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Experimental Investigation of Various Wing-Mounted External Stores on a Wing-Fuselage Combination Having a Sweptback Wing of Inverse Taper Ratio
Report presenting an investigation in the high speed tunnel to determine the effects of several wing-mounted external-store configurations on the aerodynamic characteristics of a model of a swept wing-fuselage combination for a range of Mach numbers. Some of the configurations explored included inboard underwing installations and wing-tip installations. Results regarding lift-drag ratios, drag characteristics, lift-curve slope, and pitching-moment characteristics are provided.
Date:
September 15, 1950
Creator:
Spreemann, Kenneth P. & Silvers, H. Norman
System:
The UNT Digital Library
Altitude-Wind-Tunnel Investigation of Turbine Performance in J47 Turbojet Engine
From Introduction: "Performance data are presented in this report to show the characteristics of the turbine operating as an integral part of the engine. Typical results are graphically presented to show the effects of changes in altitude, flight Mach number, and exhaust-nozzle-outlet area on turbine performance. All turbine-performance data obtained are given in tabular form."
Date:
September 21, 1950
Creator:
Thorman, H. Carl & McAulay, John E.
System:
The UNT Digital Library
Aerodynamic characteristics of a wing with quarter-chord line swept back 60 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 the wing-alone and wing-fuelage configurations employing a wing with the quarter-chord line swept back 60^o, aspect ratio 4, taper ratio 0.6, and an NACA 65A006 airfoil section parallel to the free stream."
Date:
September 6, 1949
Creator:
King, Thomas J., Jr. & Myers, Boyd C., II
System:
The UNT Digital Library
Design and Experimental Performance of a 0.35 Hub-Tip Radius Ratio Transonic Axial-Flow-Compressor Rotor Designed for 40 Pounds Per Second Per Unit Frontal Area
Memorandum presenting an investigation to determine the feasibility of a high-performance transonic axial-flow compressor stage with a weight flow of 40 pounds per second per square foot of frontal area. A transonic axial-flow inlet stage with a hub-tip ratio of 0.35 and an axial Mach number of approximately 0.75 was designed and fabricated. Results regarding overall rotor performance, flow parameters, radial matching of blade-element sections, and comparison of blade-element parameters with design rules are provided.
Date:
September 4, 1958
Creator:
Montgomery, John C. & Yasaki, Paul T.
System:
The UNT Digital Library
Altitude-chamber performance of British Rolls-Royce Nene II engine 1: standard 18.75-inch-diameter jet nozzle
Report presenting an altitude-chamber investigation to determine the altitude performance characteristics of the British Rolls-Royce Nene II turbojet engine with a standard 18.75-inch-diameter jet nozzle. Results regarding the simulated flight performance and generalized performance across other altitude and pressure characteristics are provided.
Date:
September 23, 1949
Creator:
Barson, Zelmar & Wilsted, H. D.
System:
The UNT Digital Library
Flow studies in the asymmetric adjustable nozzle of the Ames 6-by 6-foot supersonic wind tunnel
Report presenting surveys of the flow of the asymmetric adjustable nozzle of the 6- by 6-foot supersonic wind tunnel, which were made to determine the uniformity of the air stream. Test techniques for minimizing the effects of stream irregularities and the results of force and pressure-distribution tests of a swept-wing model are presented to illustrate the effectiveness of these techniques.
Date:
September 15, 1949
Creator:
Frick, Charles W. & Olson, Robert N.
System:
The UNT Digital Library
Aerodynamic Characteristics of an Airfoil-Forebody Swept Flying-Boat Hull With a Wing and Tail Swept Back 51.3 Degrees at the Leading Edge
Report discussing an investigation of the aerodynamic characteristics of an airfoil-forebody swept flying boat hull with a wing and tail swept back 51.3 degrees at the leading edge. The swept hull's minimum drag coefficient was about the same as the parent model or streamline model. Various combinations of flaps were also utilized.
Date:
September 9, 1949
Creator:
Naeseth, Rodger L. & MacLeod, Richard G.
System:
The UNT Digital Library
Investigation of Extensible Wing-Tip Ailerons on an Untapered Semispan Wing at 0 Degree and 45 Degrees Sweepback
Report presenting a low-speed wind-tunnel investigation to determine the lateral control characteristics of extensible wing-tip ailerons on an untapered semispan wing with two configurations; one was unswept and had an aspect ratio of 3.13 and the other was swept back 45 degrees and had an aspect ratio of 1.59. Results regarding the plain-wing aerodynamic characteristics and lateral control characteristics are provided.
Date:
September 20, 1949
Creator:
Hagerman, John R. & O'Hare, William M.
System:
The UNT Digital Library
Wind-Tunnel Investigation at Low Speeds of the Pitching Derivatives of Untapered Swept Wings
Report presenting a wing-tunnel investigation in straight and pitching flow to determine the effects of independently varying aspect ratio and angle of sweep on the longitudinal rotary stability characteristics of a series of ten untapered wings. The investigation showed that an interdependent relationship existed between the effects of aspect ratio and sweep. Results regarding pitching moment due to pitching velocity and lift due to pitching velocity are provided.
Date:
September 29, 1948
Creator:
MacLachlan, Robert & Fisher, Lewis R.
System:
The UNT Digital Library
Performance investigation of can-type combustor 1: instrumentation, altitude operational limits and combustion efficiency
Report presenting an investigation of the performance of a single can-type combustor designed for a turbojet engine equipped with an 11-stage axial-flow compressor and a single-stage turbine. The investigation was conducted to determine the altitude operational limits of the engine for two fuels, combustion efficiencies at various simulated conditions of altitude and engine speed, combustor-outlet temperature distribution for several altitudes at constant engine speed, and combustor total-pressure drop.
Date:
September 16, 1948
Creator:
Cook, William P. & Zettle, Eugene V.
System:
The UNT Digital Library
Preliminary Investigation of Various Ailerons on a 42 Degree Sweptback Wing for Lateral Control at Transonic Speeds
Report presenting an investigation at transonic speeds in the high speed tunnel to determine the rolling-effectiveness characteristics of several aileron arrangements for use on a 42 degree sweptback wing. Results regarding the rolling-moment coefficients, variation of coefficient with Mach number, outboard cusp aileron, and use of the leading-edge flaps are provided.
Date:
September 7, 1948
Creator:
Turner, Thomas R.; Lockwood, Vernard E. & Vogler, Raymond D.
System:
The UNT Digital Library
Tests of a triangular wing of aspect ratio 2 in the Ames 12-foot pressure wind tunnel 2: the effectiveness and hinge moments of a constant-chord plain flap
Report presenting a semispan triangular wing with a constant-chord trailing-edge flap to evaluate the aerodynamic characteristics of the wing with landing speeds up to a Mach number of 0.95. Tests were included to ascertain the effects of the addition of a body and of modifications to the airfoil section. Results regarding the wing alone with low Mach number, wing alone with high Mach number, effect of the body, effect of the flap, effect of Mach number, lift-drag ratio, and wing-profile modifications are provided.
Date:
September 21, 1948
Creator:
Stephenson, Jack D. & Amuedo, Arthur R.
System:
The UNT Digital Library
Investigation of Flow Conditions and the Nature of the Wall-Constriction Effect Near and at Choking by Means of the Hydraulic Analogy
Report presenting an investigation of the closed wind-tunnel phenomenon of choking and the wall-constriction effects in the subsonic Mach number range where supersonic Mach numbers appear using the hydraulic analogy. Application of the results to wind tunnel testing, the subsonic choking phenomena, and effects of the walls are described.
Date:
September 1, 1948
Creator:
Matthews, Clarence W. & Wright, Ray H.
System:
The UNT Digital Library
A theoretical lateral-stability analysis of XC-120 airplane
"A theoretical lateral-stability analysis of the XC-120 airplane, equipped with a detachable fuselage, was made to determine the effect on the lateral stability of the high angle of wing incidence for which the airplane was designed. The results of the investigation indicated that the lateral stability of the airplane is satisfactory with or without the detachable fuselage installed" (p. 1).
Date:
September 17, 1948
Creator:
Sternfield, Leonard & Gates, Ordway B., Jr.
System:
The UNT Digital Library
High-Speed Aerodynamic Characteristics of a Lateral-Control Model 1: NACA 0012-64 Section with 20-Percent-Chord Plain Aileron and 0 Degree and 45 Degrees Sweepback
Memorandum describing wind-tunnel tests made to determine the aerodynamic characteristics of a 20-percent-chord plain aileron on a semispan wing with the NACA 0012-64 section. The report includes the results of tests of the wing unswept and swept back 45 degrees and with the aileron deflected from 0 to 10 degrees.
Date:
September 27, 1948
Creator:
Anderson, Joseph L. & Krumm, Walter J.
System:
The UNT Digital Library
Investigation of Performance of Single-Stage Axial-Flow Compressor Using NACA 5509-34 Blade Section
Memorandum presenting an investigation conducted to study the performance of a single-stage axial-flow compressor using blades with an NACA 5509-34 airfoil section. Static- and total-pressure, total-temperature, and flow-angle surveys were taken in the compressor inlet and outlet and between blade rows to study the overall performance and individual blade-row performance.
Date:
September 30, 1948
Creator:
Mankuta, Harry & Guentert, Donald C.
System:
The UNT Digital Library
Effect of High-Lift Devices on the Low-Speed Static Lateral and Yawing Stability Characteristics of an Untapered 45 Degrees Sweptback Wing
Memorandum presenting a wind-tunnel investigation made in the stability tunnel to determine the effects of lift flaps on the static lateral stability derivatives and the yawing derivatives of an untapered 45 degree sweptback wing at low speeds. Results regarding straight flow and yawing characteristics are provided.
Date:
September 30, 1948
Creator:
Lichtenstein, Jacob H.
System:
The UNT Digital Library
Notes on the Application of Airfoil Studies to Helicopter Rotor Design
Report presenting a discussion of a number of the problems that most frequently arise with airfoils on helicopters. A reference list of published reports on airfoil section characteristics which are useful in regards to these helicopter problems is also included.
Date:
September 22, 1948
Creator:
Gustafson, F. B.
System:
The UNT Digital Library
Investigation of Internal Regenerative Fuel-Heating System for 20-Inch Ram Jet
Memorandum presenting an investigation conducted to evaluate the effectiveness of a simple internal regenerative fuel preheater for a 20-inch-diameter ram jet. Data obtained at subsonic sea-level conditions indicated that fuel could be successfully preheated in this manner.
Date:
September 1, 1949
Creator:
Baker, Sol & Perchonok, Eugene
System:
The UNT Digital Library
Free-flight performance of 16-inch-diameter supersonic ram-jet units 1: four units designed for combustion-chamber-inlet Mach number of 0.12 at free-stream Mach number of 1.6 (units A-2, A-3, A-4, and A-5)
Report presenting free-flight investigations conducted on four 16-inch-diameter ramjet units to determine the performance at high subsonic and supersonic velocities. Data for evaluating the performance were obtained from radio-telemetering and radar-tracking equipment. Results regarding combustion performance, diffuser total-pressure recovery, thrust coefficient, and external drag coefficient are provided.
Date:
September 22, 1949
Creator:
Carlton, William W. & Messing, Wesley E.
System:
The UNT Digital Library
A comparison of the experimental subsonic pressure distributions about several bodies of revolution with pressure distributions computed by means of the linearized theory
Report presenting an analysis of the effects of compressibility on the pressure coefficients of several bodies of revolution by comparing experimentally determined pressure coefficients with corresponding pressure coefficients calculated by the use of linearized equations of compressible flow. The results indicated that the theoretical methods predict the subsonic pressure-coefficient changes over the central portion of the body but do not predict the pressure-coefficient changes near the nose.
Date:
September 12, 1949
Creator:
Matthews, Clarence W.
System:
The UNT Digital Library
Tests of Lifting Surfaces on Conical and Cylindrical Portions of a Body at Subsonic Mach Numbers and at a Mach Number of 1.2
Report presenting testing of low-aspect-ratio triangular-plan-form lifting surfaces located on conical and cylindrical portions of a body have been determined at Mach number 1.2 and several subsonic speeds to determine if the aerodynamic characteristics of these surfaces at supersonic speeds could be improved by locating them in the subsonic conical-flow field. Results regarding lift and drag coefficients and lift-curve slopes are provided.
Date:
September 2, 1949
Creator:
Osborne, Robert S. & Wright, John B.
System:
The UNT Digital Library
Preliminary analysis of axial-flow compressors having supersonic velocity at the entrance of the stator
Report presenting a supersonic compressor design with supersonic velocity at the entrance of the stator on the assumption of two-dimensional flow. The rotor and stator losses assumed in the analysis are based on the results of preliminary supersonic cascade tests. The starting conditions and stability of the flow in rotor and stator are discussed, and the desirability of the variable-geometry stators and adjustable guide vanes is indicated.
Date:
September 12, 1949
Creator:
Ferri, Antonio
System:
The UNT Digital Library
Analytical and Experimental Investigation of 90 Degrees Supersonic Turning Passages Suitable for Supersonic Compressors or Turbines
"Four 90 degree two-dimensional turning passages designed by the method of characteristics were tested at an inlet Mach number of 1.71. The measured losses varied from 5 to 15 percent of the inlet stagnation pressure. The smallest loss was obtained for a passage in which separation on the convex surface was minimized through the introduction of a favorable pressure gradient" (p. 1).
Date:
September 12, 1949
Creator:
Liccini, Luke L.
System:
The UNT Digital Library