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An Aerodynamic Analysis of the Autogiro Rotor With a Comparison Between Calculated and Experimental Results

Description: This report presents an extension of the autogiro theory of Glauert and Lock in which the influence of a pitch varying with the blade radius is evaluated and methods of approximating the effect of blade tip losses and the influence of reversed velocities on the retreating blades are developed. A comparison of calculated and experimental results showed that most of the rotor characteristics could be calculated with reasonable accuracy, and that the type of induced flow assumed has a secondary ef… more
Date: January 17, 1934
Creator: Wheatley, John B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic Heating and Boundary-Layer Transition on a 1/10-Power Nose Shape in Free Flight at Mach Numbers Up to 6.7 and Free-Stream Reynolds Numbers Up To 16 x 10(Exp 6)

Description: Report presenting testing of a modified 1/10-power nose shape in free flight at Mach numbers up to 6.7. Measured heating rates were presented and compared with calculated values. Results regarding transition and comparison with previous investigations are provided.
Date: June 17, 1957
Creator: Garland, Benjamine J.; Swanson, Andrew G. & Speegle, Katherine C.
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 an Unswept Wing at Mach Numbers Between 0.75 and 1.96

Description: Report presenting an investigation to determine the aerodynamic characteristics of a sting-mounted Douglas Aircraft Company store in the presence of an unswept semispan cantilevered wing of aspect ratio 4.0. Results regarding wing loads and store loads are provided.
Date: February 17, 1956
Creator: Hadaway, William M.
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 an Unswept Wing at Mach Numbers Between 0.75 and 1.96

Description: Memorandum presenting an investigation in the blowdown tunnel of the pressure tunnel to determine the aerodynamic characteristics of a sting-mounted Douglas Aircraft Company store in the presence of, but not attached to, an unswept semispan cantilevered wing of aspect ratio 4.0. The influence of the store on the aerodynamic characteristics of the wing was also obtained.
Date: February 17, 1956
Creator: Hadaway, William M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic Performance and Static Stability and Control of Flat-Top Hypersonic Gliders at Mach Numbers From 0.6 to 18

Description: Memorandum presenting a study of aerodynamic performance and static stability and control at hypersonic speeds. In the first part of the study, the effect of interference lift is investigated by tests of asymmetric models with conical fuselages and arrow plan-form wings. In the second part, the aerodynamic performance and static stability and control characteristics of a hypersonic glider are investigated in somewhat greater detail.
Date: September 17, 1958
Creator: Syvertson, Clarence A.; Gloria, Hermilo R. & Sarabia, Michael F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic Performance of Several Techniques for Spike-Position Control of a Blunt-Lip Nose Inlet Having Internal Contraction; Mach Numbers of 0.63 and 1.5 to 2.0

Description: Memorandum presenting a study to determine locations of pressure sensors for controlling the spike position of a blunt-lip, axisymmetric inlet with internal contraction. The inlet performance was determined at Mach numbers of 0.63 and 1.5 to 2.0 for airflow schedules corresponding to those of a given turbojet engine over a wide range of ambient temperatures. The use of the ratio of a throat static pressure to either a local total or the spike-tip total pressure provided a signal that could set … more
Date: September 17, 1957
Creator: Anderson, Arthur A. & Weinstein, Maynard I.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamics of Oscillating Control Surfaces at Transonic Speeds

Description: Memorandum presenting a discussion of oscillating flap-type and all-movable controls with particular emphasis on the aerodynamic forces and moments at transonic speeds. Hinge-moment results from recent wind-tunnel and rocket-powered-model tests are summarized for trailing-edge flap-type controls to illustrate the effects of control hinge-line position and profile shape on one-degree-of-freedom flutter of this type of control.
Date: June 17, 1957
Creator: Thompson, Robert F. & Clevenson, Sherman A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Airfoil profiles for minimum pressure drag at supersonic velocities: Application of shock-expansion theory, including consideration of hypersonic range

Description: From Summary: "A comparison of optimum profiles determined by the shock-expansion method of this report with corresponding profiles determined by the linearized-theory method of a previous report shows only small differences in shape at Mach numbers up to infinity even though the linearized theory at high supersonic Mach numbers breaks down completely insofar as the drag of the profile is concerned. Curves are presented which show that for thin airfoils the use of a trailing-edge thickness cons… more
Date: September 17, 1952
Creator: Chapman, Dean R.
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-wind-tunnel investigation of several afterburner configurations having moderately high burner-inlet velocities

Description: From Introduction: "The screech investigation, reported in reference 1, included a large number of afterburner configurations. Several of these configurations are presented herein to show the effects of afterburner-inlet gas whirl pattern, flame-holder design, and fuel distribution on performance as determined by combustion efficiency, augmented thrust ratio, and special fuel consumption."
Date: November 17, 1954
Creator: Schulze, F. W.; Bloomer, H. E. & Miller, R. R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Analog Study of the Influence of Internal Modifications to a Wing Leading Edge on Its Transient Temperature Rise During Highspeed Flight

Description: Memorandum presenting an investigation made with an electrical heat-flow analog to determine the effect of internal modifications to a wing leading edge on the surface-temperature rise and temperature distribution for conditions of transient aerodynamic heating at high supersonic speeds. Results regarding the leading-edge temperature rise, influence of conduction on leading-edge temperature for skins of uniform thickness, and surface-temperature distribution are provided.
Date: March 17, 1958
Creator: Neel, Carr B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analysis of experimental sea-level transient data and analog method of obtaining altitude response for turbine-propeller engine with relay-type speed control

Description: From Introduction: "This report shows correlation between actual transient data obtained from the engine and solutions to a simulated system set up on an analog computer. Data are presented for response of engine speed to changes in set speed when the power plant was being controlled by a relay-type electronic governor that acted to maintain set speed by varying propeller pitch. Correlation obtained for sea-level conditions between actual time data and analog solutions is discussed."
Date: May 17, 1951
Creator: Vasu, George & Pack, George J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Analysis of Lateral Stability in Power-Off Flight With Charts for Use in Design

Description: "The aerodynamic and mass factors governing lateral stability are discussed and formulas are given for their estimation. Relatively simple relationships between the governing factors and the resulting stability characteristics are presented. A series of charts is included with which approximate stability characteristics may be rapidly estimated" (p. 1).
Date: November 17, 1936
Creator: Zimmerman, Charles H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analysis of Turbulent Heat Transfer, Mass Transfer, and Friction in Smooth Tubes at High Prandtl and Schmidt Numbers

Description: From Introduction: "In the analysis given herein, which was made at the NACA Lewis laboratory, the expression for eddy diffusivity given in reference 1 is modified in order to account for the effect of kinematic viscosity in reducing the turbulence in the region close to the wall. The effects of variable viscosity and of length-to-diameter ratio are also investigated."
Date: February 17, 1954
Creator: Deissler, Robert G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analytical Investigation of Ram-Jet-Engine Performance in Flight Mach Number Range From 3 to 7

Description: "An analytical investigation was made of the performance of isolated ram-jet engines in the flight Mach number range from 3 to 7 for two types of diffuser, a high-efficiency diffuser, and a normal-shock diffuser. The fuel was assumed to be a hydrocarbon similar to gasoline. The conclusions reached are: (1) a design altitude of about 100,000 feet is desirable for a high-efficiency high Mach number ram jet on the basis of engine construction and performance; and (2) although greater thrust could … more
Date: October 17, 1951
Creator: Evans, Philip J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Analytical Investigation of the Heat Losses from a U.S. Navy K-Type Airship

Description: From Summary: "The heat losses from the envelope surface of a U.S. Navy K-type airship are evaluated to determine if the use of heat is a feasible means of preventing ice and snow accumulations on lighter-than-air craft during flight and when moored uncovered. Consideration is given to heat losses in clear air (no liquid water present in the atmosphere) and in probable conditions of icing and snow. The results of the analysis indicate that the amount of heat required in flight to raise the surf… more
Date: February 17, 1947
Creator: Hillendahl, Wesley H. & George, Ralph E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analytical Investigation of Turbines With Adjustable Stator Blades and Effect of These Turbines on Jet-Engine Performance

Description: From Introduction: "A comparison is also made of the actual performance of two contemporary jet engines with estimated performance, assuming the engines were equipped with adjustable-angle stators and adjustable exhaust nozzles. Charts are presented that aid in estimating the performance of adjustable-stator turbines."
Date: July 17, 1950
Creator: Silvern, David H. & Slivka, William R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Analytical Study of the Comparative Performance of Four Air-Induction Systems for Turbojet-Powered Airplanes Designed to Operate at Mach Numbers Up to 1.5

Description: Memorandum presenting a study made to ascertain some of the operational characteristics of four types of air-induction systems for a turbojet-powered airplane intended to operate at a range of Mach numbers at an altitude of 35,332 feet. The investigation included air-induction systems with and wthout ramps to produce oblique shock waves, with fixed and variable inlet areas, and with divergent diffusers.
Date: June 17, 1952
Creator: Blackaby, James R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Analytical Study of the Effects of Increasing Fin Chord on the Lift and Longitudinal Stability Characteristics of Constant-Span Fin-Body Combinations of Fineness Ratio 14

Description: Report presenting an analysis to determine the effect of increasing the fin-chord length while holding the span constant on the lift and longitudinal static stability of fin-body combinations. Rectangular and triangular fins with spans of 2 and 3 body diameters in combination with a fineness-ratio-14 ogive-cylinder body were tested.
Date: January 17, 1957
Creator: English, Roland D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Annual Report of the National Advisory Committee for Aeronautics (42nd): Administrative Report without Technical Reports

Description: Report consisting of a summary and papers covering the activities occurring during the year 1956 in the National Advisory Committee for Aeronautics. The paper is broken up into letter of transmittal, letter of submittal, the technical activities, committee organization and membership, and the financial report.
Date: October 17, 1956
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Arrangement of Bodies of Revolution in Supersonic Flow to Reduce Wave Drag

Description: "The wave drag of a combination of slender bodies of revolution at zero angle of attack is studied with a view to determining the arrangements for which the total drag is a minimum. Linearized theory is used to calculate the pressure distribution in the field surrounding the bodies. The interference drag coefficient is computed for different arrangements. The special cases of two bodies and of a three-body combination with bilateral symmetry are considered" (p. 1).
Date: December 17, 1951
Creator: Friedman, Morris D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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