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Some Effects of Sweep and Aspect Ratio on the Transonic Flutter Characteristics of a Series of Thin Cantilever Wings Having a Taper Ratio of 0.6

Description: Report presenting an investigation of the flutter characteristics of a series of thin cantilever wings with taper ratios of 0.6 for a range of Mach numbers. Results regarding flutter frequencies, time histories, effects of sweep on the flutter-speed ratio, effects of aspect ratio on the flutter-speed ratio, effects of additional models on the reference flutter speed, application of the flutter-speed ratio, and modified experimental flutter-speed coefficient are provided.
Date: January 24, 1956
Creator: Unangst, John R. & Jones, George W., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of local heat-transfer and pressure drag characteristics of a yawed circular cylinder at supersonic speeds

Description: Local heat-transfer coefficients, temperature recovery factors, and pressure distributions were measured on the front side of a circular cylinder at a nominal Mach number of 3.9 over a range of free-stream Reynolds numbers from 2.1 x 10 to the 3rd power to 6.7 x 10 to the 3rd power and yaw angles from zero degrees to 44 degrees. Yawing the cylinder reduced the heat-transfer coefficients and the pressure drag coefficients. The amount of reduction may be predicted by a theory presented herein.
Date: January 24, 1956
Creator: Goodwin, Glen; Creager, Marcus O. & Winkler, Ernest L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Low-Amplitude Damping-in-Pitch Characteristics of Four Tailless Swept Wing-Body Combinations at Mach Numbers From 0.85 to 1.30 as Obtained With Rocket-Powered Models

Description: Report presenting an investigation to determine the damping-in-pitch characteristics of four rocket-powered wing-body combinations for a range of Mach numbers from 0.85 to 1.30. The models were tested at the same center-of-gravity location and had identical bodies. Information about the trim, lift, static longitudinal stability, dynamic longitudinal stability, and drag is provided.
Date: November 24, 1954
Creator: D'Aiutolo, Charles T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of Supersonic-Compressor Rotors Designed with External Compression

Description: Report presenting an investigation of the possibility of utilizing the relatively good characteristics of the spike-type diffuser in the supersonic compressor. Results regarding the overall performance, inlet conditions, outlet conditions, entrance flow conditions, and estimated performance of subsonic portion of rotor passage are provided.
Date: September 24, 1954
Creator: Jahnsen, Lawrence J. & Hartmann, Melvin J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Results of initial wind-tunnel flutter experiments at low speed with a towed airplane model having a 40 degree sweptback wing of aspect ratio 3.62 equipped with pylon-mounted stores

Description: Report presenting wind-tunnel flutter testing at a range of Mach numbers conducted on a swept-wing towed airplane model equipped with an autopilot system. Results regarding the towed model tests, fixed-root tests, and a comparison between the calculated and experimental flutter characteristics are provided.
Date: March 24, 1955
Creator: Martina, Albert P. & Young, George E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Low-Amplitude Damping-in-Pitch Characteristics of Tailless Delta-Wing-Body Combinations at Mach Numbers From 0.80 to 1.35 as Obtained With Rocket-Powered Models

Description: Report of an investigation using three rocket-propelled delta-wing-body combinations for a range of Mach numbers to determine the damping-in-pitch characteristics. All models were statically stable but dynamically unstable at transonic speeds. Information about trim, lift, and drag is also provided.
Date: June 24, 1954
Creator: D'Aiutolo, Charles T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The effect of ground on the low-speed aerodynamics control, and control hinge-moment characteristics of a delta-wing-fuselage model with trailing-edge controls

Description: Report presenting an investigation to determine the effect of ground on the low-speed aerodynamic, control, and control hinge-moment characteristics of a 3-percent-thick, delta-wing-fuselage configuration. Aerodynamic forces and moments and hinge-moment data were obtained for a range of angles of attack, ground heights, and a designated Mach and Reynolds number.
Date: September 24, 1954
Creator: Scallion, William I.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Low-Speed Static Stability Characteristics of a Complete Model with an M-Wing in Mid and High Positions and with Three Horizontal-Tail Heights

Description: Report presenting an investigation of the low-speed static longitudinal and lateral stability characteristics of a model with an M-wing in mid and high positions and with three horizontal-tail heights. The wing had its sweep discontinuity at 40-percent wing semispan, an aspect ratio of 6, a taper ratio of 0.60, NACA 65A009 airfoil sections parallel to the plane of symmetry, and 45 degrees sweep of the quarter-chord lines. Results regarding longitudinal stability characteristics and lateral stab… more
Date: January 24, 1956
Creator: Fournier, Paul G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of a Cermet Gas-Turbine-Blade Material of Titanium Carbide Infiltrated With Hastalloy C

Description: A cermet composition was investigated as a potential material for gas-turbine blades. Blades of HS-21 alloy were also operated in the engine simultaneously to provide a basis of comparison. The cermet blades survived as long as approximately 312-1/2 hours at about 1500 degrees F with an average midspan centrifugal stress of approximately 11,500 psi.
Date: January 24, 1955
Creator: Hoffman, Charles A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of Chord Discontinuities and Chordwise Fences on Low-Speed Static Longitudinal Stability of an Airplane Model Having a 35 Degree Sweptback Wing

Description: Report presenting the results of an investigation to determine the effect of chord discontinuities and chordwise fences on the static longitudinal stability and wake characteristics of an airplane model with a 35-degree sweptback wing. The use of a fence or chord extension was found to cause a slight improvement in the static longitudinal stability of the basic wing alone. The force data and flow characteristics in the form of wake surveys and surface tufts are provided.
Date: June 24, 1952
Creator: Jaquet, Byron M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Chordwise pressure distribution at high subsonic speeds near midsemispan of a tapered 35 degree sweptback wing of aspect ratio 4 having NACA 65A006 airfoil sections and equipped with various spoiler ailerons

Description: From Summary: "An investigation was made in the Langley high-speed 7- by 10-foot tunnel through a Mach number range from 0.60 to 0.93 to determine the effects on the chordwise pressure distributions of projecting various spoiler-type ailerons on a swept wing. The semispan 35 degree sweptback wing had an NACA 65A006 airfoil section, an aspect ratio of 4, and a taper ratio of 0.6. The results of the investigation are presented as curves of chordwise pressure distributions near the midspan of the … more
Date: June 24, 1952
Creator: Hammond, Alexander D. & McMullan, Barbara M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Determination and Use of the Local Recovery Factor for Calculating the Effectiveness Gas Temperature for Turbine Blades

Description: In an experimental investigation of local recovery factors for a blade having a pressure distribution similar to that of a typical reaction-type turbine blade, it a was found that the recovery factors were essentially independent of Mach number, Reynolds number, pressure gradient, and position on the blade surface except for regions where the boundary layer was probably in the transition range from laminar to turbulent. The recommended value of local subsonic recovery factor for use in calculat… more
Date: September 24, 1951
Creator: Esgar, Jack B. & Lea, Alfred L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Correlation of Analog Solutions With Experimental Sea-Level Transient Data for Controlled Turbine-Propeller Engine, Including Analog Results at Altitudes

Description: Memorandum presenting a satisfactory correlation obtained between experimental sea-level transient data at constant flight speed and solutions from the analog representation. The representation is accomplished by transfer functions formed from a frequency-response analysis, which is then used to compute system response at altitude.
Date: August 24, 1951
Creator: Lazar, James & DeRocher, Wilfred L., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Turbojet combustor efficiency with ceramic-coated liners and with mechanical control of fuel wash on walls

Description: Report presenting an investigation to evaluate two methods of decreasing losses of unevaporated fuel from the combustion zone of turbojet-engine combustors. One method had fuel dams on the inner surface of the combustor liner and one had a ceramic coating on the combustor-liner walls. Results regarding the effect of the fuel dams, effect of ceramic coatings, effect of combination of fuel dams and ceramic coatings, and effect of ceramic coating on carbon deposition are provided.
Date: November 24, 1952
Creator: Butze, Helmut F. & Jonash, Edmund R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of turbines suitable for use in a turbojet engine with high compressor pressure ratio and low compressor-tip speed 4: effect of increasing blade speed on velocity diagrams of turbine for engine operation at constant rotative speed

Description: Report presenting the use of a simplified method of analysis in order to estimate the turbine blade-tip speed required to design satisfactory two-stage turbines. The investigation allows for certain conditions for optimal two-stage turbine design to be determined.
Date: November 24, 1952
Creator: Davison, Elmer H. & English, Robert E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Performance characteristics of canard-type missile with wing-mounted nacelle engines at Mach numbers 1.5 to 2.0

Description: Report presenting an investigation of the overall performance characteristics of a complete canard-type missile configuration with wing-mounted nacelle engines in the 8- by 6-foot supersonic wind tunnel at a range of Mach numbers. The investigation covered a range of angles of attack, control-surface-deflection angles, and engine mass-flow ratios. Results regarding the overall force and moment evaluation, effect of engines on configuration performance, and effect of variation of engine mass-flo… more
Date: November 24, 1952
Creator: Kremzier, Emil J. & Davids, Joseph
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Some stress rupture and creep properties of molybdenum disilicide in the range of 1600 to 2000 F

Description: Report presenting an investigation of the stress-rupture and creep properties of hot-pressed molybdenum disilicide, which explored the stress-rupture properties, use of molybdenum disilicide at various temperatures, long-time strength, and a satisfactory method for creep and stress-rupture testing.
Date: June 24, 1952
Creator: Maxwell, W. A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Application of supersonic vortex-flow theory to the design of supersonic impulse compressor- or turbine-blade sections

Description: From Introduction: "The purpose of this paper is to present an analytical method for the design of two-dimensional related selection of a blade for particular rotor conditions may be made quickly and easily and its performance deduced from tests of representative sections in cascade."
Date: April 24, 1952
Creator: Boxer, Emanuel; Sterrett, James R. & Wlodarski, John
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of Effective Thermal Conductivities of Powders

Description: Memorandum presenting a simplified analysis to determine the effective thermal conductivity of a powder from the fraction of space occupied by the gas and conductivities of the solid and the gas which make up the powder. Tests were conducted to determine the conductivity of magnesium oxide powder in various gases at a range of temperatures. The effects of some of the factors neglected in the simplified analysis, such as bending of the heat-flow lines and the irregularity of the arrangement of t… more
Date: June 24, 1952
Creator: Deissler, R. G. & Eian, C. S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Instrumentation of the Ames Supersonic Free-Flight Wind Tunnel

Description: Memorandum presenting a description of the equipment used in the Ames supersonic free-flight wind tunnel to obtain the data necessary to measure the aerodynamic characteristics of free-flying models. The model is fired from a gun into the supersonic air stream of a blowdown-type wind tunnel. The action resulting from aerodynamic forces is computed from a time-distance-attitude record of the model flight through the test section.
Date: April 24, 1952
Creator: Briggs, Robert O.; Kerwin, William J. & Schmidt, Stanley F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of the Effect of a Nacelle at Various Chordwise and Vertical Positions on the Aerodynamic Characteristics at High Subsonic Speeds of a 45 Degrees Sweptback Wing With and Without a Fuselage

Description: Report presenting an investigation of a nacelle at various chordwise positions and vertical locations on a semispan model of a wing with and without a fuselage through a range of Mach numbers. The investigation was made to determine the interference characteristics between the nacelle and the model and to determine the effect of the fuselage on nacelle interference.
Date: September 24, 1951
Creator: Silvers, H. Norman; King, Thomas J., Jr. & Pasteur, Thomas B., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Free-Spinning Tunnel Investigation of a 1/20-Scale Model of the McDonnell F2H-3 Airplane

Description: Memorandum presenting an investigation conducted in the 20-foot free-spinning tunnel on a 1/20-scale model of the McDonnell F2H-3 airplane. The effects of control settings and movement on the erect spin and recovery characteristics of the model were determined for the take-off condition and for the condition with full wing-tip fuel tanks installed.
Date: July 24, 1951
Creator: Wilson, Jack H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An experimental investigation of boundary interference on force and moment characteristics of lifting models in the Langley 16- and 8-foot transonic tunnels

Description: Report presenting testing of a wing-fuselage force model configuration and the fuselage alone at angles of attack up to 32 degrees in the 16-foot transonic tunnel. Results regarding the force and moment characteristics, base pressures, and shadowgraph pictures are provided.
Date: February 24, 1953
Creator: Whitcomb, Charles F. & Osborne, Robert S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Buffeting of a vertical tail on an inclined body at supersonic Mach numbers

Description: Report presenting time histories of rolling and yawing moments on inclined bodies of revolution with vertical-tail surfaces at several Mach numbers and Reynolds numbers. Three ogival-nose bodies with three overall fineness ratios and a conical-nosed body with a fineness ratio of 12.0 were tested. Results regarding the visual-flow studies, rolling- and yawing-moment measurements, and pressure measurements are provided.
Date: March 24, 1953
Creator: Gowen, Forrest E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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