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The additional-mass effect of plates as determined by experiments

Description: From Introduction: "The apparent increase in the inertia properties of a body moving in a fluid medium has been called the additional-mass effect. This report presents a resume of test procedures and results of experimental determinations of the additional-mass effect of flat plates. In addition to data obtained from various foreign sources and from a NACA investigation in 1933, the results of tests recently conducted by the National Advisory Committee for Aeronautics are included."
Date: 1941
Creator: Gracey, William
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Experimental Determination of the Moments of Inertia of Airplanes by a Simplified Compound-Pendulum Method

Description: "A simplified compound-pendulum method for the experimental determination of the moments of inertia of airplanes about the x and y axes is described. The method is developed as a modification of the standard pendulum method reported previously in NACA report, NACA-467. A brief review of the older method is included to form a basis for discussion of the simplified method" (p. 1).
Date: June 1948
Creator: Gracey, William
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Measured Moments of Inertia of 32 Airplanes

Description: "A compilation of the experimentally determined moments of inertia of 32 airplanes is presented. The measurements were obtained at the laboratories of the NACA by means of a pendulum method. The airplanes tested are representative of several types of aircraft of gross weight less than 10,000 pounds. The results are presented in coefficient as well as in dimensional form. An elementary analysis of the data disclosed the possibility of grouping the results according to wing type of the airplane, … more
Date: October 1940
Creator: Gracey, William
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Measurement of Pressure Altitude on Aircraft

Description: Note presenting a determination of the accuracy with which pressure altitude can be measured by calculation of the errors in the measuring system, errors arising from operation of the system, and variations in atmospheric pressure. Some possibilities for reducing errors in the categories of altimeter-scale error, static-pressure error, atmospheric-reference error, flight technical error, friction error, and service error are provided.
Date: October 1957
Creator: Gracey, William
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Measurement of Static Pressure on Aircraft

Description: Note presenting existing data on the errors involved in the measurement of static pressure by means of static-pressure tubes and fuselage vents. The errors associated with the various design features of static-pressure tubes are discussed for the condition of zero angle of attack and for the case where the tube is inclined to the flow.
Date: November 1957
Creator: Gracey, William
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Measurement of Static Pressure on Aircraft

Description: "Existing data on the errors involved in the measurement of static pressure by means of static-pressure tubes and fuselage vents are presented. The errors associated with the various design features of static-pressure tubes are discussed for the condition of zero angle of attack and for the case where the tube is inclined to flow. Errors which result from variations in the configuration of static-pressure vents are also presented" (p. 645).
Date: December 17, 1956
Creator: Gracey, William
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Measurement of Static Pressure on Aircraft

Description: "Existing data on the errors involved in the measurement of static pressure by means of static-pressure tubes and fuselage vents are presented. The errors associated with the various design features of static-pressure tubes are discussed for the condition of zero angle of attack and for the case where the tube is included to the flow. Errors due to variations in the configuration of static-pressure vents are also presented" (p. 1).
Date: April 1, 1957
Creator: Gracey, William
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Summary of Methods of Measuring Angle of Attack on Aircraft

Description: Note presenting wind-tunnel calibrations of three types of angle-of-attack sensing devices - the pivoted vane, the differential pressure tube, and the null-seeking pressure tube. Flight data on the position errors for three sensor locations - ahead of the fuselage nose, ahead of the wing tip, and on the forebody of the fuselage - are also presented. Various methods for calibrating angle-of-attack installations in flight are briefly described.
Date: August 1958
Creator: Gracey, William
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of a Number of Total-Pressure Tubes at High Angles of Attack: Subsonic, Transonic, and Supersonic Speeds

Description: Note presenting the effect of inclination of the airstream on the measured pressures of 54 total-pressure tubes for angles of attack up to 60 degrees and over a Mach number range from 0.26 to 1.62. The investigation was conducted in five wind tunnels. Results regarding effect of impact-opening size, effect of varying the shape of the internal chamber, effect of external shape, effect of slant profile, effect of venting of shielded tubes, effect of varying the probe position and the throat diame… more
Date: May 1956
Creator: Gracey, William
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of a Number of Total-Pressure Tubes at High Angles of Attack -- Subsonic, Transonic, and Supersonic Speeds

Description: "The effect of inclination of the airstream on the measured pressures of 54 total-pressure tubes has been determined for angles of attack up to 60 degrees and over a Mach number range from 0.26 to 1.62. The investigation was conducted in five wind tunnels at the Langley Aeronautical Laboratory" (p. 495).
Date: January 17, 1956
Creator: Gracey, William
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Investigation at Large Angles of Attack of the Static-Pressure Errors of a Service Pitot-Static Tube Having a Modified Orifice Configuration

Description: Note presenting the effect of inclination of the airstream on the static pressure measured by two essentially similar service pitot-static tubes and by one of those tubes with three modified orifice arrangements as determined in flight. Results regarding initial calibrations at Mach numbers from 0.20 to 0.24 and the final orifice configuration are provided.
Date: February 1954
Creator: Gracey, William & Scheithauer, Elwood F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of a Number of Total Pressure Tubes at High Angles of Attack: Subsonic speeds

Description: Report presenting a wind-tunnel investigation to determine the effect of inclination of the air stream on the measured pressures of 20 total-pressure tubes through a range of angles of attack and Mach numbers. Generally, the range of angle of attack over which the tubes remained insensitive to inclination was appreciably greater at supersonic speeds than at subsonic speeds.
Date: January 1951
Creator: Gracey, William; Coletti, Donald E. & Russell, Walter R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-tunnel investigation of a number of total-pressure tubes at high angles of attack: Subsonic speeds

Description: Report presenting an investigation of the possibility of designing a fixed total-pressure tube which will remain insensitive to inclination of the air stream over a wide range of angle of attack through subsonic and supersonic speed ranges.
Date: April 1951
Creator: Gracey, William; Letko, William & Russell, Walter R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of a Shielded Total-Pressure Tube at Transonic Speeds

Description: Report presenting testing of a shielded total-pressure tube with a curved venturi entry in order to obtain the variation of total-pressure error with angle of attack from a range of 0 to 60 degrees and for a range of Mach numbers. The critical angle was found to vary from about 57 degrees at Mach number 0.90 to 56 degrees at Mach number 1.10.
Date: January 22, 1952
Creator: Gracey, William; Pearson, Albin O. & Russell, Walter R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-tunnel investigation of six shielded total-pressure tubes at high angles of attack: Subsonic speeds

Description: Report presenting a study of the effect of inclination of the air stream on the measured pressures of six shielded total-pressure tubes for a range of angles of attack. The tests were conducted over a range of Mach numbers. Results indicated that the shape of the venturi entry has a pronounced effect on the range of angles of attack over which the tubes remain insensitive to inclination of the air stream.
Date: November 1951
Creator: Russell, Walter R.; Gracey, William; Letko, William & Fournier, Paul G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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