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Flying qualities of a high-performance personal-owner airplane

Description: Report presenting an investigation to measure the flying qualities of a high-performance personal-owner airplane to investigate the possible causes of instrument flying accidents with that type of aircraft. Testing indicated that the lack of aerodynamic stall warning and rapid roll-off at the stall could contribute to stall-spin accidents with high-performance personal-owner aircraft. Results regarding the handling qualities and the control under instrument flying conditions are provided.
Date: November 8, 1951
Creator: Adams, James J. & Whitten, James B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Drag Measurements of a Swept-Back Wing Having Inverse Taper as Determined by Flight Tests at Supersonic Speeds

Description: 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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Pumping Characteristics for Several Simulated Variable-Geometry Ejectors With Hot and Cold Primary Flow

Description: Report presenting an investigation of the pumping characteristics of eight conical ejectors mounted on a fuselage portion of a supersonic airplane. The diameter ratio, spacing ratio, nozzle pressure, and ejector weight flows were varied. Results regarding the ejector pumping characteristics, comparison with previous results, comparison of data for cold and hot primary flow, and ejector air-supply requirements are provided.
Date: September 8, 1954
Creator: Allen, John L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Pumping Characteristics for Several Simulated Variablegeometry Ejectors With Hot and Cold Primary Flow

Description: Report presenting an investigation of the pumping characteristics of eight conical ejectors mounted on a scale fuselage portion of a supersonic airplane. The configurations simulated various positions of a two-position nozzle with a fixed shroud and double-iris exit. Results regarding ejector pumping characteristics, comparison with previous results, comparison of data for cold and hot primary flow, and ejector air-supply requirements are provided.
Date: September 8, 1954
Creator: Allen, John L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Lateral Stability and Control Measurements of a 0.0858-Scale Model of the Lockheed XF-104 Airplane at Transonic Speeds

Description: An investigation of the lateral stability and control effectiveness of a 0.0858-scale model of the Lockheed XF-104 airplane has been conducted in the Langley 16-foot transonic tunnel. The model has a low aspect ratio, 3.4-percent-thick wing with negative dihedral. The horizontal tail is located on top of the vertical tail. The investigation was made through a Mach number range of 0.80 to 1.06 at sideslip angles of -5 deg. to 5 deg. and angles of attack from 0 deg. to 16 deg. The control effecti… more
Date: June 8, 1955
Creator: Arabian, Donald D. & Schmeer, James W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimental investigation of thrust augmentation of axial-flow-type 4000-pound-thrust turbojet engine by water and alcohol injection at compressor inlet

Description: 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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Preliminary Investigation at Mach Number 1.91 of a Diffuser Employing a Pivoted Cone to Improve Operation at Angle of Attack

Description: Report presenting an investigation to determine the performance of a conical-nose supersonic diffuser at angle of attack. The inlet had a pivoting cone which could be oriented to any of several angles independent of the angle of attack of the diffuser. Results regarding total-pressure recovery and mass-flow characteristics, cowl lip position, cone position relative to angle of attack, shadowgraphs, and contour maps are provided.
Date: December 8, 1953
Creator: Beheim, Milton A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Free-Spinning Tunnel Tests of a 1/20-Scale Model of the McDonnell XF3H-1 Airplane : TED No. NACA DE 343

Description: Memorandum presenting an investigation conducted in the 20-foot free-spinning tunnel with a scale model to determine the spin and recovery characteristics of the McDonnell XF3H-1 airplane. The effects of control settings and movements on the erect and inverted spin and recovery characteristics of the model were determined. Results regarding design gross weight loading, variation of loading, spin-recovery parachutes, pilot escape, landing condition, control forces, and recommended recovery techn… more
Date: September 8, 1950
Creator: Berman, Theodore
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Investigation of the Characteristics of an Unswept Wing of Aspect Ratio 4.01 in the Langley 8-Foot High-Speed Tunnel

Description: Report presenting an investigation of the characteristics of a low-aspect-ratio wing at high subsonic Mach numbers in the high-speed tunnel. The wing model had an NACA 65-108 airfoil section, an aspect ratio of 4.01, a taper ratio of 0.498, and no twist or dihedral. Results regarding normal-force characteristics, pitching-moment characteristics, and drag characteristics are provided.
Date: November 8, 1949
Creator: Bielat, Ralph P. & Cahn, Maurice S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Development of Metal-Bonding Adhesive FPL-710 With Improved Heat-Resistant Properties

Description: Report presenting an adhesive, FPL-710, which produces higher strength at temperatures up to 600 degrees Fahrenheit than previously obtained and possesses good resistance to aging at high temperatures. It also has acceptable resistance to creep and immersion in various organic solvents. Results regarding its strength properties, heating and aging resistances, and variables affecting bond strength are provided.
Date: July 8, 1952
Creator: Black, John M. & Blomquist, R. F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Some Effects of Fuselage Interference, Wing Interference, and Sweepback on the Damping in Roll of Untapered Wings as Determined by Techniques Employing Rocket-Propelled Vehicles

Description: Report presenting an experimental investigation utilizing rocket propelled vehicles in free flight to determine some effects of fuselage interference, wing interference, and sweepback on the damping-in-roll characteristics of untapered wings with an aspect ratio of 3.7 and NACA 65A009 airfoil sections between a range of Mach numbers.
Date: October 8, 1951
Creator: Bland, William M., Jr. & Dietz, Albert E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Altitude operational characteristics of a prototype model of the J47D (RX1-1 and RX1-3) turbojet engines with integrated electronic control

Description: Report presenting an investigation of the altitude operational characteristics of a prototype model of the J47D turbojet engines, which includes an afterburner, a variable-area exhaust nozzle, and an integrated electronic control in an altitude wind tunnel. Results regarding compressor stall, compressor unstall, combustor blow-out during acceleration, stall and blow-out protection, acceleration characteristics, deceleration characteristics, and altitude starting characteristics, afterburner ope… more
Date: January 8, 1952
Creator: Bloomer, Harry E.; Conrad, E. William & Sobolewski, Adam E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Performance of Basic XJ79-GE-1 Turbojet Engine and Its Components

Description: Memorandum presenting an investigation to determine the performance of the XJ79-GE-1 turbojet engine and its components, while operating as integral parts of the engine, conducted in an altitude test chamber. Data were obtained over a range of Reynolds number indices and for various settings of the variable compressor stators and variable-area exhaust nozzle from fully open to fully closed positions. Results regarding the component performance and engine performance are provided.
Date: May 8, 1958
Creator: Campbell, Carl E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of internal configuration on afterburner shell temperatures

Description: From Summary: "A brief investigation was conducted in the altitude wind tunnel to determine the extent to which the afterburner shell cooling problem could be alleviated by internal configuration changes. Data were obtained with and without a cooling liner installed and for variations in the radial fuel distribution and in the radial distribution in flame-seat area. Consideration is given to the effects on both shell temperature and afterburner performance."
Date: January 8, 1952
Creator: Conrad, E. William & Jansen, Emmert T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Altitude performance and operational characteristics of 29-inch-diameter tail-pipe burner with several fuel systems and flame holders on J35 turbojet engine

Description: From Summary: "An investigation of turbojet-engine thrust augmentation by means of tail-pipe burning has been conducted in the NACA Lewis altitude wind tunnel. Several fuel systems and flame holders were investigated in a 29-inch-diameter tail-pipe burner to determine the effect of fuel distribution and flame-holder design on tail-pipe-burner performance and operational characteristics over a range of simulated flight conditions. At an altitude of 5000 feet, the type of flame holder used had on… more
Date: November 8, 1949
Creator: Conrad, E. William & Prince, William R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Altitude Performance of AN-F-58 Fuels in British Rolls-Royce Nene Single Combustor

Description: "An investigation was conducted with a single combustor from a British Rolls-Royce Nene turbojet engine to determine the altitude performance characteristics of AN-F-58 fuels. Three fuel blends conforming to AN-F-58 specifications were prepared in order to determine the influence of fuel boiling temperatures and aromatic content on combustion efficiencies and altitude operational limits. The performance of the three AN-F-58 fuels was compared in the range of altitudes from sea level to 65,000 f… more
Date: July 8, 1949
Creator: Cook, William P. & Koch, Richard G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Exploratory Investigation of the Effect of Wing Slots and Leading-Edge Slats on the Longitudinal Stability Characteristics of a 45 Degree Sweptback Wing-Fuselage Configuration

Description: Report presenting an exploratory investigation to determine the effects of wing slots on the longitudinal stability characteristics of a 45 degree sweptback wing-fuselage combination. Results regarding pitching-moment characteristics and lift and drag characteristics are provided.
Date: February 8, 1957
Creator: Critzos, Chris C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Longitudinal Stability and Control Characteristics of a Canard Missile Configuration for Mach Numbers From 1.1 to 1.93 as Determined From Free-Flight and Wind-Tunnel Investigation

Description: Report presenting a study of the supersonic longitudinal stability and control characteristics of a canard missile configuration using flight tests and wind-tunnel tests at a range of Mach numbers and Reynolds numbers. Good correlation was noted for the two techniques for slopes of lift and moment coefficients against angle of attack and for aerodynamic-center location.
Date: August 8, 1952
Creator: Curfman, Howard J., Jr. & Grigsby, Carl E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Free-Flight Experience of the Lateral Stability Characteristics at Low Lift of a 45 Degree Swept-Wing Rocket-Propelled Model Equipped With a Nonlinear Yaw-Rate Damper System at Mach Numbers From 0.76 to 1.73

Description: Report discussing a low-lift lateral stability investigation with a rocket-propelled model of a 45 degree swept-wing-airplane configuration equipped with an auxiliary yaw-rate damper system at a range of Mach numbers. Results indicated that the system was nonlinear due to a large dead spot in the system. The primary effect of the system was to increase the damping of lateral oscillations.
Date: February 8, 1957
Creator: D'Aiutolo, Charles T.; Willoughby, William W. & Coltrane, Lucille C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight and Test-Stand Investigation of High-Performance Fuels in Pratt & Whitney R-1830-94 Engines 4: Comparison of Cooling Characteristics of Flight and Test-Stand Engines

Description: "The cooling characteristics of three R-1830-94 engines, two of which were mounted in a test stand and the other in a B-24D airplane, were investigated and the results were compared. The flight tests were made at a pressure altitude of 7000 feet; the test-stand runs were made at ground-level atmospheric conditions. Three cooling runs were made for each engine: variable cooling-air pressure drop, variable carburetor-air flow, and variable fuel-air ratio" (p. 1).
Date: October 8, 1946
Creator: Dandois, Marcel & Werner, Milton
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of Fuel Temperature and Fuel Distribution on the Combustion Efficiency of a 16-Inch Ram-Jet Engine at a Simulated Mach Number of 2.9

Description: Report presenting the effect of preinjection-fuel temperature on vaporization rates and combustion efficiency of a 16-inch ram-jet engine for two different fuels. Variation of the location of the fuel injectors and use of control sleeves were also explored.
Date: January 8, 1953
Creator: Dangle, E. E.; Cervenka, A. J. & Bahr, D. W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Tests of Aerodynamically Heated Multiweb Wing Structures in a Free Jet at Mach Number 2: Four Aluminum-Alloy Models of 20-Inch Chord and Span With 0.064-Inch-Thick Skin, 0.025-Inch-Thick Ribs and Webs, and Zero, One, Two, or Three Chordwise Ribs

Description: Report presenting testing of four multiweb wing models were tested at Mach number 2 in a free jet to investigate structural effects of aerodynamic heating and loading. All of the models were the same except for the number of chordwise internal stiffening ribs; each had zero, one, two, or three. Results regarding laboratory vibration tests, jet tests, model behavior, temperatures, stresses, and discussion of failure are provided.
Date: May 8, 1958
Creator: Davidson, John R.; Rosecrans, Richard & Vosteen, Louis F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Low-Speed Investigation of a 0.16-Scale Model of the X-3 Airplane: Longitudinal Characteristics

Description: Report presenting a wind-tunnel investigation of the low-speed static longitudinal characteristics of a model of the X-3 airplane with the wing flaps neutral and deflected. Results regarding those characteristics with the flaps neutral, with the flaps fully deflected, in the presence of a ground plane, with the flaps partially deflected, and effect of miscellaneous changes of the model are provided.
Date: September 8, 1950
Creator: Delany, Noel K. & Hayter, Nora-Lee F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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