National Advisory Committee for Aeronautics (NACA) - 469 Matching Results

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Adaptation of Combustion Principles to Aircraft Propulsion, Volume 1, Basic Considerations in the Combustion of Hydrocarbon Fuels with Air

Description: The report summarizes source material on combustion for flight-propulsion engineers. First, several chapters review fundamental processes such as fuel-air mixture preparation, gas flow and mixing, flammability and ignition, flame propagation in both homogenous and heterogenous media, flame stabilization, combustion oscillations, and smoke and carbon formation. The practical significance and the relation of these processes to theory are presented. A second series of chapters describes the observ… more
Date: April 1, 1955
Creator: Barnett, Henry C. & Hibbard, Robert R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Additional Results in a Free-Flight Investigation of Control Effectiveness of Full-Span, 0.2-Chord Plain Ailerons at High Subsonic, Transonic, and Supersonic Speeds to Determine Some Effects of Wing Sweepback, Aspect Ratio, Taper, and Section Thickness Ratio

Description: Report discussing an aerodynamic control effectiveness study using free-flight, rocket-propelled test vehicles. Information about the effects of wing sweepback, aspect ratio, taper ratio, and section thickness ratio on the rolling effectiveness of full-span, sealed ailerons is provided.
Date: April 23, 1948
Creator: Sandahl, Carl A. & Strass, H. Kurt
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The aerodynamic characteristics at transonic speeds of a model with a 45 degree sweptback wing, including the effect of leading edge slats and a low horizontal tail

Description: Report presenting an investigation in the 16-foot transonic tunnel to determine the effects of leading-edge slats on the aerodynamic and longitudinal stability characteristics of a model of a swept-wing fighter-type airplane. Two different spanwise extents of leading-edge slats were tested, from 35 to 95 percent semispan and from 46 to 95 percent semispan. Results regarding the lift characteristics, drag characteristics and lift-drag ratios, stability characteristics, and flow-study pictures ar… more
Date: April 5, 1954
Creator: Runckel, Jack F. & Schmeer, James W.
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 Transonic Speeds

Description: "Tests have been conducted in the Langley 8-foot transonic tunnel on a 0.04956-scale model of the Convair F-102A airplane which employed an indented and extended fuselage, cambered wing leading edges, and deflected wing tips. Force and moment characteristics were obtained for Mach numbers from 0.60 to 1.135 at angles of attack up to 20 degrees. In addition, tests were made over a limited angle-of-attack range to determine the effects of the cambered leading edges, deflected tips, and a nose sec… more
Date: April 11, 1955
Creator: Tempelmeyer, Kenneth E. & Osborne, Robert S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic characteristics of a 60 degree delta wing having a half-delta tip control at a Mach number of 4.04

Description: From Introduction: "Numerous tests of tip controls on delta wings at transonic and low supersonic speeds have shown that such configurations provide satisfactory rolling-moment effectiveness, and that the hinge can be controlled by proper location of the hinge line (ref. 1). The purpose of the present tests is to determine the characteristics of such a configuration at Mach number of 4.04 and a Reynolds number of 5.8 X 10^6, based on the wing mean aerodynamic chord."
Date: April 25, 1955
Creator: Ulmann, Edward F. & Smith, Fred M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic characteristics of a cruciform-wing missile with canard control surfaces and of some very small span wing-body missiles at a Mach number of 1.41

Description: Report presenting an investigation to determine the aerodynamic characteristics of a cruciform 70 degree delta-wing missile configuration with 70 degree delta canard control surfaces at M = 1.41 in the 4- by 4-foot supersonic pressure tunnel. Modifications to the configuration included variation of the body length and canard area and the substitution of a series of very small span wings for the cruciform delta wings and canard controls.
Date: April 12, 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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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
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Aerodynamic characteristics of a wing with quarter-chord line swept back 35 degrees, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section: Transonic-bump method

Description: From Introduction: "This paper presents the results of the investigation of wing-alone and wing-fuselage combinations employing a wing with the quarter-chord line swept back 35^o, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section."
Date: April 21, 1949
Creator: Sleeman, William C., Jr. & Becht, Robert E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic Loads on an External Store Adjacent to a 60 Degree Delta Wing at Mach Numbers From 0.75 to 1.96

Description: Report presenting an investigation to determine separately the aerodynamic characteristics of a Douglas Aircraft Company store and a semispan delta-wing-fuselage configuration in the presence of one another. The store was located at the 50-percent-semispan station with the store nose both ahead of and behind the wing leading edge for two longitudinal and three vertical positions.
Date: April 24, 1956
Creator: Hadaway, William M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamics of slender bodies at Mach number of 3.12 and Reynolds numbers from 2 x 10(exp 6) to 15 x 10(exp 6) 3: boundary layer and force measurements on a slender cone-cylinder body of revolution

Description: Report presenting an experimental investigation to determine the aerodynamic characteristics of a slender cone-cylinder body of revolution in the 1- by 1-foot supersonic wind tunnel. Viscous drag and three component forces were measured at Mach number 3.12 and a range of Reynolds numbers and angles of attack. Results regarding pressure distributions, boundary layer, and forces are provided.
Date: April 6, 1953
Creator: Jack, John R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aeronautical interference effects on normal and axial force coefficients of several engine-strut-body configurations at Mach numbers of 1.8 and 2.0

Description: Report presenting an investigation of the aerodynamic interference effects associated with a missile configuration, consisting of a pointed body of revolution with one or two ramjet engines strut-mounted in a vertical plane through the center line of the body, at several engine locations relative to the body and a range of angles of attack. The experimental data indicated increases in slope of the normal force curve with outward movement of the engines. Results regarding the characteristics of … more
Date: April 28, 1952
Creator: Kremzier, Emil J. & Dryer, Murray
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Air-Flow Behavior Over the Wing of an XP-51 Airplane as Indicated by Wing-Surface Tufts at Subcritical and Supercritical Speeds

Description: Report presenting the air-flow behavior over the wing of an XP-51 airplane including photographs of tufts attached to the wing surface and chordwise pressure distributions. A comparison of tuft studies from flight results are compared with results from wind-tunnel testing. Three types of flow were observed: steady flow, unsteady flow, and break-away flow are provided.
Date: April 24, 1947
Creator: Beeler, De E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Air-Stream Surveys in the Vicinity of the Tail of a 1/8.33-Scale Powered Model of the Republic XF-12 Airplane

Description: "The XF-12 airplane was designed by Republic Aviation Corporation to provide the Army Air Forces with a high performance, photo reconnaissance aircraft. A series of air-stream surveys were made n the vicinity of the empennage of a 1/8.33-scale powered model of the XF-12 airplane in the Langley 19-foot pressure tunnel. Surveys of the vortical-tail region were made through a range of yaw angles of plus or minus 20 degrees at a high and low angle of attack" (p. 1).
Date: April 8, 1947
Creator: Foster, Gerald V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Altitude performance and operational characteristics of 29-inch-diameter tail-pipe burner with several fuel systems and fuel-cooled stage-type flame holders on J35-A-5 turbojet engine

Description: An investigation of tail-pipe burning was conducted in the NACA Lewis altitude wind tunnel with a full-scale turbojet engine and an 29-inch-diameter tail-pipe burner. Effects of fuel distribution and number and arrangement of stages on performance and operational characteristics of several fuel-cooled flame holders are presented and discussed. Operation with a three-stage flame holder having the large stage upstream was the most efficient. Combustion efficiency was slightly increased at high al… more
Date: April 28, 1950
Creator: Golladay, Richard L. & Bloomer, Harry E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Altitude performance of AN-F-58 fuels in J33-A-21 single combustor

Description: Report discussing three fuels conforming to AN-F-58 specification were investigated in order to determine the influence of boiling temperatures and aromatic content on altitude performance in single combustor of a 4600-pound-thrust turbojet engine.
Date: April 8, 1949
Creator: Dittrich, Ralph T. & Jackson, Joseph L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Altitude performance of pentaborane - JP-4 fuel blends in a modified J47 combustor

Description: From Introduction: "Experimental investigations of the combustion characteristics of diborane, pentaborane, and pentaborane-hydrocarbon blends in modified turbojet combustors have been conducted at this laboratory at the request of the Bureau of Aeronautics, Department of the Navy, as part of Project Zip. Results of these single-combustor tests are presented in references 2 to 5."
Date: April 17, 1957
Creator: Branstetter, J. Robert & Kaufman, Warner B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Altitude Starting Characteristics of an Afterburner With Autoignition and Hot-Streak Ignition

Description: "Ignition of the fuel-air mixture in an afterburner of turbojet engine at altitude has often proved to be a different problem to solve. Electrical ignition has not proven satisfactory because of the unreliability of such systems (ref. 1). The ignition data reported herein were obtained for two after-burner configurations. Autoignition data are included for both configurations and hot-streak-ignition data, for only one. "
Date: April 6, 1953
Creator: Renas, P. E.; Harvey, R. W., Sr. & Jansen, E. T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Altitude-Wind-Tunnel Investigation of the 19B-2, 19B-8 and 19XB-1 Jet- Propulsion Engines: 4 - Analysis of Compressor Performance

Description: "Investigations were conducted in the Cleveland altitude wind tunnel to determine the performance and operational characteristics of the 19B-2, 19B-8, and 19XS-1 turbojet engines. One objective was to determine the effect of altitude, flight Mach number, and tail-pipe-nozzle area on the performance characteristics of the six-stage and ten-stage axial-flow compressors of the 19B-8 and 19XB-1 engines, respectively, The data were obtained over a range of simulated altitudes and flight Mach numbers… more
Date: April 25, 1947
Creator: Dietz, Robert O. & Kuenzig, John K.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Altitude-Wind-Tunnel Investigation of the 19B-2, 19B-8, and 19XB-1 Jet Propulsion Engines, 4 - Performance and Windmilling Drag Characteristics

Description: The performance characteristics of the 19B-8 and 19XB-1 turbojet engines and the windmilling-drag characteristics of the 19B-6 engine were determined in the Cleveland altitude wind tunnel. The investigations were conducted on the 19B-8 engine at simulated altitudes from 5000 to 25,000 feet with various free-stream ram-pressure ratios and on the 19XB--1 engine at simulated altitudes from 5000 to 30,000 feet with approximately static free-stream conditions.
Date: April 9, 1947
Creator: Fleming, William A. & Dietz, Robert O., Jr.
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
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