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Preliminary investigation of control characteristics at transonic speeds of a tapered 45 degree sweptback wing of aspect ratio 3 having a horn-balanced full-span control

Description: Report presenting an investigation at transonic speeds in the 7- by 10-foot tunnel to determine hinge-moment and effectiveness characteristics of a horn-balanced control on an aspect-ratio-3, 45 degree sweptback wing. The investigation was extended through the transonic speed range by testing in the high velocity field over a reflection plane on the sidewall of the tunnel.
Date: April 10, 1952
Creator: Lowry, John G. & Fikes, Joseph E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds: Twisted and cambered triangular wing of aspect ratio 2 with NACA 0005-63 thickness distribution

Description: Report presenting the results of a wind-tunnel investigation at subsonic and supersonic Mach numbers to determine the aerodynamic characteristics of a wing-body combination with a triangular wing of aspect ratio 2. The mean surface of the wing was twisted and cambered to support a nearly elliptical span load distribution at Mach number 1.53 and a lift coefficient of 0.25. Lift, drag, and pitching moment are presented for a range of Mach and Reynolds numbers.
Date: April 10, 1952
Creator: Heitmeyer, John C. & Petersen, Robert B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimental investigation of the drag of 30 degree, 60 degree, and 90 degree cone cylinders at Mach numbers between 1.5 and 8.2

Description: Report presenting the total drag coefficients of 60 degree cone cylinders of fineness ratio 2.07 measured in free flight from Mach numbers of 1.5 to 8.2. Results regarding the smooth 60 degree cone cylinder, rifled models, and discontinuity lines in the shadowgraph pictures are provided.
Date: April 25, 1952
Creator: Seiff, Alvin & Sommer, Simon C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Low-speed aerodynamic characteristics of a large-scale 45 degree swept-back wing with partial-span slats, double-slotted flaps, and ailerons

Description: Report presenting experimental data from force and pressure tests on a large-scale, semispan, wing-fuselage model. Longitudinal force and moment characteristics are given for the model with various combinations of slat spans. The wing had 45 degrees of sweepback, an aspect ratio of 6, a taper ratio of 0.5, and an NACA 64A010 section normal to the quarter-chord line of the unswept panel and had partial-span slats, aileron, and double-slotted flaps equipped.
Date: April 28, 1952
Creator: James, Harry A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Longitudinal Stability and Drag Characteristics at Mach Numbers From 0.75 to 1.5 of an Airplane Configuration Having a 60 Degree Swept Wing of Aspect Ratio 2.24 as Obtained From Rocket-Propelled Models

Description: Report discussing testing of a rocket-propelled airplane configuration model and a drag model, each with a 60 degree swept wing of aspect ratio 2.24, and different fuselages, at a Mach number range of 0.75 to 1.50. Information about the longitudinal stability, control, and drag characteristics and minimum-drag characteristics is presented.
Date: April 11, 1952
Creator: Vitale, A. James; McFall, John C., Jr. & Morrow, John D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of the hydrodynamic stability and resistance of two streamline fuselages

Description: Report presenting an investigation of a dynamic model to determine the effects of hull form, gross load, and aerodynamic trimming moments on the trim limits, trim, hydrodynamic moment, hydrodynamic resistance, total resistance, and rise of two streamline fuselages modified by chine strips. Results regarding effects of hull form and effects of gross load are provided.
Date: April 9, 1952
Creator: Weinflash, Bernard & Shuford, Charles L., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Transonic Drag Characteristics and Pressure Distribution on the Body of a Wing-Body Combination Consisting of a Body of Revolution of Fineness Ratio 12 and a Wing Having Sweepback of 45 Degrees, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Sections

Description: Report presenting free-fall testing of the airplane configuration described in the title to evaluate certain new testing techniques for near sonic speeds. Results regarding the drag measurements and pressure data are provided. The data obtained from this test is also compared to free-fall tests in the high-speed tunnel and for a rocket-powered free-flight model, and the results show generally satisfactory agreement.
Date: April 8, 1952
Creator: Kurbjun, Max C. & Thompson, Jim Rogers
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The effect of bluntness on the drag of spherical-tipped truncated cones of fineness ratio 3 at Mach numbers 1.2 to 7.4

Description: Report presenting an investigation of the drag of spherically blunted conical models of fineness ratio 3 at a range of Mach and Reynolds numbers. Results of the tests showed that slightly blunted models had less drag than cones of the same fineness ratio through the Mach number range. Results regarding the total drag, wave drag, and viscous effects are provided.
Date: April 25, 1952
Creator: Sommer, Simon C. & Stark, James A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary investigation of the drag characteristics of the NACA RM-10 missile at Mach numbers of 1.40 and 1.59 in the Langley 4- by 4-foot tunnel

Description: Report presenting testing of a parabolic body of revolution in the 4- by 4-foot supersonic tunnel at two Mach numbers. The investigation included the effects of Reynolds number, fins, internal contour of body base, and two support systems on body pressure and force drag at an angle of attack of 0 degrees.
Date: April 18, 1952
Creator: Hasel, Lowell E.; Sinclair, Archibald R. & Hamilton, Clyde V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Performance of an impulse-type supersonic compressor with stators

Description: Report presenting testing of an impulse-type supersonic compressor rotor with stators tested in Freon-12 over a range of equivalent tip speeds and weight flows. A static pressure ratio of 1.83 and an efficiency of 84.7 percent were obtained at 69.1 percent of the design speed of 1604 feet per second in air.
Date: April 28, 1952
Creator: Klapproth, John F.; Ullman, Guy N. & Tysl, Edward R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Relations between fuel properties and combustion carbon deposition

Description: Report discussing some methods for predicting the carbon-forming propensity of turbojet-engine fuels from results of simple laboratory tests of the fuels. The prediction of carbon deposition from fuel characteristics including aromatic content, hydrogen-carbon ratio, distillation temperatures, gravity, and aniline point from several empirical laboratory carbon-deposition tests are provided. Results regarding fuel composition and volatility, related fuel properties, empirical laboratory tests, a… more
Date: April 14, 1952
Creator: Jonash, Edmund R.; Wear, Jerrold D. & Hibbard, Robert R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The aerodynamic characteristics of a supersonic aircraft configuration with a 40 degree sweptback wing through a Mach number range from 0 to 2.4 obtained from various sources

Description: "A summary and analysis have been made of the results of various investigations to determine the aerodynamic characteristics of a supersonic aircraft configuration. The configuration has a wing with 40 degree sweepback at the quarter-chord line, aspect ratio 4, taper ratio 0.5, and 10-percent-thick circular-arc sections normal to the quarter-chord line. Experimental data were available for a Mach number range from 0.16 to 2.32. Results obtained from wing-flow, rocket-model, transonic-bump, and … more
Date: April 11, 1952
Creator: Spearman, M. Leroy & Robinson, Ross B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary investigation at transonic speeds of the effect of balancing tabs on the hinge-moment and other aerodynamic characteristics of a full-span flap on a tapered 45 degree sweptback wing of aspect ratio 3

Description: Report presenting an investigation at transonic speeds of the control balancing characteristics of three tabs on a full-span flap on an aspect-ratio-3, 45 degree sweptback wing. The results indicated that all the tabs tested, inset, attached, or detached, would balance the flap hinge moments throughout the speed range.
Date: April 8, 1952
Creator: Lockwood, Vernard E. & Fikes, Joseph E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Ames supersonic free-flight wind tunnel

Description: From Introduction: "Because of the unusual nature of this equipment, and because it is proving to be very useful for certain kinds of aerodynamic research, this report has been prepared. It contains a description of the equipment and its use to obtain aerodynamic coefficients. The imperfections in the wind-tunnel air stream and their effect on model tests are also discussed."
Date: April 25, 1952
Creator: Seiff, Alvin; James, Carlton S.; Canning, Thomas N. & Boissevain, Alfred G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Low speed stability characteristics of a complete model with a wing of W plan form

Description: Report presenting an investigation of the low-speed static stability characteristics of a complete model equipped with a W wing. The lift-curve slope of the wing-fuselage combination was found to be in good agreement with that predicted by available wing-alone theory. Results regarding the longitudinal characteristics, wing-juncture modifications, and lateral and directional stability characteristics are provided.
Date: April 23, 1952
Creator: Polhamus, Edward C. & Becht, Robert E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Full-scale wind-tunnel investigation of the effects of wing modifications and horizontal-tail location on the low-speed static longitudinal characteristics of a 35 degree swept-wing airplane

Description: Report presenting tests made in the 40- by 80-foot wind tunnel to evaluate the effects of wing modifications on the static longitudinal characteristics of a 35 degree swept-wing airplane. The wing modifications were designed to replace existing wing slats as low-speed high-lift devices. Results regarding the two-dimensional tests, full-scale tests, design of wing modification 1, test results of the airplane, and a comparison of test results with predictions are provided.
Date: April 3, 1952
Creator: Maki, Ralph L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Some factors affecting fabrication and high-temperature strength of molybdenum disilicide

Description: Report presenting an investigation of the properties of molybdenum disilicide in which a fine-grain material and a large-grain material were produced using different methods. Results regarding the fine-particle sintered material, coarse-grain, hot-pressed material, a comparison of the two materials, and the effect of oxygen on sintering and mechanical properties are provided.
Date: April 17, 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 a 10-Stage Subsonic Axial-Flow Research Compressor 1: Aerodynamic Design

Description: Memorandum presenting a 10-stage axial-flow compressor designed for use as a research unit in which the problems associated with the compounding of high performance stages could be studied. The overall performance characteristics of the compressor, as determined experimentally, are included.
Date: April 28, 1952
Creator: Johnsen, Irving A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The effects on the aerodynamic characteristics of varying the wing thickness ratio of a triangular wing-body configuration at transonic speeds from tests by the NACA wing-flow method

Description: Testing occurred using the NACA wing-flow method at a range of Mach numbers to determine the aerodynamic characteristics of three triangular wing-fuselage models which differed only in wing thickness-chord ratio. The wings had an aspect ratio of 2.31 with 6-, 9-, and 12-percent-thick biconvex sections and a fuselage with a fineness ratio of 12. Results regarding the normal force, chord force, and pitching moment for various angles of attack.
Date: April 2, 1952
Creator: Hall, Albert W. & McKay, James M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wing load distribution on a swept wing airplane in flight at Mach numbers up to 1.11, and comparison with theory

Description: Report presenting flight tests to determine the pressure distribution over the wing of a swept-wing jet-propelled airplane over the flight range of lift coefficients for Mach numbers up to 1.11. Results regarding the section characteristics, load distribution, and trailing-edge loads are provided.
Date: April 14, 1952
Creator: Rolls, L. Stewart & Matteson, Frederick H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Some Effects of Changing Solidity by Varying the Number of Blades on Performance of an Axial Flow Compressor Stage

Description: Report presenting an investigation to determine some of the basic problems and effects involved in a change of solidity accomplished by a change in the number of blades in an axial-flow-compressor rotor row and in a complete stage. Results regarding rotor performance and complete stage performance are provided.
Date: April 14, 1952
Creator: Standahar, Raymond M. & Serovy, George K.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Experimental Investigation of the Combustion Properties of a Hydrocarbon Fuel and Several Magnesium and Boron Slurries

Description: Memorandum presenting an investigation conducted to explore the characteristics of metal-hydrocarbon combustion, to determine the effect of fuel-air ratio on the combustion efficiency, and to determine how the metal and hydrocarbon separately contribute to the overall combustion of several slurries. Results regarding an evaluation of the sampling method, combustion efficiency, effective metal weight fraction, effective hydrogen-carbon ratio, and heat of combustion per pound of air are provided.
Date: April 28, 1952
Creator: Lord, Albert M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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