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Wind-Tunnel Investigation of the Drag and Lateral-Stability Characteristics of a 1/22-Scale Model of a Bomber Airplane Employing a Low-Aspect-Ratio Triangular Wing
Report presenting the results of an investigation of cross-sectional-area distribution, nacelle configuration, and landing-gear-fairing configuration on the minimum drag characteristics of a model of a four-engine bomber airplane with a low-aspect-ratio triangular wing. The lateral stability characteristics are also included.
Date:
July 8, 1953
Creator:
Phelps, E. Ray
System:
The UNT Digital Library
Comparative Study of Turbofan and Turbojet Engines
Report presents a comparison of turbofan and turbojet engines for Mach numbers of up to 3.0 and conventional hydrocarbon fuels. There are four parts of the report: a cycle analysis of turbofan engines and information about their designs, a comparison of several commercial engines proposed for the Air Force, component performance and development problems for turbofan and turbojet engines, and a summary and conclusions based on mission studies.
Date:
July 19, 1957
Creator:
Kaufman, Harold R.; Benser, William A. & Gabriel, David S.
System:
The UNT Digital Library
Transonic Flutter Characteristics of a Cambered A-Plan-Form Wing With and Without Simulated Nacelles
Report presenting an experimental investigation to determine the effects of simulated engine nacelles on the flutter characteristics of a cambered A-plan-form wing with 45 degree sweepback of the leading edge, an aspect ratio of 3.6, and a taper ratio of 0.14. Results regarding a wing-mount fixed and a model with wing mount free are provided.
Date:
July 10, 1957
Creator:
Kelly, H. Neale
System:
The UNT Digital Library
Handbook of Structural Stability Part 2: Buckling of Composite Elements
"The local buckling of stiffener sections and the buckling of plates with sturdy stiffeners are reviewed, and the results are summarized in charts and tables. Numerical values of buckling coefficients are presented for longitudinally compressed stiffener sections of various shapes, for stiffened plates located in longitudinal compression and in shear, and for stiffened cylinders loaded in torsion. Although the data presented consist primarily of elastic-buckling coefficients, the effects of plasticity are discussed for a few special cases" (p. 1).
Date:
July 1957
Creator:
Becker, Herbert
System:
The UNT Digital Library
A Body Modification to Reduce Drag Due to Wedge Angle of Wing with Unswept Trailing Edge
From Summary: "Ward's slender-body-theory formula for zero-lift drag contains three integrals plus a base-drag term. Two of these integral terms depend only upon the cross-sectional area distribution of the body. The third integral term depends only upon the body shape and axial slopes at the base of the body. This term is neglected in the transonic area rule because in many cases it is zero; however, there are also many cases in which it is not zero. This paper examines the term for the possibility of drag reduction for a particular case."
Date:
July 1958
Creator:
Pitts, William C. & Nielsen, Jack Norman
System:
The UNT Digital Library
Skin frictional resistance of plane surfaces in air: Abstract of recent German tests, with notes
Given here is the most recent research on skin frictional resistance of plane surfaces in air that was conducted by Dr. Wieselsberger under the direction of Dr. Prandtl of Gottingen University. In all, 16 models were tested. These were divided into four groups, as follows: 1) cloth, in the original condition; 2) cloth, with the nap singed off; 3) cloth, with three coats of dope; and 4) cloth, with six coats of dope. Each group consisted of four models of uniform width, 1 meter, and of lengths of 0.5, 1.0, 1.5, and 2.0 meters.
Date:
July 1922
Creator:
Diehl, W. S.
System:
The UNT Digital Library
Notes on Aerodynamic Forces I: Rectilinear Motion
"The study of the motion of perfect fluids is of paramount importance for the understanding of the chief phenomena occurring in the air surrounding an aircraft, and for the numerical determination of their effects. The author recently successfully employed some simple methods for the investigation of the flow of a perfect fluid that have never been mentioned in connection with aeronautical problems. These methods appeal particularly to the engineer who is untrained in performing laborious mathematical computations, as they do away with these and allow one to obtain many interesting results by the mere application of some general and well-known principles of mechanics" (p. 1-2).
Date:
July 1922
Creator:
Munk, Max M.
System:
The UNT Digital Library
Notes on Aerodynamic Forces 2: Curvilinear Motion
"The laws of curvilinear motion are established and the transverse forces on elongated airship hulls along a curved path are investigated" (p. 1).
Date:
July 1922
Creator:
Munk, Max M.
System:
The UNT Digital Library
Notes on Aerodynamic Forces 3: The Aerodynamic Forces on Airships
"The results of the two preceding notes are applied to airships and checked with wind tunnel tests" (p. 1).
Date:
July 1922
Creator:
Munk, Max M.
System:
The UNT Digital Library
Notes on the N.A.C.A. Control Force Recorder
Emphasized here is the desirability of using recording instruments in the investigation of the characteristics of airplanes with particular reference to the National Advisory Committee for Aeronautics (NACA) control force recorder. Given here are photographs, records, and a description of the instrument developed by NACA for investigations on different types of aircraft. Described here is an instrument for recording control forces.
Date:
July 1923
Creator:
Reid, H. J. E.
System:
The UNT Digital Library
Theory of the ideal windmill
Report presenting the theory of the ideal propeller, which is important for solving the problem of the action of propellers. Several different theories of propeller action are described and compared to determine which ones seem to be the most accurate.
Date:
July 1921
Creator:
Hoff, Wilhelm
System:
The UNT Digital Library
Some Tables of the Factor of Apparent Additional Mass
"This note, prepared for publication by the National Advisory Committee for Aeronautics, is a collection of the tables of the factor of apparent mass that have been published up to now. The theory of the motion of solids in a perfect fluid is of the greatest value for the study of most aerodynamic problems, and the additional apparent mass of an immersed solid is the most important characteristic for such theoretical numerical computations. It will therefore be helpful to have the most important values of the apparent mass - for some elementary cases - collected in a convenient form" (p. 1).
Date:
July 1924
Creator:
Munk, Max M.
System:
The UNT Digital Library
Effects of sweepback on boundary layer and separation
"Following the law of stress adopted in the Navier-Stokes equations, the configuration of the viscous flow in planes at right angles to the axis of an infinite cylinder is found to be independent of the axial motion of the cylinder. In the limiting case of a yawed or swept wing of very high aspect ratio, certain boundary-layer and separation phenomena are thus determined independently by the crosswise component of velocity" (p. 1).
Date:
July 1947
Creator:
Jones, Robert T.
System:
The UNT Digital Library
Tank tests to determine the effect of varying design parameters of planing-tail hulls 2: effect of varying depth of step, angle of after- body keel, length of afterbody chine, and gross load
From Summary: "The second part of a series of tests made in Langley tank no. 2 to determine the effect of varying design parameters of planing-tail hulls is presented. Results are given to show the effects on resistance characteristics of varying angle of afterbody keel, depth of step, and length of afterbody chine. The effect of varying the gross load is shown for one configuration. The resistance characteristics of planing-tail hulls are compared with those of a conventional flying-boat hull. The forces on the forebody and afterbody of one configuration are compared with the forces on a conventional hull."
Date:
July 1946
Creator:
Dawson, John R.; McKann, Robert & Hay, Elizabeth S.
System:
The UNT Digital Library
Zero-Lift Drag of the Chance Vought Regulus II Missile at Mach Numbers Between 0.8 and 2.2 as Determined From the Flight Tests of Two 0.12-Scale Models
Report discussing testing of two models of the Chance Vought Regulus II missile to determine its drag characteristics for a range of Mach numbers. The measured total-drag-coefficient data was extrapolated to external-drag-coefficient data and presented.
Date:
July 15, 1954
Creator:
Church, James D.
System:
The UNT Digital Library
Investigation of a 0.6 Hub-Tip Radius-Ratio Transonic Turbine Designed for Secondary-Flow Study 2 - Design and Experimental Performance of Turbine With Low-Velocity-Turning Stator and Standard Rotor
Memorandum presenting a low-velocity-turning stator designed to reduce secondary-flow loss cores by turning the flow at low velocities and accelerating it in passages of constant flow angle with reduced cross-channel pressure gradients. Performance of the stator was determined with static-pressure measurements and detailed surveys of total pressure and flow angle made with the turbine operating at design speed near design work.
Date:
July 18, 1957
Creator:
Rohlik, Harold E.; Wintucky, William T. & Scibbe, Herbert W.
System:
The UNT Digital Library
Local Heat Transfer to Blunt Noses at High Supersonic Speeds
Memorandum presenting a brief summary of the recent theoretical and experimental work on local heat-transfer rates on blunt-nose bodies. Results regarding the calculation of local flow conditions, prediction of stagnation-point heating rates, and calculation of heating rates over entire nose are provided.
Date:
July 12, 1957
Creator:
Stoney, William E., Jr.
System:
The UNT Digital Library
Wind-Tunnel Experiments Concerning the Dynamic Behavior of a Low-Speed Slowly Spinning Fin-Stabilized Rocket
Report presenting an investigation to determine the effectiveness of studying the dynamic characteristics of a low-speed slowly spinning fin-stabilized rocket with a free-oscillation technique and to study certain types of behavior that have been observed in this type of missile. Results regarding the stability of the original model, the effect of reversing direction of arming propeller, the effect of increasing the size of the reversed-rotation arming propeller, the effect of removing the arming propeller, the effect of adding a spoiler nose ring to a basic model, and the effect of changes in the spin rate are provided.
Date:
July 6, 1954
Creator:
Bird, John D. & Lichtenstein, Jacob H.
System:
The UNT Digital Library
Performance of Multiple Jet-Exit Installations
Memorandum presenting the results of recent exploratory investigations of the performance of clustered jet-exit installations at Mach numbers from 0.60 to 3.05. Data presented in this report were obtained with tunnel-wall-mounted models with cold-air-jet exhaust. Results regarding base pressures, effect of boattailing, effect of afterbody-nozzle geometry, and terminal fairings are provided.
Date:
July 7, 1958
Creator:
Swihart, John M. & Nelson, William J.
System:
The UNT Digital Library
Some Factors Affecting the Static Longitudinal and Directional Stability Characteristics of Supersonic Aircraft Configurations
Memorandum presenting a survey of the problems introduced by the increased longitudinal stability and reduced directional stability of aircraft operating in the low supersonic speed range. Information regarding longitudinal stability and directional stability are provided.
Date:
July 12, 1957
Creator:
Spearman, M. Leroy
System:
The UNT Digital Library
Aerodynamic Loads on Tails at High Angles of Attack and Sideslip
"Results are presented for the loads and moments acting on the individual tail surfaces of a body-tail combination over a wide range of angles of attack and sideslip. The effects of forebody length and panel-panel interference on the characteristics are included. It is shown that large nonlinear variations in these loads and moments, which occur at some combinations of angle of attack and sideslip, cannot be predicted by low-angle theory" (p. 1).
Date:
July 23, 1957
Creator:
Spahr, J. Richard & Polhamus, Edward C.
System:
The UNT Digital Library
Tests With Hydrogen Fuel in a Simulated Afterburner
Report presenting an investigation in a 16-inch-diameter simulated afterburner using gaseous hydrogen fuel. Results regarding combustion efficiency, afterburner pressure losses, spontaneous ignition, and a heat-balance check are provided.
Date:
July 2, 1956
Creator:
Kerslake, W. R. & Dangle, E. E.
System:
The UNT Digital Library
Hydrodynamic Characteristics of a Model of a Proposed Six-Engine Hull-Type Seaplane Designed for Supersonic Flight
Memorandum presenting an investigation of the hydrodynamic characteristics of a six-engine hull-type seaplane designed for supersonic flight. The configuration had four engines mounted on top of the wing in individual nacelles and two engines mounted on top of the aft section of the hull with their inlets located on top of the wing.
Date:
July 14, 1958
Creator:
Coffee, Claude W., Jr.
System:
The UNT Digital Library
Flutter Experiments With Various Control Configurations
Report discussing the flutter characteristics of several control-surface configurations, including a wing with tip ailerons, an all-movable stabilizer, vertical tails with trailing-edge rudders, a t-tail, and some simple models of all-movable controls. Some trends of the configurations and suggestions for improving the flutter characteristics are provided.
Date:
July 10, 1957
Creator:
Boswinkle, Robert W., Jr. & Morgan, Homer G.
System:
The UNT Digital Library