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An experimental study of five annular air inlet configurations at subsonic and transonic speeds
Report presenting an investigation of an NACA 1-80-100 nose inlet fitted alternately with an elliptical, a parabolic, a 14 degree-inch conical, and a 22 degree-inch conical central body at subsonic and transonic speeds in the 8-foot transonic tunnel. Drag, surface-pressure, and pressure-recovery measurements were obtained at 0 degrees angle of attack through a range of Mach numbers. Results regarding tunnel boundary interference, surface-pressure distribution, external drag, pressure recovery, and propulsive thrust comparison are provided.
Date:
August 19, 1953
Creator:
Pendley, Robert E.; Milillo, Joseph R.; Fleming, Frank F. & Bryan, Carroll R.
System:
The UNT Digital Library
Free Flight Investigation at Transonic Speeds of the Power-on Characteristics Including Some Effects of Sonic Propulsive Jets of a Four Engine Delta Wing Configuration
Report discussing a model of a delta-wing configuration with four engines mounted two to a nacelle below the wing that was tested a variety of Mach numbers and Reynolds numbers. The wing static-pressure coefficients, wing pressure coefficients, and lift coefficient of different configurations are described.
Date:
August 16, 1957
Creator:
Falanga, Ralph A. & Judd, Joseph H.
System:
The UNT Digital Library
Altitude chamber evaluation of an aircraft liquid hydrogen fuel system used with a turbojet engine
From Introduction: "The objective of this report are (1) to describe the complete fuel system, (2) to discuss the procedure used for transitions between JP-4 fuel and hydrogen, and (3) to present and discuss engine performance obtained with both fuels, and (4) to review the reliability of the fuel system."
Date:
August 19, 1957
Creator:
Braithwaite, Willis M.; Fenn, David B. & Algranti, Joseph S.
System:
The UNT Digital Library
Design and performance of flight-type liquid-hydrogen heat exchanger
Report presenting an investigation of a liquid-hydrogen fuel system developed to operate one of the turbojet engines in a twin-engine light bomber at an altitude of 50,000 feet and Mach number 0.75. The heat exchanger was evaluated in an altitude test chamber in conjunction with the complete aircraft fuel system. Results regarding calculated heat-exchanger performance, experimental heat-exchanger performance, and reliability are provided.
Date:
August 19, 1957
Creator:
Fenn, David B.; Braithwaite, Willis M. & Ordin, Paul M.
System:
The UNT Digital Library
Design and Performance of Fuel Control for Aircraft Hydrogen Fuel System
Memorandum presenting the system analysis, design, and performance of a control system for an experimental flight-type hydrogen fuel system. The fuel system was designed to investigate some of the problems associated with the utilization of hydrogen as an aircraft fuel. Speed control of the engine was obtained by coupling the hydrogen regulator to the JP-4 fuel control.
Date:
August 19, 1957
Creator:
Otto, Edward W.; Hiller, Kirby W. & Ross, Phil S.
System:
The UNT Digital Library
Flight Investigation of a Liquid Hydrogen Fuel System
Memorandum presenting testing of a twin-engine light bomber modified to utilize hydrogen fuel in one of the two engines during flight at an altitude of 50,000 feet. Three completely successful flights were made using hydrogen fuel. Data are presented to show the effect of tank agitation on fuel pressure and fuel losses.
Date:
August 19, 1957
Creator:
Mulholland, Donald R.; Acker, Loren W.; Christenson, Harold H. & Gough, William V.
System:
The UNT Digital Library
An experimental investigation of the unsteady lift induced on a wing in the downwash field of an oscillating canard control surface
Report presenting the results of an experimental investigation of the unsteady lift induced on a wing in the downwash field of an oscillating canard control surface. The results indicated that existing theories provide a reliable guide for the estimation of the magnitude of the lift derivatives and centers of pressure at low values of reduced frequency and low angles of attack.
Date:
August 15, 1955
Creator:
Reese, David E., Jr.
System:
The UNT Digital Library
Investigation of some wake vortex characteristics of an inclined ogive-cylinder body at Mach number 1.98
Report presenting measurements of the pitot-pressure distributions in the flow field, pressure distributions over the body, and downwash distributions through shed vortices for an inclined body of revolution at a free-stream Mach number of 1.98. Results regarding the experimental pressure distributions and vortex positions, vortex strengths computed from experiment, comparisons of theoretical and experimental vortex paths, and comparisons of theoretical and experimental downwash distributions through the body vortices are provided.
Date:
August 23, 1955
Creator:
Jorgensen, Leland H. & Perkins, Edward W.
System:
The UNT Digital Library
Investigation of Equilibrium Temperatures and Average Laminar Heat-Transfer Coefficients for the Front Half of Swept Circular Cylinders at a Mach Number of 6.9
Report presenting the average heat-transfer coefficients and equilibrium temperatures for the front half of an isothermal cylinder with a laminar boundary layer as determined by wind tunnel testing at Mach number 6.9 and a range of Reynolds numbers and sweep angles.
Date:
August 18, 1955
Creator:
Feller, William V.
System:
The UNT Digital Library
Preliminary performance data of several tail-pipe-cascade-type model thrust reversers
Report presenting the reverse-thrust performance of several tail-pipe-cascade-type model thrust reversers over a range of exhaust-nozzle pressure ratios from 1.2 to 2.4. Both symmetrical and asymmetrical cascade blade shapes were investigated. Results regarding the performance of tail-pipe-cascade-type model thrust reversers having symmetrically shaped cascade blades and the performance of tail-pipe-cascade-type model thrust reversers having asymmetrically shaped cascade blades are provided.
Date:
August 29, 1955
Creator:
Henzel, James G., Jr. & McArdle, Jack G.
System:
The UNT Digital Library
Theoretical Investigation of Laminar Heat Transfer on Yawed Infinite Cylinders in Supersonic Flow and a Comparison With Experimental Data
Report presenting a theoretical method for calculating heat transfer in the laminar boundary layer on yawed infinite cylinders in compressible flow. The method can be applied to a cylinder of arbitrary cross section and arbitrary chordwise wall-temperature distribution. The variation in local heat transfer around the surface of the cylinder was found to have little functional dependence on yaw angle or wall temperature.
Date:
August 9, 1955
Creator:
Beckwith, Ivan E.
System:
The UNT Digital Library
Experimental investigation of a transonic compressor rotor with a 1.5-inch chord length and an aspect ratio of 3.0 2: blade-element performance
Report presenting a transonic compressor rotor with double-circular-arc blade sections, which were designed and tested to investigate the aerodynamic effects of using a short blade chord and a high aspect ratio. The report presents the blade-element performance and performance analysis.
Date:
August 18, 1955
Creator:
Schwenk, Francis C. & Tysl, Edward R.
System:
The UNT Digital Library
Tests of Aerodynamically Heated Multiweb Wing Structures in a Free Jet at Mach Number 2: Two Aluminum-Alloy Models of 20-Inch Chord With 0.064- and 0.081-Inch-Thick Skin
Report presenting testing of two 2024-T3 aluminum-alloy multiweb wing structures (MW-2 and MW-3), similar to airplane or missile wings, at a Mach number of 2 under simulated supersonic flight conditions. Results regarding experimentally determined test conditions, model temperatures, strain-gage results, and model failures are provided. The report indicates that much of the stress data does not agree with expected results, but there is too much uncertainty regarding the reduction of strain data that no conclusions can be made concerning the results.
Date:
August 9, 1955
Creator:
Griffith, George E.; Miltonberger, Georgene H. & Rosecrans, Richard
System:
The UNT Digital Library
A preliminary investigation of static-pressure changes associated with combustion of aluminum borohydride in a supersonic wind tunnel
Report presenting static-pressure changes resulting from steady combustion of aluminum borohydride in a supersonic wind tunnel. Static pressures were measured along the top wall of a tunnel adjacent to the flame that filled the upper portion of the test section. Results regarding the static-pressure increases, effect of change in fuel-injection rate, and effect of tunnel boundary layer on the character of the heat-addition region are provided.
Date:
August 18, 1955
Creator:
Dorsch, Robert G.; Serafini, John S. & Fletcher, Edward A.
System:
The UNT Digital Library
Performance of Inconel 550 Turbine Blades in a Turbojet Engine and Effects of Different Forging Temperatures and Heat Treatments
Report presenting an investigation to determine the effects of forging at 1950 degrees and 2150 degrees Fahrenheit as well as the effects of several heat treatments on the performance of Inconel 550 in a turbojet engine. Differences in engine performance of the different turbine blades could not be associated with consistent differences in microstructure or grain size. Results regarding blade performance, blade elongation during engine operation, microstructure of as-heat-treated blades, grain size, metallurgical studies of failed blades, stress-rupture tests, and hardness are provided.
Date:
August 16, 1955
Creator:
Gyorgak, C. A.; Johnston, J. R. & Weeton, J. W.
System:
The UNT Digital Library
Flight Measurements of the Lateral Response Characteristics of the Convair XF-92A Delta-Wing Airplane
Memorandum presenting rudder pulse maneuvers obtained with the Convair XF-92A delta-wing research airplane at an altitude of about 30,000 feet over a Mach number range of 0.52 to 0.92. Tests were made with and without a wing fence. By analyzing the maneuvers, the characteristics of the airplane transient, airplane stability derivatives, and frequency-response characteristics were measured.
Date:
August 5, 1955
Creator:
Holleman, Euclid C.
System:
The UNT Digital Library
Performance of a short combustor at high altitudes using hydrogen fuel
Performance characteristics of a 16-inch annular-type combustor installed in a full-scale engine using gaseous-hydrogen fuel were obtained at simulated altitudes from 66,000 to 86,000 feet at a flight Mach number of 0.8. Combustion efficiencies of 86 percent were obtained at 86,000 feet (combustor pressure, 420 lb/sq ft abs). Combustor blowout was not encountered during the investigation.
Date:
August 7, 1956
Creator:
Sivo, Joseph N. & Fenn, David B.
System:
The UNT Digital Library
Aircraft-Fuel-Tank Design for Liquid Hydrogen
"Some of the considerations involved in the design of aircraft fuel tanks for liquid hydrogen are discussed herein. Several of the physical properties of metals and thermal insulators in the temperature range from ambient to liquid-hydrogen temperatures are assembled. Calculations based on these properties indicate that it is possible to build a large-size liquid-hydrogen fuel tank which (1) will weigh less then 15 percent of the fuel weight, (2) will have a hydrogen vaporization rate less than 30 percent of the cruise fuel-flow rate, and (3) can be held in a stand-by condition and readied for flight in a short time" (p. 1).
Date:
August 9, 1955
Creator:
Reynolds, T. W.
System:
The UNT Digital Library
Experimental investigation of methods of improving diffuser-exit total-pressure profiles for side-inlet model at Mach number 3.05
Report presenting an investigation of several methods of straightening diffuser-exit total-pressure profiles produced by a typical half-conical double-shock side inlet at a free stream Mach number of 3.05. The methods included the use of longer subsonic diffusers, constant-area mixing sections at the diffuser exit, internal screens, a rapid acceleration of the flow at the diffuser exit, internal bleed, and a change in internal-flow passage shape obtained by raising the internal centerbody fairing from the floor into the diffuser duct. Each of the methods was found to be effective in reducing distortion.
Date:
August 29, 1955
Creator:
Piercy, Thomas G. & Klann, John L.
System:
The UNT Digital Library
Drag Near Zero Lift of a 1/7-Scale Model of the Convair B-58 External Store as Measured in Free Flight Between Mach Numbers of 0.8 and 2.45
"The zero-lift drag of a 1/7-scale model of the Convair B-58 external store was obtained at mach numbers between 0.8 and 2.45 at corresponding Reynolds numbers per foot of 3.5 x 10 to the 6th power and 15.3 X 10 to the 6th power. The experimental drag data are compared with calculated values at both subsonic and supersonic speeds and show good agreement. In addition to the drag data, some static stability derivatives and damping factors were also obtained and are presented with the predicted values of these derivatives for completeness and for comparison" (p. 1).
Date:
August 3, 1955
Creator:
Hopko, Russell N.
System:
The UNT Digital Library
Investigation of impulse-type supersonic compressor with hub-tip ratio of 0.6 and turning to axial direction 2: stage performance with three different sets of stators
Report presenting an impulse-type supersonic compressor designed for turning to the axial direction that was tested in air with three different sets of stator blades at eight angle settings.
Date:
August 16, 1955
Creator:
Wilcox, Ward W.
System:
The UNT Digital Library
Experimental study of shock-positioning method of ram-jet-engine control
Report presenting an investigation of ram-jet-engine control by shock positioning on a 16-inch fixed-geometry ram jet at a range of free-stream Mach numbers. The control method appears to offer adequate control of ram-jet-engine operation. Results regarding the steady-state performance, effect of control settings on response and stability, effect of disturbance size and Mach number on response to fuel-flow disturbances, Mach number disturbances, angle-of-attack disturbances, exhaust-area disturbances, and recovery from subcritical engine operation are provided.
Date:
August 29, 1955
Creator:
Hurrell, Herbert G.; Vasu, George & Dunbar, William R.
System:
The UNT Digital Library
Static Longitudinal and Lateral Stability and Control Characteristics of an Airplane Configuration Having a Wing of Trapezoidal Plan Form With Various Tail Airfoil Sections and Tail Arrangements at a Mach Number of 6.86
Memorandum presenting an investigation carried out in the 11-inch hypersonic tunnel to determine the static longitudinal and lateral stability and control characteristics of an airplane configuration with a trapezoidal wing with a modified hexagonal airfoil section and equipped with various tail airfoil sections and tail arrangements. The tests were made at Mach number 6.86 and Reynolds number 343,000 based on the wing mean aerodynamic chord.
Date:
August 15, 1955
Creator:
Penland, Jim A.; Fetterman, David E., Jr. & Ridyard, Herbert W.
System:
The UNT Digital Library
A method for evaluating the loads and controllability aspects of the pitch-up problem
Report presenting a procedure for estimating the range of peak airplane load factors and maneuvering tail loads likely to be experienced in pitch-up maneuvers. Results of computations indicated that though the load factors and maneuvering tail loads were not critical in pitch-up maneuvers at 35,000 feet, they were likely to exceed design levels at 15,200 feet.
Date:
August 23, 1955
Creator:
Sadoff, Melvin; Matteson, Frederick H. & Havill, C. Dewey
System:
The UNT Digital Library