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The effect of accelerating a hypothetical aircraft through the transonic range with controls fixed
Memorandum presenting Mach number histories of the motion experienced by a hypothetical, small, straight-wing aircraft accelerating at various rates through an assumed controls-fixed pitch-down balance change in the transonic range. Two approximate analytical solutions of the longitudinal equations of motion are developed which are based on certain simplifying assumptions indicated by the differential-analyzer results.
Date:
April 4, 1950
Creator:
Matthews, Howard F.
System:
The UNT Digital Library
An Experimental Investigation of a Jet-Engine Nacelle in Several Positions on a 37.25 Degree Swept-Back Wing
Memorandum presenting wind-tunnel testing of a jet-engine nacelle on a semispan wing with the leading edge swept back 37.25 degrees made to determine the effects of the nacelle on the aerodynamic characteristics of the wing. In comparison with the force characteristics of the wing alone, the addition of the nacelle to the wing in each position resulted in favorable interference on the maximum-lift and pitching-moment characteristics and in a small increase in drag.
Date:
April 19, 1950
Creator:
Dannenberg, Robert E. & Blackaby, James R.
System:
The UNT Digital Library
An Investigation of a Supersonic Aircraft Configuration Having a Tapered Wing With Circular-Arc Sections and 40 Degree Sweepback: Static Longitudinal Stability and Control Characteristics at a Mach Number of 1.40
Memorandum presenting an investigation conducted in the 4- by 4-foot supersonic tunnel to determine the longitudinal stability and control characteristics of a model of a supersonic airplane configuration at Mach number 1.40. The model had a 40 degree sweptback wing with 10-percent-thick circular-arc sections normal to the quarter-chord line. The results indicated a high degree of longitudinal stability that was fairly constant throughout the trim-lift-coefficient range.
Date:
April 3, 1950
Creator:
Spearman, M. Leroy
System:
The UNT Digital Library
Altitude performance and operational characteristics of 29-inch-diameter tail-pipe burner with several fuel systems and fuel-cooled stage-type flame holders on J35-A-5 turbojet engine
An investigation of tail-pipe burning was conducted in the NACA Lewis altitude wind tunnel with a full-scale turbojet engine and an 29-inch-diameter tail-pipe burner. Effects of fuel distribution and number and arrangement of stages on performance and operational characteristics of several fuel-cooled flame holders are presented and discussed. Operation with a three-stage flame holder having the large stage upstream was the most efficient. Combustion efficiency was slightly increased at high altitudes by injecting fuel upstream of the flame holder.
Date:
April 28, 1950
Creator:
Golladay, Richard L. & Bloomer, Harry E.
System:
The UNT Digital Library
Effect of wing-tank location on the drag and trim of a swept-wing model as measured in flight at transonic speeds
Report presenting results of an exploratory free-flight investigation at zero lift of several rocket-powered drag research models equipped wing wing tanks at a range of Mach numbers. The tanks, which were slender bodies of revolution, were mounted on 34 degrees sweptback, nontapered wings of 2.7 aspect ratio. Results regarding drag and trim change are provided.
Date:
April 4, 1950
Creator:
Welsh, Clement J. & Morrow, John D.
System:
The UNT Digital Library
Investigation of the aerodynamic and icing characteristics of a recessed fuel cell vent assembly 3: NACA flush-inlet-type vent
An investigation conducted in the icing research tunnel to determine aerodynamic and icing characteristics of two flush-inlet-type fuel cell vent installations. The vent tubes were mounted in two different locations in the two installations. The vents were aerodynamically investigated to obtain vent-tube static-pressure differentials and pressure surveys as a function of tunnel-air velocity and angle of attack.
Date:
April 23, 1948
Creator:
Ruggeri, Robert S.
System:
The UNT Digital Library
Additional Results in a Free-Flight Investigation of Control Effectiveness of Full-Span, 0.2-Chord Plain Ailerons at High Subsonic, Transonic, and Supersonic Speeds to Determine Some Effects of Wing Sweepback, Aspect Ratio, Taper, and Section Thickness Ratio
Report discussing an aerodynamic control effectiveness study using free-flight, rocket-propelled test vehicles. Information about the effects of wing sweepback, aspect ratio, taper ratio, and section thickness ratio on the rolling effectiveness of full-span, sealed ailerons is provided.
Date:
April 23, 1948
Creator:
Sandahl, Carl A. & Strass, H. Kurt
System:
The UNT Digital Library
A Summary and Analysis of Wind-Tunnel Data on the Lift and Hinge-Moment Characteristics of Control Surfaces Up to a Mach Number of 0.90
Report presenting an extensive collection of lift and hinge-moment characteristics of control surfaces up to a Mach number of 0.90 in a high-speed wind tunnel. A wide variety of control-surface profiles, plan forms, and aerodynamic balances are included. Results regarding elevator hinge moments and longitudinal control, aileron hinge moments and lateral control, control-surface characteristics, and transonic flutter are highlighted.
Date:
April 30, 1948
Creator:
Axelson, John A.
System:
The UNT Digital Library
Free-Fall Measurements at Transonic Velocities of the Drag of a Wing-Body Configuration Consisting of a 45 Degree Swept-Back Wing Mounted Forward of the Maximum Diameter on a Body of Fineness Ratio 12
Report presenting the drag of a series of complete airplane-like configurations and their components at transonic velocities using the free-fall method. The configuration tested in this report has a 45 degree sweptback wing of aspect ratio 4.1 mounted forward of the maximum diameter of a 10-inch-diameter body of fineness ratio 12 equipped with stabilizing tail fins. Results are presented as curves showing the variation of drag coefficient with Mach number for the complete configuration and for each component.
Date:
April 2, 1947
Creator:
Mathews, Charles W. & Thompson, Jim Rogers
System:
The UNT Digital Library
Wind-Tunnel Investigation of Horizontal Tails 1: Unswept and 35 Degrees Swept-Back Plan Forms of Aspect Ratio 3
Memorandum presenting the results of a wind-tunnel investigation of the low-speed characteristics of horizontal tails of aspect ratio 3 with unswept and swept-back plan forms. Two models were tested which had identical areas, aspect ratio, taper ratio, and airfoil section, differing only in the angle of sweepback and elevator area ratios. The major effect of sweepback was to increase the rate of change of hinge-moment coefficient with angle of attack, to reduce the rate of change with elevator deflection, and to reduce the elevator effectiveness.
Date:
April 22, 1948
Creator:
Dods, Jules B., Jr.
System:
The UNT Digital Library
The Aerodynamic Effects of Rockets and Fuel Tanks Mounted Under the Swept-Back Wing of an Airplane Model
From Summary: "The effects of externally mounted rockets and fuel tanks on the aerodynamic characteristics of an airplane model with a swept-back wing are presented in this report."
Date:
April 23, 1948
Creator:
Boddy, Lee E. & Morrill, Charles P., Jr.
System:
The UNT Digital Library
Drag Measurements of a Swept-Back Wing Having Inverse Taper as Determined by Flight Tests at Supersonic Speeds
Report discussing the results of flight tests to determine the drag at zero lift of a swept-back wing of inverse taper using an NACA 65-009 airfoil. The data was compared to untapered wings with a similar degree of sweepback. The tapered wing was found to have a lower drag coefficient than the 34-degree swept-back untapered wing but a higher drag coefficient than the 45-degree swept-back untapered wing.
Date:
April 8, 1947
Creator:
Alexander, Sidney R.
System:
The UNT Digital Library
Effects of Compressibility on the Characteristics of Five Airfoils
Report presenting the results of pressure-distribution tests to determine the effects of compressibility on the characteristics of the NACA 66,2-215, 66,2-015, 65(216)-418, 16-212, and 23015 airfoil sections. Schileren photographs of the air flow and data on the wake characteristics was also obtained.
Date:
April 25, 1947
Creator:
Daley, Bernard N.
System:
The UNT Digital Library
Canopy loads investigation for the F6F-3 airplane
Report presenting an investigation of surface static pressures over the outer and inner surfaces of the cockpit canopies on the Grumman F6F-3, Curtiss SB2C-4E, and Grumman F8F-1 airplanes in the full-scale tunnel. Results regarding the external pressure distribution and internal static pressure are provided.
Date:
April 14, 1947
Creator:
Cocke, Bennie W., Jr. & Czarnecki, K. R.
System:
The UNT Digital Library
Aerodynamic characteristics of a wing with quarter-chord line swept back 35 degrees, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section: Transonic-bump method
From Introduction: "This paper presents the results of the investigation of wing-alone and wing-fuselage combinations employing a wing with the quarter-chord line swept back 35^o, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section."
Date:
April 21, 1949
Creator:
Sleeman, William C., Jr. & Becht, Robert E.
System:
The UNT Digital Library
Investigations of an Annular Diffuser-Fan Combination Handling Rotating Flow
Memorandum presenting an investigation of two annular diffusers of different conical angles of expansion but constant outer diameters with rotating flow behind a fan. The performance characteristics are determined and the rotational-kinetic-energy effects on the overall energy transformation are observed over a range of inlet mach numbers from 0.1 to 0.44 and angles of flow up to 28 degrees.
Date:
April 25, 1949
Creator:
Schwartz, Ira R.
System:
The UNT Digital Library
Relation of Nozzle-Blade and Turbine-Bucket Temperatures to Gas Temperatures in a Turbojet Engine
Memorandum presenting an investigation conducted to determine experimentally turbine-nozzle-blade and turbine-bucket temperatures in a turbojet engine and to correlate these temperatures with the gas temperatures. Data were obtained over the normal range of engine speeds and with two tail-pipe-nozzle areas. Results regarding basic data, turbine-nozzle-blade temperature distribution, turbine-bucket-temperature distribution, temperature distribution of gas at burner-outlet, turbine-bucket temperatures during starting, and relation of material and gas temperatures are provided.
Date:
April 30, 1948
Creator:
Farmer, J. Elmo
System:
The UNT Digital Library
Measurements of the wing and tail loads during the acceptance tests of Bell XS-1 research airplane
Report presenting flight measurements obtained during acceptance tests conducted by the Bell Aircraft Corporation on the XS-1 research airplane. The primary focus was on the aerodynamic loads, handling qualities, maximum lift, and buffet boundaries of the airplane.
Date:
April 13, 1948
Creator:
Beeler, De E. & Mayer, John P.
System:
The UNT Digital Library
Analytical investigation of distribution of centrifugal stresses and their relation to limiting operating temperatures in gas-turbine blades
From Introduction: "Analyses that provide a basis for comparing the centrifugal-stress distributions inherent in jet-engine turbine blades of several designs currently in use were therefore made and are presented."
Date:
April 12, 1948
Creator:
Kemp, Richard H. & Morgan, William C.
System:
The UNT Digital Library
High-Speed Stability and Control Characteristics of a Fighter Airplane Model with a Swept-Back Wing and Tail
Memorandum presenting wind-tunnel tests conducted to determine the high-speed stability and control characteristics of an airplane model with a sweptback wing and tail. The aerodynamic coefficients and the longitudinal- and lateral-control characteristics of the plain wing-fuselage-tail combination are included. Results regarding lift, drag, and pitching moment, longitudinal characteristics, lateral characteristics, wing leading-edge slate, and fuselage-side dive brakes are provided.
Date:
April 14, 1948
Creator:
Morrill, Charles P., Jr. & Boddy, Lee E.
System:
The UNT Digital Library
Pressure recovery at supersonic speeds through annular duct inlets situated in a region of appreciable boundary layer 1: addition of energy to the boundary layer
Report presenting a model with a nozzle upstream of an annular duct inlet for the purpose of ejecting high-velocity air into the boundary layer of the flow along the forebody tested between Mach numbers of 1.36 and 2.01. Results wind-tunnel data, equivalent pressure recovery, and scale effects are provided.
Date:
April 1, 1948
Creator:
Davis, Wallace F. & Brajnikoff, George B.
System:
The UNT Digital Library
Empirical mode constants for calculating frequencies of axial-flow compressor blades
The vibration characteristics of a group of axial-flow compressor blades of similar geometry were investigated. Empirical-mode constants were determined for the first three bending and torsional modes. A comparison of experimentally determined frequencies of a second group of blades with frequencies computed using these mode constants showed that the computed values were correct within 10 percent. The approximate limiting ratios of depth to chord and length to chord below which these constants could not be used to compute the natural frequencies were also found experimentally.
Date:
April 23, 1948
Creator:
Millenson, M. B. & Wilterdink, P. I.
System:
The UNT Digital Library
Experimental investigation of thrust augmentation of 4000-pound-thrust axial-flow-type turbojet engine by interstage injection of water-alcohol mixtures in compressor
Report presenting an experimental investigation of thrust augmentation of a 4000-pound-thrust axial-flow-type turbojet engine by interstage injection of water-alcohol mixtures into the compressor at sea-level, zero-ram conditions. the number, size, and arrangement of interstage nozzles were varied to produce a satisfactory augmentation system of minimum complication. Results regarding the unaugmented performance with and without interstage-injection nozzles, augmented performance with three-stage system, augmented performance with other injection systems, temperature surveys, and engine operation are provided.
Date:
April 6, 1950
Creator:
Povolny, John H.; Useller, James W. & Chelko, Louis J.
System:
The UNT Digital Library
Investigation to determine contraction ratio for supersonic-compressor rotor
Report presenting a method for applying the limited contraction ratio to obtain the maximum allowable blade thickness of a two-dimensional model of a supersonic-compressor rotor.
Date:
April 30, 1948
Creator:
Wright, Linwood C.
System:
The UNT Digital Library