Theoretical Characteristics of Two-Dimensional Supersonic Control Surfaces (open access)

Theoretical Characteristics of Two-Dimensional Supersonic Control Surfaces

Report presenting aerodynamic characteristics of uncambered symmetrical parabolic and double-wedge airfoils with leading-edge and trailing-edge flaps using the Busemann second-order-approximation theory. Characteristics presented include aileron effectiveness factor, rate of change of hinge-moment coefficient with aileron deflection, rate of change of the pitching-moment coefficient, and the location of the center of pressure of the airfoil-aileron combination.
Date: July 27, 1948
Creator: Morrissette, Robert R. & Oborny, Lester F.
System: The UNT Digital Library
Theoretical analysis of the motions of an aircraft stabilized in roll by a displacement-response, flicker-type automatic pilot (open access)

Theoretical analysis of the motions of an aircraft stabilized in roll by a displacement-response, flicker-type automatic pilot

Report presenting a general analysis that allows the rolling motions of an aircraft using a displacement-response, flicker-type automatic pilot to be determined. The system is not ideal for many stabilization problems due to inherent residual oscillations, but it offers a simple and economical solution in situations in which steady state oscillations are not a problem. Results regarding some general remarks, transient and steady states, stabilization boundaries, amplitude equations, and period equations are provided.
Date: July 7, 1948
Creator: Curfman, Howard J., Jr. & Gardner, William N.
System: The UNT Digital Library
Notes on Geared Tabs at Supersonic Speeds (open access)

Notes on Geared Tabs at Supersonic Speeds

Memorandum presenting an analysis of the two-dimensional, geared, trailing-edge flap-tab combination at supersonic speeds to determine if the combination could be used to reduce the hinge moments to extremely small values while retaining a large part of the lift effectiveness of a plain flap with the same ratio of flap chord to wing chord.
Date: July 8, 1948
Creator: Tucker, Warren A.
System: The UNT Digital Library
Wind-Tunnel Investigation of a Wing-Fuselage Combination With External Stores (open access)

Wind-Tunnel Investigation of a Wing-Fuselage Combination With External Stores

Report presenting an investigation of a basic wing-fuselage combination with several types of external-store installations meant to delay the advent of airplane buffet caused by external stores. Modifications for airplane design in order to minimize the effect of drag are provided. Some of the arrangements tested included the tandem-mounted arrangement, flush-mounted arrangement, store with a fan-shaped tail, and auxiliary airfoil arrangement.
Date: July 9, 1948
Creator: Silvers, H. Norman & Spreemann, Kenneth P.
System: The UNT Digital Library
Experimental investigation of thrust augmentation of axial-flow-type 4000-pound-thrust turbojet engine by water and alcohol injection at compressor inlet (open access)

Experimental investigation of thrust augmentation of axial-flow-type 4000-pound-thrust turbojet engine by water and alcohol injection at compressor inlet

Report presenting an experimental investigation of thrust augmentation of an axial-flow-type turbojet engine with a 4000-pound-thrust rating using a water-alcohol injection at the compressor inlet at sea-level conditions and zero ram. Three injection systems were investigated in order to obtain satisfactory atomization and distribution of the injected liquids. Results regarding engine performance and engine operation are provided.
Date: July 8, 1948
Creator: Baron, Burnett; Dowman, Harry W. & Dackis, William C.
System: The UNT Digital Library
High-Speed Wind-Tunnel Tests of a 1/16-Scale Model of the D-558 Research Airplane: Longitudinal Stability and Control of the D-558-1 (open access)

High-Speed Wind-Tunnel Tests of a 1/16-Scale Model of the D-558 Research Airplane: Longitudinal Stability and Control of the D-558-1

Report presenting the results of pitching-moment and lift measurements on a model of the D-558-1 airplane with no nose-inlet flow at several tail and elevator settings at a range of Mach numbers. Information about the stability, control, and downwash results is provided.
Date: July 8, 1948
Creator: Wright, John B.
System: The UNT Digital Library
Flight Test of NACA FR-1-B, a Low-Acceleration Rocket-Propelled Vehicle for Transonic Flutter Research (open access)

Flight Test of NACA FR-1-B, a Low-Acceleration Rocket-Propelled Vehicle for Transonic Flutter Research

Report presenting testing of a low-acceleration transonic flutter test vehicle to obtain flutter data on two similar sweptback wings which indicated that wing flutter was symmetrical in mode. Results regarding flight and flutter characteristics for the FR-1-B are provided.
Date: July 20, 1948
Creator: Angle, Ellwyn E.; Clevenson, Sherman A. & Lundstrom, Reginald R.
System: The UNT Digital Library
Longitudinal Stability and Control Characteristics of a Semispan Airplane Model With a Sweptback Wing and Tail From Tests at Transonic Speeds by the NACA Wing-Flow Method (open access)

Longitudinal Stability and Control Characteristics of a Semispan Airplane Model With a Sweptback Wing and Tail From Tests at Transonic Speeds by the NACA Wing-Flow Method

Report presenting an investigation using the NACA wing-flow method to determine the longitudinal stability and control characteristics at transonic speeds of a semispan airplane with a 45 degree sweptback wing and tail. Measurements of the lift and angle of attack for trim were made for several stabilizer and elevator settings. Testing was also performed to investigate the effects of transition wires mounted on the wing and tail, the effect of increasing the boundary-layer thickness on the test surface, and the effectiveness of a wing flap with a sweepback of 45 degrees.
Date: July 23, 1948
Creator: Sawyer, Richard H. & Lina, Lindsay J.
System: The UNT Digital Library
Free-Flight-Tunnel Tests of a Target-Seeking Glide-Bomb Model With Flicker Lateral Control (open access)

Free-Flight-Tunnel Tests of a Target-Seeking Glide-Bomb Model With Flicker Lateral Control

Report presenting an investigation of control systems suitable for target-seeking missiles. Testing occurred in the free-flight tunnel of the GB-5 glide bomb equipped with a light-seeker control unit which applied flicker control. Results indicated that good stability could be obtained with the control system, but was somewhat less stable than with a proportional control system.
Date: July 28, 1948
Creator: McKinney, Marion O., Jr. & Drake, Hubert M.
System: The UNT Digital Library
Some effects of gutter flame-holder dimensions on combustion-chamber performance of 20-inch ram jet (open access)

Some effects of gutter flame-holder dimensions on combustion-chamber performance of 20-inch ram jet

Report presenting the operational characteristics of a 20-inch ramjet with four different gutter-grid flame holders and a three-gutter flame holder with an adjustable gutter angle. The flame holders were compared on the basis of operating ranges of fuel-air ratio, combustion-chamber-inlet velocity, and the combustion efficiencies obtainable.
Date: July 30, 1948
Creator: Wilcox, Fred A.; Perchonok, Eugene & Wishnek, George
System: The UNT Digital Library
Some Flight Measurements of Pressure-Distribution and Boundary-Layer Characteristics in the Presence of Shock (open access)

Some Flight Measurements of Pressure-Distribution and Boundary-Layer Characteristics in the Presence of Shock

Memorandum presenting some pressure-distribution and boundary-layer measurements made in flight in the presence of shock on two modifications of the local contour of the wings of a high-speed airplane. Results regarding the pressure distribution, boundary-layer surveys, and effects on test airplane are provided.
Date: July 23, 1948
Creator: Zalovcik, John A. & Luke, Ernest P.
System: The UNT Digital Library
Free-Flight Investigation at Transonic and Supersonic Speeds of a Wing-Aileron Configuration Simulating the D-558-2 Airplane (open access)

Free-Flight Investigation at Transonic and Supersonic Speeds of a Wing-Aileron Configuration Simulating the D-558-2 Airplane

"An investigation of the rolling effectiveness at transonic and supersonic speeds of a wing-aileron configuration simulating the D-558-2 airplane has been made by means of a rocket-propelled test vehicle. The variation of rolling effectiveness with Mach number is similar to that obtained previously for tapered sweptback wings having full-span, 0.2-chord ailerons" (p. 1).
Date: July 21, 1948
Creator: Sandahl, Carl A.
System: The UNT Digital Library
Charts for Determining Preliminary Values of Span-Load, Shear, Bending-Moment, and Accumulated-Torque Distributions of Swept Wings of Various Taper Ratios (open access)

Charts for Determining Preliminary Values of Span-Load, Shear, Bending-Moment, and Accumulated-Torque Distributions of Swept Wings of Various Taper Ratios

Contains charts for use in determining preliminary values of the spanwise-load, shear, bending-moment, and accumulated-torque distributions of swept wings. The charts are based on strip theory and include four aerodynamic-load distributions, two section-moment distributions, and two inertia-load distributions. The taper ratios considered cover the range from 1.0 to 0 and the results are applicable to any angle of sweep.
Date: July 6, 1948
Creator: Wollner, Bertram C.
System: The UNT Digital Library
Investigation of High-Temperature Operation of Liquid-Cooled Gas Turbines 1: Turbine Wheel of Aluminum Alloy, a High-Conductivity Nonstrategic Material (open access)

Investigation of High-Temperature Operation of Liquid-Cooled Gas Turbines 1: Turbine Wheel of Aluminum Alloy, a High-Conductivity Nonstrategic Material

Report presenting an investigation of turbine operating temperatures as affected by liquid cooling, especially if materials of high conductivity are used, at gas temperatures up to 1925 degrees Fahrenheit. Results regarding the statio heat-transfer rig and turbine rig are provided. The investigation showed that nonstrategic material such as aluminum alloy can be used in liquid-cooled turbine wheels at high gas temperatures.
Date: July 22, 1948
Creator: Kottas, Harry & Sheflin, Bob W.
System: The UNT Digital Library
Experimental investigation of hot-gas bleedback for ice protection of turbojet engines 1: nacelle with offset air inlet (open access)

Experimental investigation of hot-gas bleedback for ice protection of turbojet engines 1: nacelle with offset air inlet

Report presenting aerodynamic and icing investigations on a model of a turbojet-engine nacelle in order to provide icing protection for the engine, protective screen, and accessory housing by the introduction of hot gases into the inlet-air stream. Adequate ice protection was afforded when the minimum kinetic temperature in the protective screen was greater than 32 degrees Fahrenheit.
Date: July 9, 1948
Creator: Callaghan, Edmund E.; Ruggeri, Robert S. & Krebs, Richard P.
System: The UNT Digital Library
The NACA 2000-horsepower propeller dynamometer and tests at high speed of an NACA 10-(3)(08)-03 two-blade propeller (open access)

The NACA 2000-horsepower propeller dynamometer and tests at high speed of an NACA 10-(3)(08)-03 two-blade propeller

This paper contains a detailed description of a 2,000-horsepower propeller dynamometer used to make wind-tunnel tests of a two-blade NACA 10-(3)(08)-03 propeller for a range of blade angles from 20 degrees to 55 degrees at airspeeds up to 500 miles per hour. The results of these tests and comparisons with results obtained from a theoretical analysis and from previous tests made in other wind tunnels are presented.
Date: July 20, 1948
Creator: Corson, Blake W., Jr. & Maynard, Julian D.
System: The UNT Digital Library
Performance of several air ejectors with conical mixing sections and small secondary flow rates (open access)

Performance of several air ejectors with conical mixing sections and small secondary flow rates

An investigation of several ejector configurations to determine the ability to handle the air required for engine cooling. The results are limited to investigations of conical-type mixing-section ejectors at ratios of mixing-section minimum diameter to primary-jet-nozzle diameter using unheated air. Results regarding experimental data, generalization of experimental data, spacing for maximum weight-flow ratio, ejector thrust, ejector configurations for constant weight-flow ratio, and selection of ejector design are provided.
Date: July 19, 1948
Creator: Huddleston, S. C.; Wilsted, H. D. & Ellis, C. W.
System: The UNT Digital Library
Longitudinal Stability and Control Characteristics of a Semispan Airplane Model at Transonic Speeds as Obtained by the Transonic-Bump Method (open access)

Longitudinal Stability and Control Characteristics of a Semispan Airplane Model at Transonic Speeds as Obtained by the Transonic-Bump Method

Memorandum presenting an investigation in the high-speed 7- by 10-foot tunnel using the transonic bump method to determine the longitudinal stability and control characteristics of a semispan airplane model at transonic speeds. The results indicated an increase in the maneuvering stability through the transonic range, but regions of instability were indicated by the slope of the curve stabilizer incidence for trim against Mach number at all positions tested.
Date: July 19, 1948
Creator: Weil, Joseph & Spearman, M. Leroy
System: The UNT Digital Library
Effect of Inlet-Air Parameters on Combustion Limit and Flame Length in 8-Inch-Diameter Ram-Jet Combustion Chamber (open access)

Effect of Inlet-Air Parameters on Combustion Limit and Flame Length in 8-Inch-Diameter Ram-Jet Combustion Chamber

Report presenting an investigation with a ram-jet combustion chamber to determine the effect of fuel-air ratio and the inlet-air parameters of pressure, temperature, and velocity on combustion limit, combustion efficiency, and flame length.
Date: July 22, 1948
Creator: Cervenka, A. J. & Miller, R. C.
System: The UNT Digital Library
Measurement Through the Speed of Sound of Static Pressures on the Rear of Unswept and Sweptback Circular Cylinders and on the Rear and Sides of a Wedge by the NACA Wing-Flow Method (open access)

Measurement Through the Speed of Sound of Static Pressures on the Rear of Unswept and Sweptback Circular Cylinders and on the Rear and Sides of a Wedge by the NACA Wing-Flow Method

Report presenting static-pressure measurements made through the speed of sound by the NACA wing-flow method at the back of two unswept circular cylinders and one sweptback cylinder. Static pressures were found to decrease considerably with an increase in Mach number. Information about the length and diameter of the cylinders and how it affects measurements is provided.
Date: July 21, 1948
Creator: Sawyer, Richard H. & Daum, Fred L.
System: The UNT Digital Library
Longitudinal Stability Characteristics of a 42 Degree Sweptback Wing and Tail Combination at a Reynolds Number of 6.8 X 10 (Exp 6) (open access)

Longitudinal Stability Characteristics of a 42 Degree Sweptback Wing and Tail Combination at a Reynolds Number of 6.8 X 10 (Exp 6)

Results of a wind-tunnel investigation at a Reynolds number of 6.8 x 10(exp 6) to determine the static longitudinal stability characteristics of a 42 degree sweptback wing and fuselage combination with a sweptback horizontal tail are provided. Included are the effects of vertical position of fuselage and tail with respect to wing for several combinations of high-lift and staff-control devices. Also included is the effect of a simulated ground.
Date: July 22, 1948
Creator: Spooner, Stanley H. & Martina, Albert P.
System: The UNT Digital Library
An investigation at low speed of a 51.3 degrees sweptback semispan wing with a raked tip and with 16.7-percent-chord ailerons having three spans and three trailing-edge angles (open access)

An investigation at low speed of a 51.3 degrees sweptback semispan wing with a raked tip and with 16.7-percent-chord ailerons having three spans and three trailing-edge angles

Report presenting a wind-tunnel investigation at low speed to determine the aerodynamic characteristics of a 51.3 degree sweptback semispan wing with a raked tip and with 16.7-percent-chord sealed plain ailerons. Lift, drag, pitching-moment, and hinge-moment data were obtained for the wing with transition free and fixed with various spans of aileron deflected as lift flaps. The rolling moment, yawing moment, hinge moment, and aileron seal pressure characteristics were determined for each of the nine possible aileron-span and trailing-edge-angle combinations tested.
Date: July 21, 1948
Creator: Fischel, Jack & Schneiter, Leslie E.
System: The UNT Digital Library
Free-flight investigation of the rolling effectiveness at high subsonic, transonic, and supersonic speeds of leading-edge and trailing-edge ailerons in conjunction with tapered and untapered plan forms (open access)

Free-flight investigation of the rolling effectiveness at high subsonic, transonic, and supersonic speeds of leading-edge and trailing-edge ailerons in conjunction with tapered and untapered plan forms

Report presenting several rectangular and tapered wing configurations with leading-edge and trailing-edge ailerons tested as part of a general investigation of an aerodynamic control at supersonic speeds. Results indicated that the use of the leading-edge aileron alone was ineffective or caused negative control until a high Mach number was attained. Results for the untapered configurations, tapered configurations, and drag measurements are provided.
Date: July 23, 1948
Creator: Strass, H. Kurt
System: The UNT Digital Library
Tests of the NACA 64(Sub 1)-012 and 64(Sub 1)A012 Airfoils at High Subsonic Mach Numbers (open access)

Tests of the NACA 64(Sub 1)-012 and 64(Sub 1)A012 Airfoils at High Subsonic Mach Numbers

Memorandum presenting an investigation on NACA 64(sub 1)-012 and 64(sub 1)A012 airfoils at a range of Mach numbers and low Reynolds numbers, which indicated that the effect of increasing the trailing-edge angle was inappreciable on the Mach number for the normal-force break, to decrease the normal-force-curve slope, to reduce the effects of compressibility, and to decrease the minimum drag coefficient and to increase maximum normal-force to drag ratio.
Date: July 9, 1948
Creator: Lindsey, W. F. & Humphreys, Milton D.
System: The UNT Digital Library