UNT Libraries Government Documents Department - 215 Matching Results

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Cascade Investigation of Cooling Characteristics of a Castfinned Air-Cooled Turbine Blade for Use in a Turboprop Engine

Description: Memorandum presenting an experimental investigation of the cooling characteristics of a small air-cooled turbine blade for use in a turboprop engine in a static cascade facility. Three test blades were studiued at three combustion-gas temperatures. Results regarding gas-flow conditions in cascade test section, correlation of temperature data, and application of correlated data to the typical engine are provided.
Date: June 12, 1957
Creator: Stepka, Francis S.; Richards, Hadley T. & Hickel, Robert O.
Item Type: Refine your search to only Report
open access

Summary of Subsonic-Diffuser Data

Description: Memorandum presenting a review of the subsonic-diffuser data available in the literature, which is then reduced to certain appropriate performance coefficients and presented as functions of the significant geometric and flow variables. Results regarding total-pressure-loss factor, diffuser effectiveness, recovery of diffuser effectiveness in the tailpipe, inlet speed effects, exit flow distributions, boundary-layer control, and effects of distorted inlet velocity distribution are provided.
Date: October 12, 1956
Creator: Henry, John R.; Wood, Charles C. & Wilbur, Stafford W.
Item Type: Refine your search to only Report
open access

Wind-Tunnel Investigation at Subsonic and Supersonic Speeds of a Model of a Tailless Fighter Airplane Employing a Low-Aspect-Ratio Swept-Back Wing-Stability and Control

Description: Memorandum presenting the results of a wind-tunnel investigation of the static stability and control characteristics of a model of a fighter airplane employing a low-aspect-ratio swept-back wing with trailing-edge elevons, a swept-back vertical tail, but no horizontal tail. The results indicated that, for the test conditions at which the investigation was conducted, the model, with elevons undeflected, was longitudinally and directionally stable.
Date: January 12, 1953
Creator: Smith, Willard G.
Item Type: Refine your search to only Report
open access

Free-flight Tests of 45 Deg Swept Wings of Aspect Ratio 3.15 and Taper Ratio 0.54 to Measure Wing Damping of the First Bending Mode and to Investigate the Possibility of Flutter at Transonic Speeds

Description: Free flight tests of 45-deg swept wings of 3.15 aspect ratio and 0.54 taper ratio to measure wing damping and possible transonic flutter.
Date: October 12, 1954
Creator: O'Kelly, Burke R.; Lundstrom, Reginald R. & Lauten, William T., Jr.
Item Type: Refine your search to only Report
open access

Natural Icing of an Axial-Flow Turbojet Engine in Flight for a Single Icing Condition

Description: Memorandum presenting an investigation in natural icing conditions to determine the effect of ice formations on the performance of an axial-flow turbojet engine. A description of the change over time in tail-pipe temperature, engine jet thrust, fuel flow, ice collection, and acceleration qualities are provided.
Date: August 12, 1948
Creator: Acker, Loren W.
Item Type: Refine your search to only Report
open access

Experimental Investigation of Air-Cooled Turbine Blades in Turbojet Engine. 7: Rotor-Blade Fabrication Procedures

Description: "An experimental investigation was conducted to determine the cooling effectiveness of a wide variety of air-cooled turbine-blade configurations. The blades, which were tested in the turbine of a - commercial turbojet engine that was modified for this investigation by replacing two of the original blades with air-cooled blades located diametrically opposite each other, are untwisted, have no aerodynamic taper, and have essentially the same external profile. The cooling-passage configuration is … more
Date: September 12, 1951
Creator: Long, Roger A. & Esgar, Jack B.
Item Type: Refine your search to only Report
open access

A Method for Calculating the Lift and Center of Pressure of Wing-Body-Tail Combinations at Subsonic, Transonic, and Supersonic Speeds

Description: Report presenting a method for calculating the lift and pitching-moment characteristics of circular cylindrical bodies in combination with triangular, rectangular, or trapezoidal wings or tails through the subsonic, transonic, and supersonic speed ranges. A computing table and set of design charts are presented to reduce the calculations to routine operations. Information about lift, center of pressure, effects of wing incidence, and limitations and extensions of the method is provided.
Date: November 12, 1953
Creator: Nielsen, Jack Norman; Kaattari, George E. & Anastasio, Robert F.
Item Type: Refine your search to only Report
open access

Rocket-Powered-Model Investigation of the Effects of Aeroelasticity on the Rolling Effectiveness of an 8.06-Percent-Scale McDonnell F3H-1 Airplane Wing at Mach Numbers From 0.5 to 1.4

Description: Report discussing an investigation to determine the effects of aeroelasticity on the rolling effectiveness of a model of a McDonnell F3H-1 airplane wing. The plane was found to be subject to aeroelastic losses that varied with Mach number and altitude.
Date: April 12, 1954
Creator: English, Roland D.
Item Type: Refine your search to only Report
open access

A Review of NACA Research Through 1954 on Boron Compounds as Fuels for Jet Aircraft (Project Zip)

Description: Report discussing a project to determine a high-energy fuel suitable for turbojet-powered aircraft. Components of the project include thermal and combustion properties, experiments with combustors using boron compounds, evaluation of boron fuels in full-scale turbojets with and without afterburners, and boron fuel use in ramjet flights. The most promising fuel found in the report is pentaborane.
Date: April 12, 1957
Creator: Olson, Walter T.; Breitwieser, Roland & Gibbons, Louis C.
Item Type: Refine your search to only Report
open access

Local Heat Transfer to Blunt Noses at High Supersonic Speeds

Description: 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.
Item Type: Refine your search to only Report
open access

Effect of Several Jet-Engine Air-Inlet Configurations on the Low-Speed Static Longitudinal Stability Characteristics and Quantity Flow of a 1/6-Scale Model of the MX-1764 Airplane

Description: Memorandum presenting an investigation in the 7- by 10-foot tunnel to determine the effect of wing-root leading-edge and scoop-type jet-engine air-inlet configurations on the static longitudinal stability characteristics and the duct-flow characteristics of a scale model of the MX-1764 airplane. The addition of the inlet configurations to the model generally resulted in slight reductions in longitudinal stability and increases of maximum lift coefficient.
Date: January 12, 1954
Creator: Croom, Delwin R.
Item Type: Refine your search to only Report
open access

An Acceleration Schedule Control for Accelerating a Turbojet Engine and Its Use With a Speed Control

Description: Memorandum presenting a study of an acceleration-limiting control on a turbojet engine in order to determine its feasibility as an acceleration control. A proportional-plus-integral type of controller was used in the investigation. Results regarding the one-loop control and two-loop control are provided.
Date: May 12, 1958
Creator: Gerus, Theodore F.; Powers, Albert G. & Heppler, Herbert J.
Item Type: Refine your search to only Report
open access

Some Factors Affecting the Static Longitudinal and Directional Stability Characteristics of Supersonic Aircraft Configurations

Description: 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
Item Type: Refine your search to only Report
open access

In-Flight Gains Realized by Modifying a Twin Side-Inlet Induction System

Description: Memorandum presenting an investigation of the effects of modifying a twin side-inlet duct system on an interceptor airplane as recorded and analyzed over an altitude range from about 25,000 to 51,000 feet throughout the transonic speed range to a Mach number of about 1.2. The modifications consisted primarily of redesigning the inlet lip, increasing the cross-sectional area of the inlet and diffuser, and adding a region of duct contraction ahead of the engine.
Date: December 12, 1957
Creator: Saltzman, Edwin J.
Item Type: Refine your search to only Report
open access

Total-Pressure-Recovery Characteristics of a Model of the McDonnell XF3H-1 Inlets and Forebody in a Free Jet at a Mach Number of 1.55

Description: Report presenting free jet tests of a model of the inlets and forebody of the McDonnell XF3H-1 airplane with the original and two alternate nose shapes. Results regarding the total-pressure recovery after diffusion, maximum mass-flow ratio, inlet total-pressure profile, shadowgraphs, flow variation, and pressure oscillations are provided.
Date: March 12, 1952
Creator: Merlet, Charles F. & Carter, Howard S.
Item Type: Refine your search to only Report
open access

Effects of Some Configuration Changes on Afterburner Combustion Performance

Description: Report presenting an experimental investigation in a simulated afterburner test rig to determine the effects of some configuration variations on afterburner combustion performance. Results regarding the reduced-diameter flameholder, inclined radial-gutter flameholder, tapered-shell afterburner, and turbulence generators are provided.
Date: June 12, 1957
Creator: Nakanishi, Shigeo & King, Charles R.
Item Type: Refine your search to only Report
open access

Preliminary Investigation of a Ceramic Lining for a Combustion Chamber for Gas-Turbine Use

Description: Combustion chamber liners for gas turbines and experimental set-ups were tested for failure. A ceramic-lined test chamber was operated at fuel/air ratios up to 0.050. Thermal-shock evaluation indicated that a ceramic lining, which expands after firing, would crack but would not fall apart during operation. Refractoriness of the lining and the resistance to mechanical shock were adequate. In general, shell temperature reductions of approximately 400 deg F were effected by the use of this lining … more
Date: April 12, 1948
Creator: Woodward, William H. & Bobrowsky, A. R.
Item Type: Refine your search to only Report
open access

Preliminary investigation of spoiler lateral control on a 42 degree sweptback wing at transonic speeds

Description: Investigation at transonic speeds in the high-speed 7- by 10-foot tunnel to determine the rolling-effectiveness characteristics of a spoiler on a double-wedge-type semispan wing with a sweepback angle of 42 degrees. Results regarding the variation of rolling-moment coefficient, spoiler effectiveness, and rolling effectiveness are provided.
Date: August 12, 1947
Creator: Schneiter, Leslie E. & Ziff, Howard L.
Item Type: Refine your search to only Report
open access

Full-Scale Investigation of the Maximum Lift and Flow Characteristics of an Airplane Having Approximately Triangular Plan Form

Description: Report discussing an investigation of the DM-1 glider, which has an approximately triangular plan form, with auxiliary studies of a model of triangular wings. The pitching-moment coefficient, drag coefficient, and angle of attack with the lift coefficient are provided. Results indicated that the angles of descent without power are likely to be prohibitive and airplanes with the tested type of wings will not be able to land safely without power.
Date: February 12, 1947
Creator: Wilson, Herbert A., Jr. & Lovell, J. Calvin
Item Type: Refine your search to only Report
open access

Flight Investigation to Determine the Hinge Moments of a Beveled-Edge Aileron on a 45 Degree Sweptback Wing at Transonic and Low Supersonic Speeds

Description: Report discussing testing of a model of the pilotless aircraft RM-1 to measure aileron hinge moments in flight in order to determine the reason for loss of roll stabilization at supercritical speeds in flight. The aileron was found to become quickly underbalanced over the full deflection range at supercritical speeds. Information about the general flight behavior, aileron hinge moments, and roll stabilization of the model is provided.
Date: November 12, 1947
Creator: Gardner, William N. & Curfman, Howard J., Jr.
Item Type: Refine your search to only Report
open access

Two-dimensional wind-tunnel investigation at high Reynolds numbers of two symmetrical circular-arc airfoil sections with high-lift devices

Description: Report presenting an investigation of two symmetrical circular-arc airfoils of 6 and 10 percent thickness equipped with leading-edge and trailing-edge high-lift devices. A trialing-edge flap, drooped-nose flap, and leading-edge extensible flap were all tested. Results regarding the plain airfoils, airfoils with high-lift devices, combined deflection of high-lift devices, and low-drag-control flaps are provided.
Date: March 12, 1947
Creator: Underwood, William J. & Nuber, Robert J.
Item Type: Refine your search to only Report
open access

Preliminary Investigation of Two Full-Scale Propellers to Determine the Effect of Swept-Back Blade Tips on Propeller Aerodynamic Characteristics

Description: Report presenting an investigation of two 10-foot-diameter three-blade propellers to determine the effect of swept-back blade tips on propeller aerodynamic characteristics. Results regarding the effect of swept-back tips on maximum efficiency and constant-power propeller operation are provided.
Date: May 12, 1947
Creator: Evans, Albert J. & Klunker, E. Bernard
Item Type: Refine your search to only Report
open access

High-Speed Aerodynamic Characteristics of a Model Tail Plane with Modified NACA 65-010 Sections and 0 Degree and 45 Degrees Sweepback

Description: Memorandum presenting wind-tunnel tests that have been made to determine the aerodynamic characteristics of a model tail plane with modified NACA 65-010 sections and a tapered plan form. Results were obtained with the model tail plane unswept and swept back. The data show the lift, drag, pitching-moment, and hinge-moment coefficient variation with angle of attack and flap deflection at various Mach numbers.
Date: January 12, 1948
Creator: Anderson, Joseph L. & Martin, Andrew
Item Type: Refine your search to only Report
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