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Wind-Tunnel Investigation of a Number of Total-Pressure Tubes at High Angles of Attack -- Subsonic, Transonic, and Supersonic Speeds
"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
System:
The UNT Digital Library
Tests of nacelle-propeller combinations in various positions with reference to wings 4: thick wing - various radial-engine cowlings - tandem propellers
This report is the fourth of a series giving the results obtained from wind tunnel tests to determine the interference lift and drag and propulsive efficiency of wing-nacelle-propeller combinations. Previous reports give the results of tests with tractor propellers with various forms of nacelles and engine cowlings. This report gives the results of tests of tandem arrangements of engines and propellers in 11 positions with reference to a thick wing.
Date:
January 17, 1934
Creator:
McHugh, James G.
System:
The UNT Digital Library
Noise From Two-Blade Propellers
"The two-blade propeller, one of the most powerful sources of sound known, has been studied with the view of obtaining fundamental information concerning the noise emission. In order to eliminate engine noise, the propeller was mounted on an electric motor. A microphone was used to pick up the sound whose characteristics were studied electrically. The distribution of noise throughout the frequency range, as well as the spatial distribution about the propeller, was studied. The results are given in the form of polar diagrams. An appendix of common acoustical terms is included" (p. 359).
Date:
January 17, 1935
Creator:
Stowell, E. Z. & Deming, A. F.
System:
The UNT Digital Library
An Aerodynamic Analysis of the Autogiro Rotor With a Comparison Between Calculated and Experimental Results
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 effect upon the net rotor forces, although the flapping motion is influenced appreciably. An approximate evaluation of the effect of parasite drag on the rotor blades established the importance of including this factor in the analysis.
Date:
January 17, 1934
Creator:
Wheatley, John B.
System:
The UNT Digital Library