Measurement of static pressure on aircraft

Measurement of static pressure on aircraft

Date: April 1, 1957
Creator: Gracey, William
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The additional-mass effect of plates as determined by experiments

The additional-mass effect of plates as determined by experiments

Date: January 1, 1941
Creator: Gracey, William
Description: 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.
Contributing Partner: UNT Libraries Government Documents Department
Measurement of static pressure on aircraft

Measurement of static pressure on aircraft

Date: January 1, 1958
Creator: Gracey, William
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. Errors due to the position of a static-pressure tube in the flow field of the airplane are given for locations ahead of the fuselage nose, ahead of the wing tip, and ahead of the vertical tail fin. The errors of static-pressure vents on the fuselage of an airplane are also presented. Various methods of calibrating static-pressure installations in flight are briefly discussed.
Contributing Partner: UNT Libraries Government Documents Department
The measurement of pressure altitude on aircraft

The measurement of pressure altitude on aircraft

Date: October 1, 1957
Creator: Gracey, William
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Measured moments of inertia of 32 airplanes

Measured moments of inertia of 32 airplanes

Date: October 1, 1940
Creator: Gracey, William
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, as low-wing monoplanes, parasol and high-wing monoplanes, and biplanes. The data are shown to provide a convenient means of rapidly estimating the moments of inertia of other airplanes. A three view drawing of each of the 32 airplanes is included.
Contributing Partner: UNT Libraries Government Documents Department
The experimental determination of the moments of inertia of airplanes by a simplified compound-pendulum method

The experimental determination of the moments of inertia of airplanes by a simplified compound-pendulum method

Date: June 1, 1948
Creator: Gracey, William
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. (author).
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation of a number of total-pressure tubes at high angles of attack -- subsonic, transonic, and supersonic speeds

Wind-tunnel investigation of a number of total-pressure tubes at high angles of attack -- subsonic, transonic, and supersonic speeds

Date: January 1, 1957
Creator: Gracey, William
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.
Contributing Partner: UNT Libraries Government Documents Department
Summary of methods of measuring angle of attack on aircraft

Summary of methods of measuring angle of attack on aircraft

Date: August 1, 1958
Creator: Gracey, William
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Measurement of static pressure on aircraft

Measurement of static pressure on aircraft

Date: November 1, 1957
Creator: Gracey, William
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation of a number of total-pressure tubes at high angles of attack subsonic, transonic, and supersonic speeds

Wind-tunnel investigation of a number of total-pressure tubes at high angles of attack subsonic, transonic, and supersonic speeds

Date: May 1, 1956
Creator: Gracey, William
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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