National Advisory Committee for Aeronautics (NACA) - 171 Matching Results

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Aerodynamic characteristics at Mach number of 2.01 of two cruciform missile configurations having 70 degree delta wings with length-diameter ratios of 14.8 and 17.7 with several canard controls

Description: From Introduction: "The present paper contains the results of the investigation of the aerodynamic characteristics at Mach number of 2.01 of the two cruciform wing missiles equipped with larger canard controls and compares the result with that obtained previously with a smaller control."
Date: August 30, 1954
Creator: Spearman, M. Leroy & Robinson, Ross B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic characteristics in pitch of a series of cruciform-wing missiles with canard controls at a Mach number of 2.01

Description: From Introduction: "This paper presents the results of tests made at a Mach number of 2.01 to determine the effect of body length on the longitudinal characteristics (zero roll angle) for five complete configurations as well as for the bodies alone, the bodies plus wings, and the bodies plus canard surfaces. The experimental results are compared with some simple theoretical estimates."
Date: October 30, 1953
Creator: Spearman, M. Leroy
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic Characteristics of a 0.04956-Scale Model of the Convair F-102A Airplane at Mach Numbers of 1.41, 1.61, and 2.01

Description: "Tests have been made in the Langley 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.41, 1.61, and 2.01 of various arrangements of a 0.04956-scale model of the Convair F-102A airplane with faired inlets. Tests made of the model equipped with a plain wing, a wing with 6.4 percent conical camber, and a wing with 15 percent conical camber. Body modifications including an extended nose, a modified canopy, and extended afterbody fillets were evaluated" (p. 1).
Date: September 30, 1955
Creator: Spearman, M. Leroy & Driver, Cornelius
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The aerodynamic characteristics throughout the subsonic speed range of a thin, sharp-edged horizontal tail of aspect ratio 4 equipped with a constant-chord elevator

Description: From Introduction: "Recent investigations have indicated several wing plan forms, wing sections, and wing-body-tail combinations suitable for flight at supersonic speeds. One such lifting surface, a thin, sharp-edged without sweep of aspect ratio 4 and taper ratio 0.5, has been the subject of an investigation in the Ames 12-foot pressure wind tunnel. The aim of the investigation was to determine the aerodynamic characteristics of such a wing plan form throughout the range of subsonic Mach numbe… more
Date: June 30, 1949
Creator: Bandettini, Angelo & Reed, Verlin D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Altitude performance evaluation of J71-A-11 turbojet engine

Description: From Summary: "Data were obtained with five exhaust-nozzle areas and with the variable-area exhaust nozzle interlinked with the control system at conditions simulating flight at a Mach number of 0.8 and altitudes of 35,00 and 45,000 feet. Data simulating operation at zero flight Mach number at an altitude of 15,000 feet are also included. Engine component performance data are presented in addition to the overall engine performance."
Date: March 30, 1956
Creator: Useller, James W. & Pappas, George E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analysis of a Form of Peak Holding Control

Description: From Introduction: "The general objective of this report is a study of the characteristics of the described form of peak holding control. The control has not yet been used in experimental turbojet-engine study.This study is concerned with only one method of extracting the maximum amount of information from a peak output for the purpose of maintaining that peak. The criteria sought in this control process are: maintenance of peak average output, minimum duration of time in undesirable operation,… more
Date: March 30, 1956
Creator: Delio, G. J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analysis of Heat Transfer and Fluid Friction for Fully Developed Turbulent Flow of Supercritical Water With Variable Fluid Properties in a Smooth Tube

Description: From Summary: "Calculated velocity and temperature distributions, as well as relations among Nusselt number, Reynolds number, and friction factor, are presented."
Date: January 30, 1953
Creator: Deissler, R. G. & Taylor, M. F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An analysis of the forces and pressure distribution on a wing with the leading edge swept back 37.25 degrees

Description: Report presenting testing of a semispan model of a wing with the leading edge swept back 37.25 degrees, an aspect ratio of 6.04, and a taper ratio of 0.5 in order to ascertain the compressibility effects on the forces, moments, and surface pressures. Lift, drag, and pitching-moment data along with chordwise distribution of static pressure at five spanwise stations are presented for a range of Mach numbers and a constant Reynolds number. Results regarding force and moment characteristics, critic… more
Date: March 30, 1950
Creator: Edwards, George G. & Boltz, Frederick W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analysis of two-stage-turbine efficiency characteristics in terms of work and speed requirements

Description: From Introduction: "In this report two-stage-turbine efficiency characteristics are analyzed as a function of work and speed requirements in terms of the effect of changing the required mean-section velocity diagram. The fundamental assumptions and limits used in reference 2 and 3 are also used herein."
Date: August 30, 1957
Creator: Stewart, Warner L. & Wintucky, William T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Application of a channel design method to high-solidity cascades and tests of an impulse cascade with 90 degrees of turning

Description: From introduction: "A technique for application of the channel design methods of reference 11 to the design of high-solidity cascades with prescribed velocity distributions as a function of arc length along the blade-element profiles is presented herein."
Date: November 30, 1951
Creator: Stanitz, John D. & Sheldrake, Leonard J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Application of an ultraviolet spectrophotometric method to the estimation of alkylnaphthalenes in 10 experimental jet-propulsion fuels

Description: Report presenting the combustion efficiencies of 10 experimental jet-propulsion fuels that are approximately 200 degrees Fahrenheit cuts of five selected crudes available in large quantities in a turbojet engine combustor at altitude conditions.
Date: April 30, 1947
Creator: Cleaves, Alden P. & Carver, Mildred S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Blowing-type boundary-layer control as applied to the trailing-edge flaps of a 35 degree swept-wing airplane

Description: A wind-tunnel investigation was made to determine the effects on the aerodynamic characteristics of a 35 degree swept-wing airplane of applying blowing-type boundary-layer control to the trailing-edge flaps. Flight tests of a similar airplane were then conducted to determine the effects of boundary-layer control on the handling qualities and operation of the airplane, particularly during landing and take-off. The wind-tunnel and flight tests indicated that blowing over the flaps produced large … more
Date: April 30, 1958
Creator: Kelly, Mark W.; Anderson, Seth B. & Innis, Robert C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Buffeting of External Fuel Tanks at High Speeds on a Grumman F7F-3 Airplane

Description: Attempts were made to alleviate the buffeting of external fuel tanks mounted under the wings of a twin-engine Navy fighter plane. The Mach number at which the buffeting began was increased from 0.529 to 0.640 by streamlining the sway braces and increasing the lateral rigidity of the sway brace system. Further increases of the Mach number, at which buffeting began to 0.725, was obtained by moving the external fuel tank to a position under the fuselage.
Date: January 30, 1947
Creator: Turner, Howard L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Calculated Aerodynamic Loadings of M, W, and Delta Wings in Incompressible Flow

Description: Report presenting the results of theoretical incompressible-flow calculations of the spanwise lift distributions, lift-curve slopes, spanwise centers of pressure, aerodynamic centers, coefficients of damping in roll, rolling-moment coefficients due to aileron deflection, and induced-drag coefficients of twenty M, W, and delta wings.
Date: August 30, 1951
Creator: Diederich, Franklin W. & Latham, W. Owen
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Calculated Lift Distributions of a Consolidated Vultee B-36 and Two Boeing B-47 Airplanes Coupled at the Wing Tips

Description: Report presenting the calculated lift distributions and associated aerodynamic parameters for a Consolidated Vultee B-36 and two Boeing B-47 airplanes coupled at the wing tips for different angles of attack and deflections of the ailerons. Results regarding lifts, moments, and induced drags and the use of the data for calculating aerodynamic forces and equilibrium conditions are provided.
Date: November 30, 1950
Creator: Diederich, Franklin W. & Zlotnick, Martin
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Calculated Reactivity of Uranyl-Fluoride - Water Criticality Experiments

Description: Memorandum presenting a modified group method used to calculate the reactivity of the uranyl-fluoride-water experimental critical assemblies which are part of the Oak Ridge critical mass studies. The method relates the experimental slowing-down length for water to that in fluoride solutions and includes the effects of epithermal absorption and fission.
Date: March 30, 1956
Creator: Bogart, Donald & Soffer, Leonard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Characteristics of a canard-type missile configuration with an underslung scoop inlet at Mach numbers from 1.5 to 2.0

Description: Report presenting an experimental investigation of a canard-type missile configuration with an underslung scoop inlet in the 8 by 6-foot supersonic wind tunnel at a range of Mach numbers, angles of attack, control-surface deflection angles, boundary-layer-scoop heights, and inlet mass-flow ratios. Measurement of the external forces indicated that maximum lift-drag ratios were in excess of 5 at all test Mach numbers.
Date: January 30, 1953
Creator: Fradenburgh, Evan A. & Campbell, Robert C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Characteristics of swept wings at high speeds

Description: "Progress is being made in subjecting to systematic study some of the many important factors affecting the behavior of swept wings at high speeds. In this paper are presented some of the results of recent swept-wing investigations that were undertaken to determine the effects of thickness and thickness distribution, camber and twist, nose-flap deflection, and devices or 'fixes' for improving the wing pitching-moment characteristics at high lift coefficients" (p. 1).
Date: January 30, 1952
Creator: Donlan, Charles J. & Weil, Joseph
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Column Strength of Two Extruded Aluminum-Alloy H-Sections

Description: "Extruded aluminum-alloy members of various cross sections are used in aircraft as compression members either singly or as stiffeners for aluminum-alloy sheet. In order to design such members, it is necessary to know their column strength or, in the case of stiffeners, the value of the double modulus, which is best obtained for practical purposes from column tests. Column tests made on two extruded h-sections are described, and column formulas and formulas for the ratio of the double modulus to… more
Date: September 30, 1938
Creator: Osgood, William R. & Holt, Marshall
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Combustor performance with various hydrogen-oxygen injection methods in a 200-pound-thrust rocket engine

Description: Report presenting a determination of the characteristics velocity of liquid oxygen and gaseous hydrogen as a function of mixture ratio in a nominal 200-pound-thrust variable-length rocket engine. Fourteen injectors, which varied mixing and oxygen atomization, were investigated. The four types of injector designs included triplets of two hydrogen jets impinging on one oxygen jet, concentric injection with hydrogen surrounding a jet of oxygen, radial injection of oxygen with variations in hydroge… more
Date: September 30, 1958
Creator: Heidmann, M. F. & Baker, Louis, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Comparison of performance of experimental and conventional cage designs and materials for 75-millimeter-bore cylindrical roller bearings at high speed

Description: From Summary: "The results of two investigations, one to determine the relative merits of four experimental and two conventional design 75-millimeter-bore (size 215) cylindrical roller bearings and one to determine the relative merits of nodular iron and bronze as cage materials for this size and type of bearing, are presented in this report. Nine test bearings were operated over a range of dn values (product of bearing bore in mm and shaft speed in r.p.m) from 0.3 x 10(6) to 2.3 x 20(6), radia… more
Date: June 30, 1954
Creator: Anderson, William J.; Macks, E. Fred & Nemeth, Zolton N.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Comparison of theoretically and experimentally determined effects of oxide coatings supplied by fuel additives on uncooled turbine-blade temperature during transient turbojet-engine operation

Description: From Summary: "An analysis was made to permit the calculation of the effectiveness of oxide coatings in retarding the transient heat flow into turbine blades when the combustion gas temperature of a turbojet engine is suddenly changed. The analysis is checked with experimental data obtained from a turbojet engine whose blades were coated with two different coating materials (silicon dioxide and boric oxide) by adding silicone oil and tributyl borate to the engine fuel. The very thin coatings (a… more
Date: March 30, 1953
Creator: Schafer, Louis J., Jr.; Stepka, Francis S. & Brown, W. Byron
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Component Performance Investigation of J71 Experimental Turbine 9 - Effect of First-Stator Adjustment;Internal Flow Conditions of J71-97 Turbine With 87-Percent-Design Stator Area

Description: "An experimental radial-survey investigation of the J71-97 three-stage turbine equipped with a first stator having a throat area 87 percent of the design value was conducted at one turbine operating point. The first-, second-, and third-stage mass-averaged efficiencies were 0.897, 0.843, and 0.755, respectively. The corresponding over-all turbine efficiency was 0.856" (p. 1).
Date: April 30, 1957
Creator: Schum, Harold J.; Petrash, Donald A. & Davison, Elmer H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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