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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.
open access

Effects of Inlet Modification and Rocket-Rack Extension on the Longitudinal Trim and Low-Lift Drag of the Douglas F5D-1 Airplane as Obtained with a 0.125-Scale Rocket-Boosted Model Between Mach Numbers of 0.81 and 1.64: TED No. NACA AD 399

Description: From Summary: "A flight investigation was conducted to determine the effects of inlet modification and rocket-rack extension on the longitudinal trim and low-lift drag of the Douglas F5D-1 airplane. The investigation was conducted with a 0.125-scale rocket-boosted model between Mach Numbers of 0.81 and 1.64. This paper presents the changes in trim angle of attack, trim lift coefficient, and low-lift drag caused by the modified inlets alone over a small part of the test Mach number range and by … more
Date: April 29, 1957
Creator: Hastings, Earl C., Jr. & Dickens, Waldo L.
open access

An experimental investigation of two methods for reducing transonic drag of swept-wing and body combinations

Description: Report presenting an investigation of a wing swept back 35 degrees in combination with one basic body and three modified bodies at a range of Mach numbers from 0.60 to 1.20. Results regarding force studies and pressure studies are provided. The bodies modified according to the Kuchenmann ring-vortex method resulted in superior aerodynamic characteristics except with regard to zero-lift drag at high supersonic Mach numbers.
Date: April 29, 1955
Creator: McDevitt, John B.
open access

Internal-film-cooling experiments with 2- and 4-inch smooth-surface tubes and gas temperatures to 2000 degrees Fahrenheit

Description: Report presenting an investigation of liquid-film cooling at a variety of air temperatures and Reynolds numbers. Results regarding the effect of coolant flow per circumferential length on liquid-cooled length, correlation of heat transfer from hot gas to liquid film for constant coolant flow per circumferential length, and generalized plot of film-cooling data based on heat-transfer correlation at constant coolant flow per circumferential length are provided.
Date: April 29, 1952
Creator: Kinney, George R.
open access

Some torsional-damping measurements of laminated beams as applied to the propeller stall-flutter problem

Description: The structural damping in the torsion mode of vibration of a series of untwisted, laminated thin beams simulating propeller blades is presented. The number of lamination were varied, as well as the bonding material and the method of joining lamination. Application of the data to the calculation of the minimum flutter speed of thin propeller blades indicates that appreciable gains in the minimum flutter speed may be obtained for laminated blades using a Cycleweld bond.
Date: April 29, 1953
Creator: Heath, Atwood R., Jr.
open access

Low-Speed Aileron Effectiveness as Determined by Force Tests and Visual-Flow Observations on a 52 Degree Sweptback Wing With and Without Chord-Extensions

Description: The results of an investigation of the effects of leading-edge chord-extensions and extensible leading-edge flaps on the low-speed aileron characteristics of a 52 degrees sweptback wing with circular-arc airfoil sections are presented. A description and illustrations of the vortex flow as it passes over the wing are included. The investigation was conducted at Reynolds numbers of 5.5 times 10(exp 6) and 1.3 times 10(exp 6) and corresponding Mach numbers of 0.11 and 0.065 for an angle-of-attack … more
Date: April 29, 1953
Creator: Cancro, Patrick A.
open access

A Theoretical Study of the Effect of Control-Deflection and Control-Rate Limitations on the Normal Acceleration and Roll Response of a Supersonic Interceptor

Description: Memorandum presenting a theoretical study of the effect of limiting the deflection and rate of deflection of the control surface on the normal acceleration and roll response to step commands for a representative, automatically controlled, supersonic, tailless interceptor. Results regarding pitch, roll, and some general comments are provided.
Date: April 29, 1953
Creator: Matthews, Howard F. & Schmidt, Stanley F.
open access

Effect of rotor leading-edge sweepback on performance of a transonic turbine

Description: Report presenting an experimental investigation to determine the effect of rotor leading-edge sweepback on the aerodynamic performance of a transonic turbine. Using an unmodified stator with the modified rotor resulted in large incidence angles at the rotor mean and tip sections.
Date: April 29, 1955
Creator: Stewart, Warner L. & Wong, Robert Y.
open access

Flight Investigation of the Supersonic Area Rule for a Straight Wing-Body Configuration at Mach Numbers Between 0.8 and 1.5

Description: Report discussing an investigation of the supersonic area rule using rocket-propelled zero-lift models of straight wing-body configurations at a range of Mach and Reynolds numbers. The body was modified with symmetrical indentations according to area-rule considerations in order to reduce wave drag. The indentations were found to have an effect at Mach numbers 1.10 and 1.41 but did not have any benefit above Mach number 1.3.
Date: April 29, 1955
Creator: Hoffman, Sherwood; Wolff, Austin L. & Faget, Maxime A.
open access

Static Longitudinal and Lateral Stability and Control Data From an Exploratory Investigation at a Mach Number of 6.86 of an Airplane Configuration Having a Wing of Trapezoidal Plan Form

Description: Memorandum presenting an investigation to determine the static longitudinal and lateral stability and control characteristics of an airplane configuration with a trapezoidal wing with modified hexagonal airfoil section and tail surfaces with 5 degrees semiangle wedge sections carried out in the 11-inch hypersonic tunnel.
Date: April 29, 1955
Creator: Fetterman, David E., Jr.; Penland, Jim A. & Ridyard, Herbert W.
open access

Free-Spinning-Tunnel Investigation of a 1/25-Scale Model of the McDonnell F3H-2N Airplane

Description: Memorandum presenting an investigation in the 20-foot free-spinning tunnel on a 1/25-scale model of the McDonnell F3H-2N airplane. The effects of control settings and movements on the erect and inverted spin and recovery characteristics of the model were determined for the clean condition. Results regarding erect spins, engine gyroscopic moments, inverted spins, spin-recovery parachute, and landing condition tests are provided.
Date: April 29, 1957
Creator: Lee, Henry A.
open access

Rotating-Stall and Rotor-Blade-Vibration Survey of a 13-Stage Axial-Flow Compressor in a Turbojet Engine

Description: Report presenting a blade-vibration and rotating-stall survey on a production turbojet engine with a 13-stage axial-flow compressor with a pressure ratio of 7 and an air flow of 120 pounds per second. Results regarding stall patterns, maximum vibratory stresses, and location of the stall zones are provided.
Date: April 29, 1955
Creator: Calvert, Howard F.; Braithwaite, Willis M. & Medeiros, Arthur A.
open access

Exploratory investigation of the low-speed static stability of a configuration employing three identical triangular wing panels and a body of equal length

Description: Report presenting an investigation at low speeds of the static-stability characteristics of a simplified model of an unusual configuration. The model had three identical triangular airfoils of low aspect ratio. Results of tests of the simplified model of the configuration are presented for a large range of angles of attack and sideslip.
Date: April 29, 1955
Creator: Delany, Noel K.
open access

Low-speed lateral-control characteristics of an unswept wing with hexagonal airfoil sections and aspect ratio 2.5 equipped with spoilers and with sharp- and thickened-trailing-edge flap-type ailerons at a Reynolds number of 7.6 x 10(exp 6)

Description: Report presenting the lateral-control characteristics of two spans of spoiler and flap-type ailerons on an unswept wing with an aspect ratio of 2.5 and hexagonal airfoil sections. Measurements of rolling moments, yawing moments, aileron hinge moments, normal forces, and balance-camber pressures for various configurations of the wing.
Date: April 29, 1952
Creator: Fitzpatrick, James E. & Woods, Robert L.
open access

Preparation of Refractories from Uranium Dioxide for Melting Uranium

Description: Attention is now being drawn to the refractory properties of the pure dioxide of uranium, which make it suitable for special applications, such as the melting of pure uranium. Properties of uranium dioxide are described as they relate to fabrication. Forming of UO{sub 2} refractories by pressing and slip casting is discussed, as well as the firing of urania refractories and the properties of fired ware. Health hazards pertaining to UO{sub 2} are briefly described.
Date: April 29, 1952
Creator: R.E. Corwin, G.B. Eyerly
open access

TRANSURANIC STUDIES STATUS AND PROBLEM STATEMENT

Description: The purpose of the Transuranics Program is to develop separation processes for the transuranic elements, primarily those produced by long-term neutron irradiation of Pu/sup 239/. The program includes laboratory process development, pilot-plant process testing, processing of 10 kg of Pu/sup 239/ irradiated to greater than 99% burn-up for plutonium and americium-curium recovery, and processing the reirradiated plutonium and americium-curium fractions. The proposed method for processing highly irr… more
Date: April 29, 1959
Creator: Leuze, R E
open access

A PRELIMINARY STUDY OF MOLTEN SALT POWER REACTORS

Description: A preliminary study of molten salt pcwer reactors was made. The most promising fuel carrier salts were the fluorides and chlorides of the alkali metals, zirconium, and beryllium. The chlorides were found to have lower melting points but were less stable and more corrosive than the fluorides. A Li/sup 7/ F- - BeF/sub 2/ mixture with ThF/sub 4/ and UF/sub 4/appeared to perform best. Of the numerous alloys tested as container material, Inconel and a nickel-- molybdenum alloy INOR-8 appeared to be … more
Date: April 29, 1957
Creator: MacPherson, H. G.; Alexander, L. G.; Carrison, D. A.; Estabrook, J. Y.; Kinyon, B. W.; Mann, L. A. et al.
open access

TECHNICAL REPORT ON THE EXPANDED HARSHAW TBP EXTRACTION PROCESS

Description: effect of various concentrations of tributyl phosphate upon pressing the uranyl nitrate distribution are included. An electrolytic method is suggested for separating uranium, neptanium, plutonium, aad americium traces from acid solutions. The yield is independent of anion concentration but dependent on pH. Conditions for quantitative separation of plutonium from various metallic admixtures are analyzed. The influence of iron was eliminated by the addition of oxalic acid. (tr-auth)
Date: April 29, 1954
Creator: Hammond, D.A.
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