UNT Libraries Government Documents Department - 158 Matching Results

Search Results

Results: 1 - 24 next
open access

A flight study of longitudinal-control-system dynamic characteristics by the use of a variable-control-system airplane

Description: Report presenting flight tests with an airplane equipped to vary the longitudinal-control-system dynamic characteristics over a wide range. Control is obtained through a stabilizer force-command position-feedback longitudinal-control system. Results at a Mach number of 0.80 at 35,000 feet altitude, Mach number of 0.35 at 5,000 feet altitude, and normal-acceleration response are provided.
Date: March 3, 1958
Creator: McFadden, Norman M.; Pauli, Frank A. & Heinle, Donovan R.
Item Type: Refine your search to only Report
open access

Static Longitudinal and Lateral Stability and Control Characteristics of a Model of a Swept-Wing Fighter-Bomber-Type Airplane With a Top Inlet at Mach Numbers From 1.6 to 2.35

Description: "Static longitudinal and lateral stability characteristics of a swept-wing fighter-bomber airplane model with a top inlet have been determined experimentally. In addition, vertical-tail effectiveness, spoiler effectiveness, effects of several store configurations, and effects of mass flow were investigated. Tests were made at Mach numbers of 1.6, 1.8, 2.0, 2.2, and 2.35 and Reynolds numbers, based upon mean aerodynamic chord, of between 2.0x10(exp 6) and 2.5x10(exp 6)" (p. 1).
Date: March 3, 1958
Creator: Gnos, A. Vernon & Kurkowski, Richard L.
Item Type: Refine your search to only Report
open access

Heat Transfer Measured on a Flat-Face Cylinder-Flare Configuration in Free Flight at Mach Numbers From 1.6 to 2.7

Description: Report presenting heat-transfer measurements for a flat-face cylinder-flare configuration in free flight up to Mach number 2.7. Skin temperatures were measured at 12 points along the configuration. Information about the heating rates was compared to data obtained from theoretical calculations.
Date: February 3, 1958
Creator: Lee, Dorothy B. & Swanson, Andrew G.
Item Type: Refine your search to only Report
open access

Subsonic aerodynamic characteristics up to extreme angles of attack of an airplane model having an unswept wing and a high horizontal tail

Description: Report presenting wind-tunnel measurements of the forces and moments of a model of an airplane with pitch-up tendencies at angles of attack up to 70 degrees. The model had an unswept, low-aspect-ratio wing, a long fuselage, and a high horizontal tail. Results regarding longitudinal and lateral directional characteristics, effects of wing-tip tanks and tip-tank fins, and longitudinal characteristics of the fuselage-tail combination are provided.
Date: February 3, 1958
Creator: Tinling, Bruce E.
Item Type: Refine your search to only Report
open access

A Wind Tunnel Investigation of Several Wingless Missile Configurations at Supersonic Speeds

Description: Report presenting an investigation of several wingless missile configurations for a range of Mach numbers to determine their lift, drag, and pitching-moment coefficients. Results for missiles having nose controls and missiles having tail controls are provided. The results were also compared to a conventional missile with wings.
Date: February 3, 1958
Creator: Reese, David E., Jr.
Item Type: Refine your search to only Report
open access

Wind-Tunnel Investigation of the Effects of Lip Geometry on Drag and Pressure Recovery of a Normal-Shock Nose Inlet on a Body of Revolution at Mach Numbers of 1.41 and 1.81

Description: Report presenting an investigation to determine some of the effects of lip geometry on drag and pressure recovery of a normal-shock nose inlet. Lip bluntness, lip camber, and forebody angle were all explored as possible variables. Total-pressure recoveries, external drags, duct total-pressure distributions, lip and forebody pressure distributions, and Schileren photographs are provided.
Date: February 3, 1958
Creator: Robins, A. Warner
Item Type: Refine your search to only Report
open access

Effect of inlet air distortion on steady-state performance of an axial-flow turbojet engine

Description: Report presenting an investigation to determine the effects of magnitude and circumferential extent of inlet total-pressure distortions on the overall an component performance of a current turbojet engine. Results regarding the pressure and temperature profiles, component performance, engine pumping characteristics, net thrust and net-thrust specific fuel consumption are provided.
Date: January 3, 1958
Creator: Russey, Robert E. & Seashore, Ferris L.
Item Type: Refine your search to only Report
open access

Aerodynamic characteristics at Mach number of 4.06 of a typical supersonic airplane model using body and vertical-tail wedges to improve directional stability

Description: Report presenting an investigation at Mach number 4.06 on a typical supersonic airplane model with a 40 degree sweptback wing. The purpose of the investigation was to determine the effectiveness of using wedges on the body and on the vertical tail to increase the static directional stability. Results regarding the longitudinal characteristics and lateral characteristics are provided.
Date: December 3, 1957
Creator: Dunning, Robert W.
Item Type: Refine your search to only Report
open access

Aerodynamic Characteristics of a Model of an Escape Capsule for a Supersonic Bomber-Type Airplane at a Mach Number of 2.49

Description: Report discussing an investigation of the aerodynamic characteristics of a model of an escape capsule with and without stabilizing fins for a supersonic bomber-type airplane. Lift, drag, longitudinal and lateral stability characteristics, and photographs of the capsule model are presented.
Date: December 3, 1957
Creator: Presnell, John G., Jr.
Item Type: Refine your search to only Report
open access

Effects of string-support interference on the drag of an olgive-cylinder body with and without a boatail at 0.6 to 1.4 Mach number

Description: Report presenting tests to determine the effects of sting-support interference on the zero-lift drag of two bodies of revolution (with and without boattailing). The sting support consisted of a constant-diameter sting followed by a sting flare terminating in a cylindrical support. Results regarding the effect of sting length and sting diameter are provided.
Date: December 3, 1957
Creator: Lee, George & Summers, James L.
Item Type: Refine your search to only Report
open access

Investigation at High Subsonic Speeds of the Static Longitudinal and Lateral Stability Characteristics of Two Canard Airplane Configurations

Description: "The present investigation was conducted in the Langley high-speed 7-by 10-foot tunnel to determine the static longitudinal and lateral stability characteristics at high subsonic speeds of two canard airplane configurations previously tested at supersonic speeds. The Mach number range of this investigation extended from 0.60 to 0.94 and a maximum angle-of-attack range of -2deg to 24deg was obtained at the lowest test Mach number. Two wing plan forms of equal area were studied in the present tes… more
Date: December 3, 1957
Creator: Sleeman, William C., Jr.
Item Type: Refine your search to only Report
open access

Heat-Exchanger-Core Weights for Use With Hydrogen-Expansion Turbine

Description: Memorandum presenting an analysis of probable heat-exchanger weights for stationary and rotary regenerator heat exchangers for use in a hydrogen-expansion turbine engine. This is because rotary regenerators offer possibilities for a considerably lighter heat-exchanger core, possibly one-fourth that of the stationary regenerators.
Date: October 3, 1957
Creator: Reynolds, Thaine W.
Item Type: Refine your search to only Report
open access

Investigation of Rotating-Stall Limits in a Supersonic Turbofan Engine

Description: Memorandum presenting a theoretical mixed-jet one-spool turbofan engine analyzed over a range of flight Mach numbers up to 2.95. The engine was characterized by an eight-stage fan-compressor unit. Results regarding performance maps, rotating stall, turbofan inlet axial velocity, and weight-flow variations are provided.
Date: October 3, 1957
Creator: Dugan, James F., Jr.
Item Type: Refine your search to only Report
open access

A Note on the Ability to Predict Transonic Drag-Rise Changes Due to Model Modifications

Description: Memorandum presenting an experimental and analytical study made at transonic speeds up to Mach number 1.43 to determine the ability of present calculation procedures to predict transonic drag-rise changes which result from physical model changes. Both wing-body and wing-body-tail configurations were investigated.
Date: October 3, 1957
Creator: Pierpont, P. Kenneth
Item Type: Refine your search to only Report
open access

A Note on the Ability to Predict Transonic Drag-Rise Changes Due to Model Modifications

Description: Report presenting an experimental and analytical study at transonic speeds up to Mach number 1.43 to determine the ability of present calculation procedures to predict transonic drag-rise changes resulting from physical model changes. Results regarding wing-body configurations, wing-body-tail configurations, and drag-rise change are provided. With the exception of the model with the bluff forebody and afterbody, the currently available calculative procedures provided estimates of transonic drag… more
Date: October 3, 1957
Creator: Pierpont, P. Kenneth
Item Type: Refine your search to only Report
open access

Summary of NACA Research on Ignition Lag of Self-Igniting Fuel - Nitric Acid Propellants

Description: Memorandum presenting a summary of ignition-lag data obtained from 1949 to 1956 in terms of dependence on temperature, pressure, reactor geometry, mixing method, and propellant composition. Analysis of the results and comparisons with data from other sources indicate agreement with a chemical kinetics model provided that mixing is reasonably energetic.
Date: October 3, 1957
Creator: Morrell, Gerald
Item Type: Refine your search to only Report
open access

Analysis of two-spool turboprop-engine characteristics

Description: From Introduction: "The purpose of this report is to present the results of an analytical investigation of the engine characteristics of two-spool engines with high over-all compressor pressure ratio (12.0 at design). Some of the turbine design problems encountered in a single-spool engine with current compressor pressure ratio (7.32 at design) were investigated in reference 1. The investigation was extended in reference 2 to cover the effect of mode of engine operation on the turbine design re… more
Date: June 3, 1957
Creator: Davison, Elmer H.
Item Type: Refine your search to only Report
open access

Effect of fuel properties on liner temperatures in a single tubular turbojet combustor

Description: Report presenting the effect of fuel properties on combustion-liner temperatures in a single tubular combustor at combustor-inlet conditions representative of those encountered in turbojet-powered high-flight-speed aircraft. Testing was conducted with three liquid jet-type fuels that varied in voltaility and aromatic content. The variations in fuel properties were found to produce only moderate and not always consistent changes in average liner temperature.
Date: June 3, 1957
Creator: Butze, Helmut F.
Item Type: Refine your search to only Report
open access

Experimental Investigation of Effects of Combustion-chamber Length and Inlet Total Temperature, Total Pressure, and Velocity on Afterburner Performance

Description: Report presenting an investigation of the effects of afterburner-inlet total temperature, total pressure, velocity, fuel-air ratio, and afterburner combustion-chamber length on afterburner performance and stability limits using a cylindrical afterburner installed in a duct test rig. The afterburner was investigated over a range of total temperature, total pressure, velocity, and afterburner fuel-air ratios.
Date: June 3, 1957
Creator: King, Charles R.
Item Type: Refine your search to only Report
open access

Experimental Investigation of Modified Cast-Cored Blades Having Hollow Tip Sections

Description: Memorandum presenting the development of fabrication techniques to provide cast-cored turbine blades with hollow tip sections. Two types of modified cast-cored blades that provided an 11-percent weight reduction from a fully cast-cored blade and a 13-percent weight reduction from a standard uncooled blade were investigated in a turbojet engine modified for air-cooling. Results regarding the experimental heat-transfer, temperature comparison with other cooled-blade configurations, calculated and… more
Date: June 3, 1957
Creator: Oldrieve, Robert E. & Freche, John C.
Item Type: Refine your search to only Report
Back to Top of Screen