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Turbine Failure Investigation of J65-W-4 Turbojet Engine in an Altitude Test Chamber

Description: Memorandum presenting an altitude investigation to determine the basic mechanism by which J65-W-4 turbine rotor-blade failures were occurring in service. The engine was installed in an altitude test chamber and a series of controlled engine throttle bursts, with and without inlet-air distortion, over a range of altitudes, flight Mach numbers, and inlet-air temperatures. An examination of the data obtained during the investigation indicated that the danger of turbine failure could be eliminated … more
Date: September 21, 1956
Creator: McAulay, John E.; Braithwaite, Willis M. & Ciepluch, Carl C.
Item Type: Refine your search to only Report
open access

Analysis of turbojet and ram-jet engine cycles using various fuels

Description: From Introduction: "These data have been collected for presentation in this report to illustrate the performance of turbojet and ram-jet cycles utilizing several of the more promising high-energy fuels. Results are presented in terms of engine over-all efficiency and thrust per pound of airflow as functions of flight Mach number."
Date: November 27, 1956
Creator: Wilcox, E. Clinton; Weber, Richard J. & Tower, Leonard K.
Item Type: Refine your search to only Report
open access

Full-Scale Evaluation of Some Flameholder Design Concepts for High-Inlet-Velocity Afterburners

Description: Memorandum presenting an investigation of a full-scale afterburner with high burner-inlet velocity conducted to determine burner performance with several variations in burner design. Variables receiving particular attention were flameholder design and burner length. Results regarding diffuser performance, performance of the reference two-V-gutter flameholder, designs to improve combustion for high-velocity conditions, and operational characteristics are provided.
Date: June 28, 1956
Creator: Prince, William R.; Velie, Wallace W. & Braithwaite, Willis M.
Item Type: Refine your search to only Report
open access

Wing-Body Combinations With Wings of Very Low Aspect Ratio at Supersonic Speeds

Description: Memorandum presenting force and moment characteristics of configurations employing wings of very low aspect ratio as determined for Mach numbers of 1.97 and 3.33. The angle of attack range was from 0 to 17 degrees for Mach number 1.97 and from 0 to 30 degrees for Mach number 3.33. Results regarding experimental force and moment characteristics, comparisons of theoretical and experimental force and moment characteristics, and visual observations of flow over models are provided.
Date: October 26, 1956
Creator: Jorgensen, Leland H. & Katzen, Elliott D.
Item Type: Refine your search to only Report
open access

Static Lateral and Directional Stability and Control Characteristics of a Revised 1/22-Scale Model of the Republic F-105 Airplane at Mach Numbers of 1.41 and 2.01

Description: Report discussing testing to determine the static lateral and directional stability and control characteristics of a model of the Republic F-105 airplane. The effects of various vertical tails and ventral fins, wing-tip fences, a canopy fin, fuselage nose shape, external stores, and deflection of horizontal tail, spoiler, and rudder were explored.
Date: October 16, 1956
Creator: Robinson, Ross B. & Foster, Gerald V.
Item Type: Refine your search to only Report
open access

Investigation of Drag and Static Longitudinal and Lateral Stability Characteristics of a 1/15-Scale Model of the Grumman F11F-1F Airplane at Mach Numbers of 1.56, 1.76, 2.06, and 2.53

Description: Report presenting an investigation in the Langley Unitary Plan wind tunnel to determine the drag and static longitudinal and lateral stability characteristics of a model of the Grumman F11F-1F airplane at Mach numbers 1.56, 1.76, 2.06, and 2.53. The investigation included the effects on performance and stability of modifications, including a wing-root leading-edge fillet and horizontal tails with negative dihedral of 10 degrees and 30 degrees. Information regarding net external minimum drag coe… more
Date: November 30, 1956
Creator: Turner, Kenneth L. & Fournier, Roger H.
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

The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wing-Fuselagestore Configurations 6. - Swept-Wing Heavy-Bomber Configuration With Stores of Different Sizes and Shapes

Description: Memorandum presenting a supersonic wind-tunnel investigation of the origin and distribution of store interference performed in the 4- by 4-foot supersonic pressure tunnel at Mach number 1.61 in which separate forces on a store, a fuselage, a swept wing, and a swept-wing-fuselage combination were measured. The report presents data on a configuration which simulated a heavy-bomber airplane with stores of several shapes and sizes.
Date: March 8, 1956
Creator: Smith, Norman F.
Item Type: Refine your search to only Report
open access

Force and Pressure-Distribution Investigation to High Angles of Attack on All-Movable Triangular and Rectangular Wings in Combination With a Body at Supersonic Speeds

Description: Force and pressure distribution studies to high angles of attack on all-movable triangular and rectangular wings in combination with body at supersonic speeds. The ranges of aspect ratios were, for the triangular wings, 3/8 to 4, and for the rectangular wings, 1 to 3.
Date: July 10, 1956
Creator: Hill, William A., Jr. & Kaattari, George E.
Item Type: Refine your search to only Report
open access

Some Considerations Regarding the Application of the Supersonic Area Rule to the Design of Airplane Fuselages

Description: Memorandum presenting certain considerations and techniques pertinent to the application of the supersonic area rule to the design of airplane fuselages. Some of the factors considered are an extension of the rule to account for the interference effects of the wing and tail on the general flow field for asymmetrical configurations, the determination of fuselage area developments which result in approximately the minimum wave drag, and the influence of wing parameters and design Mach number on t… more
Date: July 3, 1956
Creator: Whitcomb, Richard T.
Item Type: Refine your search to only Report
open access

A Summary of Results Obtained During Flight Simulation of Several Aircraft Prototypes With Variable-Stability Airplanes

Description: Memorandum describing an investigation using two airplanes, an F6F-3 and F-86A, each fitted with servo equipment for varying in flight the lateral and directional stability and handling characteristics, which have been flown by test pilots to simulate the predicted dynamic behavior of six prototype airplanes. The methods of simulation and the types and ranges of variables considered are presented and the results of the individual programs are discussed.
Date: May 25, 1956
Creator: McNeill, Walter E. & Creer, Brent Y.
Item Type: Refine your search to only Report
open access

Minimum Drag of Four Versions of a Swept-Wing Fighter Airplane Obtained From Flight Tests of Rocket-Boosted Models at Mach Numbers From 0.81 to 1.71

Description: Memorandum presenting tests conducted with four specific versions of a swept-wing fighter airplane, which indicate that a large reduction in external-drag coefficient was accomplished by redesigning the original configuration. The forebody modifications, which consisted of a smaller canopy, slimmer nose, and sharper inlet lip, reduced the value of the external-drag coefficient from 0.044 to 0.042 at a Mach number of 1.05 and from 0.042 to 0.040 at a Mach number of 1.28.
Date: September 7, 1956
Creator: Hastings, Earl C., Jr.
Item Type: Refine your search to only Report
open access

Low-Speed Investigation of the Effect of Small Canard Surfaces on the Directional Stability of a Sweptback-Wing Fighter-Airplane Model

Description: Memorandum presenting a low-speed investigation in the free-flight tunnel to determine the effect of small canard surfaces on the directional stability of a fighter-airplane model with an aspect ratio of 3.4 and a 42 degree sweptback wing. The canard surfaces were found to be generally ineffective at angles of attack below 20 degrees.
Date: August 23, 1956
Creator: Paulson, John W. & Boisseau, Peter C.
Item Type: Refine your search to only Report
open access

Low-Speed Roll Effectiveness of a Differentially Deflected Horizontal-Tail Surface on a 42 Degree Swept-Wing Model

Description: Memorandum presenting an investigation to determine the roll effectiveness of a differentially deflected horizontal tail of a 42 degree swept-wing model. The model was tested through an angle-of-attack range of 0 degrees through the stall in the clean and landing configurations with the horizontal tail in a low position. Results regarding the longitudinal characteristics and lateral characteristics are provided.
Date: June 19, 1956
Creator: Boisseau, Peter C.
Item Type: Refine your search to only Report
open access

Full-Scale Wind-Tunnel Tests of a North American FJ-3 Airplane with a Spoiler-Slot-Deflector Lateral Control System

Description: Report discussing an investigation to determine the low-speed aerodynamic characteristics of a North American FJ-3 airplane with a segmented spoiler-slot-deflector lateral control system installed ahead of convention ailerons and operated as individual units and as combined segments. The longitudinal characteristics of the plane, the spoiler-slot-deflector effectiveness, and spoiler-deflector hinge-moment data are all described.
Date: April 9, 1956
Creator: Scallion, William I.
Item Type: Refine your search to only Report
open access

Static Lateral-Directional Stability Characteristics of Five Contemporary Airplane Models From Wind-Tunnel Tests at High Subsonic and Supersonic Speeds

Description: Memorandum presenting the static lateral-directional stability characteristics of several airplane models recently investigated which cover many of the geometric arrangements of high-speed airplane components of current interest. The results are limited to the most pertinent aerodynamic phenomena contributing to the lateral-directional characteristics of each airplane type. Results for five different models are provided.
Date: January 4, 1956
Creator: Smith, Willard G. & Ball, Louis H.
Item Type: Refine your search to only Report
open access

Transonic Aerodynamic and Trim Characteristics of a Multi-Engine Delta-Wing Airplane Model

Description: Memorandum presenting an investigation of three models of a delta-wing airplane designed for a long-range subsonic cruise and a supersonic dash. Results regarding the aerodynamic characteristics of the models and effect of elevon deflection on aerodynamic characteristics of the four-engine model are provided.
Date: February 17, 1956
Creator: Swihart, John M. & Foss, Willard E., Jr.
Item Type: Refine your search to only Report
open access

Some Interference Effects That Influence Vertical-Tail Loads at Supersonic Speeds

Description: Memorandum presenting three types of aerodynamic interference originating from forward components of airplanes, which are shown to contribute to decreased vertical-tail effectiveness. The vorticity originating from a slender fuselage ahead of the wing resulted in a marked reduction in vertical-tail effectiveness with angle of attack for one model.
Date: February 17, 1956
Creator: Edwards, S. Sherman
Item Type: Refine your search to only Report
open access

Pressure Distributions at Mach Numbers of 1.6 and 1.9 of a Conically Cambered Wing of Triangular Plan Form With and Without Pylon-Mounted Engine Nacelles

Description: Memorandum presenting the results of an experimental investigation to determine the pressure-distribution characteristics of a conically cambered wing with and without pylon-mounted engine nacelles for Mach numbers of 1.6 and 1.9. The pressure data obtained during this investigation indicate that the low-pressure region existing on the upper surface over the forward part of the wing was spread over a larger proportion of the local chord than would be the case for an uncambered wing.
Date: April 20, 1956
Creator: Phelps, E. Ray
Item Type: Refine your search to only Report
open access

Use of Truncated Flapped Airfoils for Impingement and Icing Tests of Full-Scale Leading-Edge Sections

Description: From Summary: "In an effort to increase the operational range of existing small icing tunnels, the use of truncated airfoil sections has been suggested. With truncated airfoils, large-scale or even full-scale wing-icing-protection systems could be evaluated. Therefore, experimental studies were conducted in the NACA Lewis laboratory icing tunnel with an NACA 651-212 airfoil section to determine the effect of truncating the airfoil chord on velocity distribution and impingement characteristics. … more
Date: July 24, 1956
Creator: von Glahn, Uwe H.
Item Type: Refine your search to only Report
open access

Wind Tunnel Investigation at Low Speed of Aerodynamic Characteristics of Army Chemical Corps Model E-112 Bomblets with Span Chord Ratio of 2 - 1

Description: "An experimental investigation has been made in the Langley stability tunnel to determine the aerodynamic characteristics of the Army Chemical Corps model E-112 bomblets with span-chord ratio of 2:1. A detailed analysis has not been made; however, the results showed that all the models were spirally unstable and that a large gap between the model tips and end plates tended to reduce the instability" (p. 1).
Date: December 26, 1956
Creator: Letko, William
Item Type: Refine your search to only Report
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