be made with an airplane so heavily loaded that it cannot climb to a height greater than the span of its wings. The explanation is that the power required to maintain level flight at an altitude of the order of the wing span may be as much as 50 per cent greater than that necessary when the airplane is just clear of the ground. The failure of heavily loaded airplanes to continue climbing at the rate attained immediately after the actual take-off is a grave hazard and has resulted in great risk or catastrophe in three notable cases which are cited" (p. 1).
Date:
July 1927
Creator:
Reid, Elliott G. & Carroll, Thomas
System:
The UNT Digital Library
Wind-tunnel investigation at low speeds of flight characteristics of a sweptback-wing jet-transport airplane model equipped with an external-flow jet-augmented slotted flap
Report presenting a wind-tunnel investigation at low speeds to determine the flight characteristics of a model of a sweptback-wing jet-transport airplane equipped with an external-flow jet-augmented slotted flap. Results regarding the longitudinal stability characteristics, longitudinal control characteristics, lateral stability characteristics, and lateral control characteristics are provided.
Date:
July 1958
Creator:
Johnson, Joseph L., Jr.
System:
The UNT Digital Library
Wind-tunnel investigation of effects of spoiler location, spoiler size, and fuselage nose shape on directional characteristics of a model of a tandem-rotor helicopter fuselage
Report presenting a low-speed investigation made in the stability tunnel to study the effect of spoiler location, spoiler size, and fuselage nose shape on the directional stability characteristics of a model of a tandem-rotor helicopter fuselage. The model was found to be directionally unstable at certain positive angles of attack.
Date:
July 1958
Creator:
Williams, James L.
System:
The UNT Digital Library
Wind-Tunnel Investigation of Split Trailing-Edge Lift and Trim Flaps on a Tapered Wing With 23 Degree Sweepback
Note presenting the results of force tests and pressure-distribution measurements from a wind-tunnel investigation to determine the effects of size and hinge location of lift and trim flaps on the lift and pitching moment characteristics of a semispan tapered wing with 23 degrees sweepback of the quarter-chord line. The flaps were tested with different chords, spans, and trim flaps. The results indicated that the static longitudinal stability of the sweptback wing, as indicated by the slope of the curves of pitching-moment coefficient against lift coefficient, was increased when the lift flaps were deflected, especially for the larger flaps.
Date:
July 1947
Creator:
Letko, William & Feigenbaum, David
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.
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.
System:
The UNT Digital Library
Wind-tunnel investigation of the high-subsonic static longitudinal stability characteristics of several wing-body configurations designed for high lift-drag ratios at a Mach number of 1.4
Report presenting testing in the high-speed 7- by 10-foot tunnel to investigate the high-subsonic static longitudinal stability characteristics and lift-drag ratios of several wing-body models designed to provide high lift-drag ratios at Mach number 1.4. The basic configuration had a thin highly swept wing of aspect ratio 2.91 with NACA 65-A series airfoil sections. Results regarding longitudinal stability, lift, drag, and lift-drag ratio are provided.
Date:
July 1958
Creator:
Fournier, Paul G.
System:
The UNT Digital Library
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.
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.
System:
The UNT Digital Library
Wind Tunnel Pressure Distribution Tests on a Series of Biplane Wing Models Part I: Effects of Changes in Stagger and Gap
This report is on the changes in forces on each wing of a biplane cellule when either the stagger or the gap is varied. Since each test was carried up to a 90 degree angle of attack, the results may be used in the study of stalled flight and of spinning as well as in the structural design of biplane wings.
Date:
July 1929
Creator:
Knight, Montgomery & Noyes, Richard W.
System:
The UNT Digital Library
X-Ray Diffraction Investigation of Minor Phases of 20 High-Temperature Alloys
Report presenting the use of x-ray diffraction methods to identify the minor phases present in 20 high-temperature alloys in current use. The minor phases were noted in seven of the 20 alloys. A description of the relation of the alloys to one another and their chemical properties are provided.
Date:
July 1948
Creator:
Rosenbaum, B. M.
System:
The UNT Digital Library