Tests of Several Model Nacelle-Propeller Arrangements in Front of a Wing

Tests of Several Model Nacelle-Propeller Arrangements in Front of a Wing

Date: September 1, 1939
Creator: Mchugh, James G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tests of Several Model Nacelle-Propeller Arrangements in Front of a Wing

Tests of Several Model Nacelle-Propeller Arrangements in Front of a Wing

Date: September 1, 1939
Creator: McHugh, James G.
Description: An investigation was conducted in the N.A.C.A. 20-foot wind tunnel to determine the drag, the propulsive and net efficiencies, and the cooling characteristics of severa1 scale-model arrangements of air-cooled radial-engine nacelles and present-day propellers in front of an 18- percent-thick, 5- by 15-foot airfoil. This report deals with an investigation of wing-nacelle arrangements simulating the geometric proportions of airplanes in the 40,000- to 70,000- pound weight classification and having the nacelles located in the vicinity of the optimum location determined from the earlier tests.
Contributing Partner: UNT Libraries Government Documents Department
Comparison of Three Exit-Area Control Devices on an N.A.C.A. Cowling, Special Report

Comparison of Three Exit-Area Control Devices on an N.A.C.A. Cowling, Special Report

Date: May 1, 1940
Creator: McHugh, James G.
Description: Adjustable cowling flaps, an adjustable-length cowling skirt, and a bottom opening with adjustable flap were tested as means of controlling the rate of cooling-air flow through an air-cooled radial-engine cowling. The devices were tested in the NACA 20-foot tunnel on a model wing-nacelle-propeller combination, through an airspeed range of 20 to 80 miles per hour, and with the propeller blade angle set 23 degrees at 0.75 of the tip radius. The resistance of the engine to air flow through the cowling was simulated by a perforated plate. The results indicated that the adjustable cowling flap and the bottom opening with adjustable flap were about equally effective on the basis of pressure drop obtainable and that both were more effective means of increasing the pressure drop through the cowling than the adjustable-length skirt. At conditions of equal cooling-air flow, the net efficiency obtained with the adjustable cowling flaps and the adjustable-length cowling skirt was about 1% greater than the net efficiency obtained with the bottom opening with adjustable flap.
Contributing Partner: UNT Libraries Government Documents Department
Pressure-distribution measurements at large angles of pitch on fins of different span-chord ratio on a 1/40-scale model of the U. S. Airship "Akron."

Pressure-distribution measurements at large angles of pitch on fins of different span-chord ratio on a 1/40-scale model of the U. S. Airship "Akron."

Date: January 1, 1937
Creator: Mchugh, James G
Description: Report presents the results of pressure-distribution measurements on a 1/40-scale model of the U. S. Airship "Akron" conducted in the NACA 20-foot wind tunnel. The measurements were made on the starboard fin of each of four sets of horizontal tail surfaces, all of approximately the same area but differing in span-chord ratio, for five angles of pitch varying from 11.6 degrees to 34 degrees, for four elevator angles, and at air speeds ranging from 56 to 77 miles per hour. Pressures were also measured at 13 stations along the rear half of the port side of the hull at one elevator setting for the same five angles of pitch and at an air speed of approximately 91 miles per hour. The normal force on the fin and the moment of forces about the fin root were determined. The results indicate that, ignoring the effect on drag, it would be advantageous from structural considerations to use a fin of lower span-chord ratio than that used on the "Akron.".
Contributing Partner: UNT Libraries Government Documents Department
Tests of nacelle-propeller combinations in various positions with reference to wings IV : thick wing - various radial-engine cowlings - tandem propellers

Tests of nacelle-propeller combinations in various positions with reference to wings IV : thick wing - various radial-engine cowlings - tandem propellers

Date: January 1, 1935
Creator: Mchugh, James G
Description: 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.
Contributing Partner: UNT Libraries Government Documents Department
The Characteristics of Two Model Six-Blade Counterrotating Pusher Propellers of Conventional and Improved Aerodynamic Design

The Characteristics of Two Model Six-Blade Counterrotating Pusher Propellers of Conventional and Improved Aerodynamic Design

Date: April 1, 1942
Creator: Pepper, Edward & McHugh, James G.
Description: Two airfoil plans were used for propeller blades. One is modified Clark Y section designed for structural reliability and the second an NACA 16 airfoil section designed to produce minimum aerodynamic losses. At low air speeds, the propeller designed for aerodynamic effects showed a gain of from 1.5 to 4.0 percent in propulsive efficiency over the conventional type depending on the pitch. Because of the numerous variables involved, the effect of each one on the aerodynamic characteristics of the propellers could not be isolated.
Contributing Partner: UNT Libraries Government Documents Department
A summary and analysis of the low-speed longitudinal characteristics of swept wings at high Reynolds number

A summary and analysis of the low-speed longitudinal characteristics of swept wings at high Reynolds number

Date: January 1, 1957
Creator: Furlong, G Chester
Description: An analysis of the longitudinal characteristics of swept wings which is based on available large-scale low-speed data and supplemented with low-scale data when feasible is presented. The emphasis has been placed on the differentiation of the characteristics by a differentiation between the basic flow phenomenon involved. Insofar as possible all large-scale data available as of August 15, 1951 have been summarized in tabular form for ready reference.
Contributing Partner: UNT Libraries Government Documents Department
The effect of nacelle-propeller diameter ratio on body interference and on propeller and cooling characteristics

The effect of nacelle-propeller diameter ratio on body interference and on propeller and cooling characteristics

Date: January 1, 1939
Creator: Mchugh, James G
Description: Report presents the results of an investigation conducted in the NACA 20-foot tunnel to determine the slipstream drag, the body interference, and the cooling characteristics of nacelle-propeller diameter. Four combinations of geometrically similar propellers and nacelles, mounted on standard wing supports, were tested with values of the ratio of nacelle diameter to propeller diameter of 0.25, 0.33, and 0.44.
Contributing Partner: UNT Libraries Government Documents Department
A summary and analysis of the low-speed longitudinal characteristics of swept wings at high Reynolds number

A summary and analysis of the low-speed longitudinal characteristics of swept wings at high Reynolds number

Date: August 14, 1952
Creator: Furlong, G Chester
Description: None
Contributing Partner: UNT Libraries Government Documents Department