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Performance of Isentropic Nose Inlets at Mach Number of 5.6

Description: Memorandum presenting an investigation of the performance of inlet configurations with a forebody designed for isentropic external compression at a nominal Mach number of 5.6. At zero angle of attack, all the configurations yielded larger total-pressure recoveries than had previously been obtained with a single-conical-shock inlet. Results regarding the flow about the forebody, inlet performance, and performance comparisons are provided.
Date: May 6, 1954
Creator: Bernstein, Harry & Haefeli, Rudolph C.
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

Wind-Tunnel Investigation at Low Speed of the Rolling Stability Derivatives of a 1/10-Scale Model of the Douglas A4D-1 Airplane

Description: Report discussing an experimental investigation of the low-speed rolling stability derivatives of a model of the Douglas A4D-1. The model was tested under a variety of conditions, including in clean and landing configurations and with the horizontal and vertical tails on and off, and the study also explored the effects of slats and flaps on the derivatives of the wing. No analysis of the data is provided.
Date: October 7, 1954
Creator: Wolhart, Walter D. & Fletcher, H. S.
Item Type: Refine your search to only Report
open access

Wind-Tunnel Investigation at Low Speed of the Yawing Stability Derivatives of a 1/10-Scale Model of the Douglas A4D-1 Airplane

Description: Report discussing testing of a model of the Douglas A4D-1 to determine its low-speed yawing stability derivatives. The model was tested in clean and landing configurations with horizontal and vertical tails on and off and an investigation into the effect of slats and flaps on the wing-alone derivatives.
Date: August 25, 1954
Creator: Wolhart, Walter D. & Fletcher, H. S.
Item Type: Refine your search to only Report
open access

The Effect of Blunt-Trailing-Edge Modifications on the High-Speed Stability and Control Characteristics of a Swept-Wing Fighter Airplane

Description: An investigation was conducted on a 35 deg swept-wing fighter airplane to determine the effects of several blunt-trailing-edge modifications to the wing and tail on the high-speed stability and control characteristics and tracking performance. The results indicated significant improvement in the pitch-up characteristics for the blunt-aileron configuration at Mach numbers around 0.90. As a result of increased effectiveness of the blunt-trailing-edge aileron, the roll-off, customarily experienced… more
Date: May 26, 1954
Creator: Sadoff, Melvin; Matteson, Frederick H. & Van Dyke, Rudolph D., Jr.
Item Type: Refine your search to only Report
open access

Experimental Determination of Thermal Conductivity of Low-Density Ice

Description: "The thermal conductivity of low-density ice has been computed from data obtained in an experimental investigation of the heat transfer and mass transfer by sublimation for an iced surface on a flat plate in a high-velocity tangential air stream. The results are compared with data from several sources on the thermal conductivity of packed snow and solid glaze ice. The results show good agreement with the equations for the thermal conductivity of packed snow as a function of snow density. The ag… more
Date: March 1954
Creator: Coles, Willard D.
Item Type: Refine your search to only Report
open access

A Procedure for the Design of Air-Heated Ice-Prevention Systems

Description: A procedure proposed for use in the design of air-heated systems for the continuous prevention of ice formation on airplane components is set forth. Required heat-transfer and air-pressure-loss equations are presented, and methods of selecting appropriate meteorological conditions for flight over specified geographical areas and for the calculation of water-drop-impingement characteristics are suggested. In order to facilitate the design, a simple electrical analogue was devised which solves th… more
Date: June 1954
Creator: Neel, Carr B.
Item Type: Refine your search to only Report
open access

Investigation of Three Low-Temperature-Ratio Combustor Configurations in a 48-Inch-Diameter Ram-Jet Engine

Description: Memorandum presenting a preliminary evaluation of three types of combustor configuration in a 48-inch-diameter ramjet engine in order to select the one with the greatest promise of efficient and stable combustion at low fuel-air ratios and low combustor-inlet pressures. Results regarding the inlet conditions, performance, and a comparison of the configurations are provided.
Date: March 10, 1954
Creator: Meyer, Carl L. & Weina, Harry J.
Item Type: Refine your search to only Report
open access

Longitudinal Aerodynamic Characteristics to Large Angles of Attack of a Cruciform Missile Configuration at a Mach Number of 2

Description: Memorandum presenting the lift, pitching-moment, and drag characteristics of a missile configuration with a body of fineness ratio 9.33 and a cruciform triangular wing and tail of aspect ratio 4 at a Mach number of 1.99 and a Reynolds number of 6.0 million. Testing was performed to investigate the effects on the aerodynamic characteristics of roll angle, wing-tail interdigitation, wing deflection, and interference among the components. Results regarding the body-wing-tail combination, body, win… more
Date: December 6, 1954
Creator: Spahr, J. Richard
Item Type: Refine your search to only Report
open access

Preliminary Transient Performance Data on the Fuel Control of the XRJ47-W-5 Ram-Jet Engine

Description: Report discussing the characteristics of the fuel control of the 48-inch diameter WRJ47-W-5 ramjet engine, including the time history of the fuel system pressures, fuel flow, and engine inlet total pressure. Oscillograph traces for the different variables are provided as well as the accuracy of the calibration factors.
Date: January 29, 1954
Creator: Welna, Henry J. & Smith, Ivan D.
Item Type: Refine your search to only Report
open access

On the Three-Dimensional Instability of Laminar Boundary Layers on Concave Walls

Description: Memorandum presenting a study of the stability of laminar boundary layer profiles on slightly curved walls relative to small disturbances, in the shape of vortices, whose axes are parallel to the principal direction of flow. The result in an eigenvalue problem by which, for a given undisturbed flow at a prescribed wall, the amplification or decay is computed for each Reynolds number and each vortex thickness.
Date: June 1954
Creator: Görtler, H.
Item Type: Refine your search to only Thesis or Dissertation
open access

The Resistance to Air Flow of Porous Materials Suitable for Boundary-Layer-Control Applications Using Area Suction

Description: "Measurements were made of the resistance to air flow of commercially available porous materials. Three general types of porous media were tested - granular (sintered materials), fibrous (felt cloths and filter papers), and perforated. The flow-resistance characteristics of the porous materials tested are presented in a form intended to assist in the selection of materials for applications to boundary-layer control using area suction" (p. 1).
Date: January 1954
Creator: Dannenberg, Robert E.; Weiberg, James A. & Gambucci, Bruno J.
Item Type: Refine your search to only Report
open access

A flight investigation of the practical problems associated with porous-leading-edge suction

Description: From Summary: "A flight investigation has been made of the practical problems associated with the use of porous-leading-edge suction. The wing leading edge of the test airplane was porous over approximately 83 percent of the span and the first 8 percent of the chord on the upper surface. Various other extents of suction area within these limits were also tested."
Date: February 1954
Creator: Hunter, Paul A. & Johnson, Harold I.
Item Type: Refine your search to only Report
open access

A theoretical study of the effect of forward speed on the free-space sound-pressure field around propellers

Description: Report presenting an analysis of the sound-pressure field of a rotating propeller in forward flight in free space by replacing the normal-pressure distribution over the propeller associated with thrust and torque by a distribution of acoustic pressure doublets acting at the propeller disk. The result is presented for a moving and a fixed observer.
Date: 1954
Creator: Garrick, I. E. & Watkins, Charles E.
Item Type: Refine your search to only Report
open access

Effect of Ice Formations on Section Drag of Swept NACA 63A-009 Airfoil with Partial-Span Leading-Edge Slat for Various Modes of Thermal Ice Protection

Description: From Summary: "The effects of primary and runback ice formations on the section drag of a 36 deg swept NACA 63A-009 airfoil section with a partial-span leading-edge slat were studied over a range of angles of attack from 2 to 8 deg and airspeeds up to 260 miles per hour for icing conditions with liquid-water contents ranging from 0.39 to 1.23 grams per cubic meter and datum air temperatures from 10 to 25 F. The results with slat retracted showed that glaze-ice formations caused large and rapid … more
Date: March 15, 1954
Creator: von Glahn, Uwe H. & Gray, Vernon H.
Item Type: Refine your search to only Report
open access

Tests of the Northrop XB-62 Missile in the Ames 40- by 80-Foot Wind Tunnel

Description: Memorandum presenting a series of tests made on a full-scale Northrop XB-62 missile to determine the cause of a directional out-of-trim condition which was encountered on the initial missile flight tests. The results indicated that the directional out-of-trim condition was caused by aerodynamic loads induced by engine operation.
Date: September 27, 1954
Creator: Graham, David
Item Type: Refine your search to only Report
open access

Flight Investigation to Evaluate the Roll-Rate Stabilization System of the Naval Ordnance Test Station SIDEWINDER Missile at Mach Numbers From 0.9 to 2.3

Description: Report presenting a flight investigation using a rocket-powered model to evaluate the roll-rate stabilization of the Naval Ordnance Test Station SIDEWINDER missile, which uses aerodynamic damping by gyro-actuated rollerons. Dynamic roll instability was found to occur in flight.
Date: April 29, 1954
Creator: Brown, Clarence A., Jr. & Nason, Martin L.
Item Type: Refine your search to only Report
open access

Impingement of Water Droplets on an Ellipsoid with Fineness Ratio 5 in Axisymmetric Flow

Description: "The presence of radomes and instruments that are sensitive to water films or ice formations in the nose section of all-weather aircraft and missiles necessitates a knowledge of the droplet impingement characteristics of bodies of revolution. Because it is possible to approximate many of these bodies with an ellipsoid of revolution, droplet trajectories about an ellipsoid of revolution with a fineness ratio of 5 were computed for incompressible axisymmetric air flow. From the computed droplet t… more
Date: March 1954
Creator: Dorsch, Robert G.; Brun, Rinaldo J. & Gregg, John L.
Item Type: Refine your search to only Report
open access

Variation of Local Liquid-Water Concentration About and Ellipsoid of Fineness Ratio 5 Moving in a Droplet Field

Description: From Summary: "Trajectories of water droplets about an ellipsoid of revolution with a fineness ratio of 5 (which often approximates the shape of an aircraft fuselage or missile) were computed with the aid of a differential analyzer. Analyses of these trajectories indicate that the local concentration of liquid water at various points about an ellipsoid in flight through a droplet field varies considerably and under some conditions may be several times the free-stream concentration."
Date: July 1954
Creator: Dorsch, Robert G. & Brun, Rinaldo J.
Item Type: Refine your search to only Report
open access

Experimental Investigation of Sublimation of Ice at Subsonic and Supersonic Speeds and Its Relation to Heat Transfer

Description: "An experimental investigation was conducted in a 3.84- by 10-inch tunnel to determine the mass transfer by sublimation, heat transfer, and skin friction for an iced surface on a flat plate for Mach numbers of 0.4, 0.6, and 0.8 and pressure altitudes to 30,000 feet. Measurements of rates of sublimation were also made for a Mach number of 1.3 at a pressure altitude of 30,000 feet. The results show that the parameters of sublimation and heat transfer were 40 to 50 percent greater for an iced surf… more
Date: March 1954
Creator: Coles, Willard D. & Ruggeri, Robert S.
Item Type: Refine your search to only Report
open access

Preliminary Investigation of a Technique for Stability Studies of a Self-Propelled Model of a Submerged Submarine

Description: Report presenting the initial development of a technique for the qualitative study of the stability and control characteristics of a free, self-propelled, dynamic submarine model. Two types of control systems were evaluated. Results regarding the qualitative analysis of the control system, dive paths, equations of motion, and comparison with experimental paths are provided.
Date: April 15, 1954
Creator: McKann, Robert E. & Petynia, William W.
Item Type: Refine your search to only Report
open access

Impingement of Water Droplets on NACA 65A004 Airfoil at 8 Degree Angle of Attack

Description: The trajectories of droplets in the air flowing past an NACA 65AO04 airfoil at an angle of attack of 8 deg were determined. The amount of water in droplet form impinging on the airfoil, the area of droplet impingement, and the rate of droplet impingement per unit area on the airfoil surface were calculated from the trajectories and presented to cover a large range of flight and atmospheric conditions. These impingement characteristics are compared briefly with those previously reported for the … more
Date: July 1954
Creator: Brun, Rinaldo J.; Gallagher, Helen M. & Vogt, Dorothea E.
Item Type: Refine your search to only Report
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