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Lift and drag data for 30 pusher-propeller shaft housings on an NACA 65,3-018 airfoil section

Description: Report presenting tests in the two-dimensional low-turbulence pressure tunnel to study the interference effects of various pusher-propeller shaft-housing combinations on a low-drag airfoil. Thirty different combinations were tested, variations being made in shaft size, shape, angle, and fillet.
Date: November 1943
Creator: Abbott, Frank T., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Variation with Mach Number of Static and Total Pressures Through Various Screens

Description: "Tests were conducted in the Langley 24-inch highspeed tunnel to ascertain the static-pressure and total-pressure losses through screens ranging in mesh from 3 to 12 wires per inch and in wire diameter from 0.023 to 0.041 inch. Data were obtained from a Mach number of approximately 0.20 up to the maximum (choking) Mach number obtainable for each screen. The results of this investigation indicate that the pressure losses increase with increasing Mach number until the choking Mach number, which c… more
Date: February 1946
Creator: Adler, Alfred A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of Pressure on Thermal Conductance of Contact Joints

Description: Technical note presenting tests conducted to determine the factors influencing the thermal conductance across the interface formed between stationary plane surfaces of 75S-T6 aluminum-alloy and AISI Type 416 stainless-steel blocks. The types of joints investigated included bare metal-to-metal contact, contact surfaces separated by a good conductor (brass), and contact surfaces separated by a thin sheet of insulation (asbestos). Results regarding the effect of surface roughness, pressure, mean i… more
Date: May 1955
Creator: Barzelay, Martin E.; Tong, Kin Nee & Holloway, George F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Impact Waves and Detonation: Part 2

Description: A continuation of a previous technical memorandum regarding impact waves and detonation. This particular report focuses on the applications to detonation under several different conditions, including variations in pressure.
Date: March 1929
Creator: Becker, R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Exploratory Investigation of the Flow in the Separated Region Ahead of Two Blunt Bodies at Mach Number 2

Description: Memorandum presenting an investigation of flow separation from a flat plate ahead of two blunt two-dimensional bodies in detail at Mach number 2. Interferograms were obtained for the separated regions, and the pitot-pressure distribution and flow directions were surveyed in one of the regions. Results regarding recovery factors and static pressures, density, total pressure, Mach number distribution, and flow-direction survey are provided.
Date: June 30, 1955
Creator: Bernstein, Harry & Brunk, William E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Free-flight pressure measurements over a flare-stabilized rocket model with a modified Von Karman nose for Mach numbers up to 4.3

Description: Report presenting pressures measured during a free-flight test at zero angle of attack over a rocket model with a modified Von Karman nose in combination with a cylindrical center section and a 10 degree half-angle flare.
Date: January 13, 1958
Creator: Bland, William M., Jr. & Kolenkiewicz, Ronald
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Analysis of Pressure Studies and Experimental and Theoretical Downwash and Sidewash Behind Five Pointed-Tip Wings at Supersonic Speeds

Description: The following report covers an investigation that was done to supplement available experimental data on flow fields behind wings of an aircraft at supersonic speeds, as well as to furnish more quantitative information on the choice of the theoretical method for a given configuration and the accuracy to be expected when using such a method.
Date: April 21, 1954
Creator: Boatright, William B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Analysis of Pressure Studies and Experimental and Theoretical Downwash and Sidewash Behind Five Pointed-Tip Wings at Supersonic Speeds

Description: "Flow-angle and pressure surveys behind five, thin, pointed-tip wings of varying plan form have been made at Mach numbers 1.62 and 2.41. Schlieren studies at a Mach number 1.93 for the same five plan-form wings were made to illustrate the behavior of the vortex sheet. The surveys were conducted at 1.5, 3, and 4 root chords behind three triangular wings of 50 degree, 63 degree, and 72 degree leading-edge sweep angle, and behind the 50 degree triangular wing reversed" (p. 1067).
Date: January 22, 1954
Creator: Boatright, William B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Characteristics of a 40 Degree Cone for Measuring Mach Number, Total Pressure, and Flow Angles at Supersonic Speeds

Description: Note presenting an experimental investigation conducted to determine the characteristics of a 40 degree cone for use in the measurement of Mach number, total pressure, and flow angles. The cone had a total-pressure orifice at the apex and four equally spaced static-pressure orifices on the surface and pressure measurements were taken at a range of angles of pitch, Mach numbers, and Reynolds numbers. Results regarding cone pressure distribution, determination of Mach number, determination of tot… more
Date: May 1957
Creator: Centolanzi, Frank J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Canopy loads investigation for the F6F-3 airplane

Description: Report presenting an investigation of surface static pressures over the outer and inner surfaces of the cockpit canopies on the Grumman F6F-3, Curtiss SB2C-4E, and Grumman F8F-1 airplanes in the full-scale tunnel. Results regarding the external pressure distribution and internal static pressure are provided.
Date: April 14, 1947
Creator: Cocke, Bennie W., Jr. & Czarnecki, K. R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Digital Automatic Multiple Pressure Recorder

Description: Note presenting a machine which will automatically measure and record 100 pressures in a range from 5 to 65 inches of mercury, in approximately 2.5 minutes, to an accuracy of 0.1 inch of mercury. The method used is to compare the unknown pressures with a scanning pressure whose value at any instant is known in digitalized form.
Date: January 1953
Creator: Coss, Bert A.; Daykin, D. R.; Jaffe, Leonard & Sharp, Elmer M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Performance Characteristics of an Axial-Flow Transonic Compressor Operating Up to Tip Relative Inlet Mach Number of 1.34

Description: Performance data are presented for a transonic axial-flow compressor rotor designed to operate at a tip speed of 1300 ft/sec with maximum relative tip Mach number of 1.37. The compressor had an inlet diameter of 16 inches, a hub-tip diameter ratio of 0.5 and design specific weight flow of 31.1 (lb/sec/(sq ft frontal area). Experimental values of relative total-pressure-loss coefficient were considerably higher than the assumed values. This disparity, hub choking, and application of the simple r… more
Date: August 17, 1956
Creator: Creagh, John W. R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A note on the effect of heat transfer on peak pressure rise associated with separation of turbulent boundary layer on a body of revolution (NACA RM-10) at a Mach number of 1.61

Description: Report presenting an investigation to determine the effect of heat transfer on the peak pressure rise associated with the separation of a turbulent boundary layer on a body of revolution at Mach number 1.61. The results indicated that little or no effect of heat transfer on the shock angles associated with separation on the peak pressure rise required to separate a turbulent boundary layer.
Date: April 1957
Creator: Czarnecki, K. R. & Sinclair, Archibald R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Behavior of Static Pressure Heads at High Speeds

Description: "Memorandum presenting the development of a static pressure head for high speeds. These tests proved the practicability of static pressure heads at speeds up to 400 km/h (248.5 mph). It weighs 6.5 kg or 2.5 times as much as the old head. The position of the pressure head below the airplane was determined by bearing method at different speeds and for different lengths of suspension" (p. 1).
Date: June 1938
Creator: Danielzig, Helmut
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Comparison of experimental with theoretical total-pressure loss in parallel-walled turbojet combustors

Description: "An experimental investigation of combustor total-pressure loss was undertaken to confirm previous theoretical analyses of effects of geometric and flow variables and of heat addition. The results indicate that a reasonable estimate of cold-flow total-pressure-loss coefficient may be obtained from the theoretical analyses. Calculated total-pressure loss due to heat addition agreed with experimental data only when there was no flame ejection from the liner at the upstream air-entry holes" (p. 1). more
Date: January 9, 1957
Creator: Dittrich, Ralph T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Study of the pressure rise across shock waves required to separate laminar and turbulent boundary layers

Description: Results are presented of a dimensional study and an experimental investigation of the pressure rise across a shock wave which causes separation of the boundary layer on a flat plate. The experimental part of the investigation was conducted at a Mach number of 3.03 for a Reynolds number range of 2 x 10 (sup) 6 to 19 x 10 (sup) 6. The available experimental data are compared with the predictions of the present study, and the significance of the results obtained is discussed relative to certain pr… more
Date: September 1952
Creator: Donaldson, Coleman duP. & Lange, Roy H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Study of the Pressure Rise Across Shock Waves Required to Separate Laminar and Turbulent Boundary Layers

Description: Report presenting a study and experimental investigation on the pressure rise across shock waves required to cause separation of the boundary layer on a flat plate. The interaction of shock wave and boundary layer was investigated experimentally when the boundary layer was caused to separate from the surface of a tube. Results regarding testing and correlation with other results are provided.
Date: May 5, 1952
Creator: Donaldson, Coleman duP. & Lange, Roy H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation at a Mach Number of 2.01 of Forebody Strakes for Improving Directional Stability of Supersonic Aircraft

Description: Memorandum presenting an investigation in the 4- by 4-foot supersonic pressure tunnel to determine the effects of forebody strakes on the aerodynamic characteristics in sideslip of a delta-wing airplane model at Mach number of 2.01. The presence of the strakes increased the directional-stability level for both vertical-tail arrangements. Results of pressure tunnels for a forebody show that the presence of the strakes provides a stabilizing influence on the forebody which is consistent with the … more
Date: May 26, 1958
Creator: Driver, Cornelius
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Static longitudinal stability and control characteristics of a model of a 45 degree swept-wing fighter airplane at Mach numbers of 1.41, 1.61, and 2.01

Description: Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel to determine the static longitudinal stability and control characteristics of a model of a 45 degree swept-wing fighter airplane at three Mach numbers. The results indicate that the static margin, which was fairly constant through the lift range, decrease from 32 to 27 percent mean aerodynamic chord with increase in Mach number from 1.41 to 2.01.
Date: July 11, 1956
Creator: Driver, Cornelius & Foster, Gerald V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Nonmetallic diaphragms for instruments

Description: "This report, the second of a series of reports relating to the general subject of instrument diaphragms. The first report of the series was published as Technical Report no. 165, "diaphragms for aeronautic instruments," and comprised an outline of historical developments and theoretical principles. The present report relates entirely to nonmetallic diaphragms, the use of which in certain types of pressure elements has been increasing for some time" (p. 423).
Date: 1925
Creator: Eaton, H. N. & Buckingham, C. T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Estimation of Compressible Boundary-Layer Growth Over Insulated Surfaces With Pressure Gradient

Description: Note presenting the incompressible boundary-layer theory of Truckenbrodt extended using a modified Stewartson-type transformation to include compressible boundary-layer development over insulated surfaces. The method is applicable to two-dimensional and axisymmetric, laminar and turbulent boundary layer, and accounts for the pressure gradient along the wall for both compressible and incompressible flow. Some experimental measurements of the boundary layer on small axisymmetric bodies on the wal… more
Date: June 1957
Creator: Englert, Gerald W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Turbine-rotor-blade designs based on one-dimensional-flow theory 1: performance of single-stage turbine having 40-percent reaction

Description: Report presenting an investigation of a family of turbine-rotor-blade designs based on one-dimensional-flow theory and incorporating systematic changes in design variables. They were designed for 40-percent reaction and a total-to-static pressure ratio of 4.00 based on the assumption of constant static pressure along the radius and one-dimensional-flow theory for the design of the rotor-blade passages.
Date: June 10, 1949
Creator: English, Robert E. & Hauser, Cavour H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Force and pressure characteristics for a series of nose inlets at Mach numbers from 1.59 to 1.99 1: conical spike all-external compression inlet with subsonic cowl lip

Description: Report presenting an experimental investigation to determine the force and pressure characteristics of a typical nose inlet ramjet configuration. It consisted of a conical spike all-external compression inlet attached to an annular subsonic diffuser. Results regarding external-flow characteristics and internal-flow characteristics are provided.
Date: January 19, 1951
Creator: Esenwein, Fred T. & Valerino, Alfred S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Prediction of Downwash and Dynamic Pressure at the Tail From Free-Flight Measurements

Description: "The present measurements form a continuation of earlier flight tests published in a previous report for predicting the downwash at the tail of an airplane. The method makes use of the tail itself as integrating contact surface to the extent that, beginning from the measurement of the self-alignment of the elevator, the mean downwash angle and dynamic pressure at the tail are determined. The instrumental accuracy is considerably improved if the elevator is completely separate from the controls … more
Date: July 1942
Creator: Eujen, E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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