Resource Type
Collection
Serial/Series Title
Country
States
166 Matching Results
Results open in a new window/tab.
Results:
1 - 24 of
166
next
Analysis of Limitations Imposed on One-Spool Turbojet-Engine Designs by Turbines Having Downstream Stators at 0, 2.0, and 2.8 Flight Mach Numbers
Memorandum presenting an aerodynamic design-point analysis of one-spool turbojet engines with one-stage turbines with one and with two rows of downstream stator blades. The object of the analysis was to evaluate the design characteristics of the turbines in comparison with conventional one- and two-stage turbines, to determine the extent to which exit whirl can be increased before causing weight-flow capacity to decrease, and to determine the effect of downstream stators on engine design limitations.
Date:
January 19, 1955
Creator:
Cavicchi, Richard H. & Constantine, Anita B.
Object Type:
Report
System:
The UNT Digital Library
Experimental Investigation of a Body Flare for Obtaining Pitch Stability and a Body Flap for Obtaining Pitch Control in Hypersonic Flight
Memorandum presenting the effectiveness of a body flare as a pitch-stabilizing device and a body flap as a pitch-control device investigated experimentally at Mach numbers from 3.00 to 6.25. The basic test body was rotationally symmetric and consisted of a fineness ratio 3 nose followed by a fineness ratio 9 afterbody. Results regarding the stability of the flared body, effect of body flap on lift and drag, trim conditions, flow visualization studies, and comparison of theory and experiment are provided.
Date:
January 18, 1955
Creator:
Eggers, A. J., Jr. & Syvertson, Clarence A.
Object Type:
Report
System:
The UNT Digital Library
Investigation of Porous Gas-Heated Leading-Edge Section for Icing Protection of a Delta Wing
"A tip section of a delta wing having an NACA 0004-65 airfoil section and a 600 leading-edge sweepback was equipped with a porous leading-edge section through which hot gas was bled for anti-icing. Heating rates for anti-icing were determined for a wide range of icing conditions. The effects of gas flow through the porous leading-edge section on airfoil pressure distribution and drag in dry air were investigated" (p. 1).
Date:
January 19, 1955
Creator:
Bowden, Dean T.
Object Type:
Report
System:
The UNT Digital Library
A Fibrous-Glass Compact as a Permeable Material for Boundary-Layer-Control Applications Using Area Suction
"Measurements were made of the resistance of fibrous-glass compacts to normal air flow. The flow resistance was related to the thickness and density. As a porous material for boundary-layer-control applications using area suction, the fibrous-glass compact could be made to any desired thickness and permeability and sandwiched between perforated rigid surfaces" (p. 1).
Date:
January 1955
Creator:
Dannenberg, Robert E.; Weiberg, James A. & Gambucci, Bruno J.
Object Type:
Report
System:
The UNT Digital Library
A Heated-Wire Liquid-Water-Content Instrument and Results of Initial Flight Tests in Icing Conditions
Memorandum presenting an investigation of a flight version of the NACA heated-wire liquid-water-content instrument, which was constructed and flight tested in natural icing conditions. Data obtained simultaneously with rotting multicylinders indicated that reliable flight measurements of liquid-water content could be made with the heated-wire instrument.
Date:
January 20, 1955
Creator:
Neel, Carr B.
Object Type:
Report
System:
The UNT Digital Library
An Investigation of the Longitudinal Stability Characteristics of Three Specialized Store Configurations at Transonic Speeds
Report presenting testing to determine the longitudinal stability characteristics of the TX-17, the "Short Seven", and the TX-21 special weapons. Dynamic and static stability data are provided for a range of Mach numbers and stagnation-pressure levels.
Date:
January 14, 1955
Creator:
Braden, John A.
Object Type:
Report
System:
The UNT Digital Library
Flight Characteristics of a Wingless Rocket- Powered Model With Four Externally Mounted Air-to-Air Missiles at Mach Numbers 0.7 to 1.6
Report presenting a flight investigation of four air-to-air missiles mounted by pylons on a rocket-powered basic wingless buffet-research vehicle to determine the trim, buffet, and drag characteristics of the combination.
Date:
January 25, 1955
Creator:
Henning, Allen B. & Brown, Clarence A., Jr.
Object Type:
Report
System:
The UNT Digital Library
A Note on the Drag Due to Lift of Rectangular Wings of Low Aspect Ratio
Note presenting some methods of estimating the induced drag of low-aspect-ratio wings, which are discussed and compared with experiments. The profile drag due to lift is also discussed and a method is developed which relates the effect of aspect ratio on the profile drag due to lift to an "effective" two-dimensional lift coefficient.
Date:
January 1955
Creator:
Polhamus, Edward C.
Object Type:
Report
System:
The UNT Digital Library
Some Considerations on Two-Dimensional Thin Airfoils Deforming in Supersonic Flow
"The aerodynamic characteristics of indicially cambered two-dimensional airfoils in supersonic flow are determined theoretically. These indicial functions are used to determine the power required to sustain a general time-varying chordwise deformation. The harmonically oscillating parabolic mode is considered in detail and stability boundaries are presented for this case" (p. 1).
Date:
January 1955
Creator:
Migotsky, Eugene
Object Type:
Report
System:
The UNT Digital Library
Use of Nonlinearities to Compensate for the Effects of a Rate-Limited Servo on the Response of an Automatically Controlled Aircraft
Report presenting a simple method for determining the nonlinear gains required to give optimum responses for step inputs of all magnitudes. The method is based on the fact that the control surface moves at its maximum rate during almost the entire transient maneuver and thus the servo system can be considered as a simple on-off type controller.
Date:
January 1955
Creator:
Schmidt, Stanley F. & Triplett, William C.
Object Type:
Report
System:
The UNT Digital Library
On the Small-Disturbance Iteration Method for the Flow of a Compressible Fluid With Application to a Parabolic Cylinder
Note presenting the assumptions of the Prandtl-Busemann small-disturbance method, together with the requirements of continuity and irrotationality, which lead to a recursive system of first-order partial-differential equations. The results of the analysis are applied to the case of subsonic flow past a parabolic cylinder.
Date:
January 1955
Creator:
Kaplan, Carl
Object Type:
Report
System:
The UNT Digital Library
A fibrous-glass compact as a permeable material for boundary-layer control applications using area suction
"Measurements were made of the resistance of fibrous-glass compacts to normal air flow. The flow resistance was related to the thickness and density. As a porous material for boundary-layer-control applications using area suction, the fibrous-glass compact could be made to any desired thickness and permeability and sandwiched between perforated rigid surfaces" (p. 1).
Date:
January 1955
Creator:
Dannenberg, Robert E.; Weiberg, James A. & Gambucci, Bruno J.
Object Type:
Report
System:
The UNT Digital Library
Charts for Estimating Performance of High-Performance Helicopters
Note presenting theoretically derived charts showing the profile-drag-thrust ratio for a helicopter rotor operating in forward flight and with hinged rectangular blades with a linear twist of -8 degrees. The charts, which show the profile-drag characteristics of the rotor for various combinations of pitch angle, ratio of thrust coefficient to solidity, and a parameter representing shaft power input, are presented for tip-speed ratios ranging from 0.05 to 0.50.
Date:
January 1955
Creator:
Gessow, Alfred & Tapscott, Robert J.
Object Type:
Report
System:
The UNT Digital Library
Study of the momentum distribution of turbulent boundary layers in adverse pressure gradients
Report presenting the evaluation and analysis of the mean and turbulent terms of the equations of motion and the stress tensor at four stations in a turbulent boundary layer with a progressively increasing adverse pressure gradient. Report presenting mean flow parameters, summary of velocity measurements, evaluation of wall shearing stress, shear stress distribution across boundary layer, and stress tensor are provided.
Date:
January 1955
Creator:
Sandborn, Virgil A. & Slogar, Raymond J.
Object Type:
Report
System:
The UNT Digital Library
Experimental evaluation of momentum terms in turbulent pipe flow
Report presenting an experimental evaluation of the mean and turbulent momentum terms in fully developed turbulent pipe flow. The terms of the longitudinal-direction momentum equation, obtained from the Reynolds equations of turbulent fluid motion, were experimentally evaluated in a 4-inch-diameter pipe from total- and static-pressure data and hot-wire anemometer surveys.
Date:
January 1955
Creator:
Sandborn, Virgil A.
Object Type:
Report
System:
The UNT Digital Library
Description and Analysis of a Rocket-Vehicle Experiment on Flutter Involving Wing Deformation and Body Motions
Report presenting flight testing and a mathematical analysis to demonstrate and confirm a type of subsonic flutter involving rigid-body motions and wing deformations. The period of oscillation was approximately 100 chords per cycle, which is well within the range of period found in dynamic-stability work on rigid aircraft with free controls. Results regarding the Rayleigh-Ritz treatment in four degrees of freedom, effect of various binary and ternary combinations of freedoms, and effect of relative positions of wing and missile center of gravity are provided.
Date:
January 1955
Creator:
Cunningham, H. J. & Lundstrom, R. R.
Object Type:
Report
System:
The UNT Digital Library
Prediction of losses induced by angle of attack in cascades of sharp-nosed blades for incompressible and subsonic compressible flow
Report presenting a method of computing the losses in total pressure caused by a non-zero angle of attack at the inlet to a row of sharp-nosed blades for both incompressible and subsonic compressible flow. The method is based on momentum considerations across a row of zero-thickness flat plates and assumes that the blade force is normal to the plate surface.
Date:
January 1955
Creator:
Kramer, James J. & Stanitz, John D.
Object Type:
Report
System:
The UNT Digital Library
Method for rapid graphical evaluation of cooled or uncooled turbojet and turboprop engine or component performance (effects of variable specific heat included)
Report presenting a series of curves that have been prepared to simplifying and accelerate calculation procedures for component or overall cycle performance of gas-turbine engines. The curves are based on the thermodynamic properties of air and combustion gases for a hydrogen-combustion ratio of 0.167.
Date:
January 1955
Creator:
Esgar, Jack B. & Ziemer, Robert R.
Object Type:
Report
System:
The UNT Digital Library
Investigation of temperature limitation of various lubricants for high-temperature 20-millimeter-bore ball bearings
Report presenting lubrication studies of bearings lubricated with liquids and solids in a bearing test rig under conditions of minimum lubricant flow. Six liquid lubricants were investigated, including two petroleums and four synthetics. Results regarding bearings with silver-plated beryllium copper cages, bearings with cast Inconel cages, and an analysis of experimental results are provided.
Date:
January 1955
Creator:
Nemeth, Z. N. & Anderson, W. J.
Object Type:
Report
System:
The UNT Digital Library
Analysis of Laminar Forced-Convection Heat Transfer in Entrance Region of Flat Rectangular Ducts
From Introduction: "Beyond the position where the boundary layer treatment can no longer be used, curves have been faired to connect the Nusselt number results of the present analysis with those of reference 3, in which a parabolic velocity profile is assumed throughout the entire duct length. So that a comparison could be made with the results of reference 3, the boundary layer analysis was used to study the development of the temperature profile associated with a parabolic velocity profile throughout."
Date:
January 1955
Creator:
Sparrow, E. M.
Object Type:
Report
System:
The UNT Digital Library
Effect of lag of sidewash on the vertical-tail contribution to oscillatory damping in yaw of airplane models
Report presenting tests of two models for which the rate of change of sidewash with angle of sideslip could be varied. Both models were tested in steady-yawing flow and by the freely damped oscillation-in-yaw technique to establish the effect of the lag of the sidewash on the unsteady lateral damping of the models. Results regarding the model with auxiliary fins and model with wings in various vertical positions are provided.
Date:
January 1955
Creator:
Fisher, Lewis R. & Fletcher, Herman S.
Object Type:
Report
System:
The UNT Digital Library
The Linearized Equations of Motion Underlying the Dynamic Stability of Aircraft, Spinning Projectiles, and Symmetrical Missiles
Note presenting linearized equations of motions which are derived for both conventional aircraft having mirror symmetry and spinning projectiles or missiles with rotational and mirror symmetry. The equations for aircraft are compared with those for missiles and shortcomings in the currently accepted theories are pointed out. The dynamic-stability requirements for spin-stabilized projectiles are discussed briefly.
Date:
January 1955
Creator:
Charters, A. C.
Object Type:
Report
System:
The UNT Digital Library
Effective Moment of Inertia of Fluid in Offset, Inclined, and Swept-Wing Tanks Undergoing Pitching Oscillations
Report presenting fluid-dynamics studies of simplified model fuel tanks mounted on a mechanism that simulated a wing undergoing torsional oscillations. The tanks were mounted in several configurations and the effective moment of inertia of the fluid was determined experimentally. Results regarding the effect of frequency, pylon-mounted tanks, centrally mounted tanks, and effect of a diffused baffle on the damping factor are provided.
Date:
January 1955
Creator:
Reese, James R. & Sewall, John L.
Object Type:
Report
System:
The UNT Digital Library
Prediction of Downwash Behind Swept-Wing Airplanes at Subsonic Speed
Report presenting a rapid method for estimating the downwash behind swept-wing airplanes. The agreement with available experimental data taken behind airplane models is good. Results regarding the comparison with experiment and a comparison of the downwash due to a flat sheet and that due to a rolling-up vortex sheet are provided.
Date:
January 1955
Creator:
DeYoung, John & Barling, Walter H., Jr.
Object Type:
Report
System:
The UNT Digital Library