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  Partner: UNT Libraries Government Documents Department
 Decade: 1940-1949
 Collection: National Advisory Committee for Aeronautics Collection
Aerodynamic Characteristics of Three Deep-Stepped Planing-Tail Flying-Boat Hulls

Aerodynamic Characteristics of Three Deep-Stepped Planing-Tail Flying-Boat Hulls

Date: March 13, 1947
Creator: Riebe, John M.
Description: An investigation was made in the Langley 300 MPH 7- by 10-foot tunnel to determine the aerodynamic characteristics of three deep-stepped planing-tail flying-boat hulls differing only in the amount of step fairing. The hulls were derived by increasing the unfaired step depth of a planing-tail hull of a previous aerodynamic investigation to a depth about 92 percent of the hull beam. Tests were also made on a transverse-stepped hull with an extended afterbody for the purpose of comparison and in order to extend and verify the results of a previous investigation. The investigation indicated that the extended afterbody hull had a minimum drag coefficient about the same as a conventional hull, 0.0066, and an angle-of-attack range for minimum drag coefficient of 0.0057 which was 14 percent less than the transverse stepped hull with extended afterbody; the hulls with step fairing had up to 44 percent less minimum drag coefficient than the transverse-stepped hull, or slightly more drag than a streamlined body having approximately the same length and volume. Longitudinal and lateral instability varied little with step fairing and was about the same as a conventional hull.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of two all-movable wings tested in the presence of a fuselage at a Mach number of 1.9

Aerodynamic characteristics of two all-movable wings tested in the presence of a fuselage at a Mach number of 1.9

Date: October 28, 1948
Creator: Conner, D William
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic characteristics throughout the subsonic speed range of a thin, sharp-edged horizontal tail of aspect ratio 4 equipped with a constant-chord elevator

The aerodynamic characteristics throughout the subsonic speed range of a thin, sharp-edged horizontal tail of aspect ratio 4 equipped with a constant-chord elevator

Date: June 30, 1949
Creator: Bandettini, Angelo
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic data for a wing section of the Republic XF-12 airplane equipped with a double slotted flap

Aerodynamic data for a wing section of the Republic XF-12 airplane equipped with a double slotted flap

Date: January 1, 1946
Creator: Cahill, Jones F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic effects of rockets and fuel tanks mounted under the swept-back wing of an airplane model

The aerodynamic effects of rockets and fuel tanks mounted under the swept-back wing of an airplane model

Date: April 23, 1948
Creator: Boddy, Lee E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic factors affecting the ability of a pilot to return an airplane to level from a banked attitude by use of the rudder alone and without change of heading

Aerodynamic factors affecting the ability of a pilot to return an airplane to level from a banked attitude by use of the rudder alone and without change of heading

Date: October 1, 1941
Creator: Harmon, S M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic Heat-Power Engine Operating on a Closed Cycle

Aerodynamic Heat-Power Engine Operating on a Closed Cycle

Date: November 1, 1942
Creator: Ackeret, J.
Description: Hot-air engines with dynamic compressors and turbines offer new prospects of success through utilization of units of high efficiencies and through the employment of modern materials of great strength at high temperature. Particular consideration is given to an aerodynamic prime mover operating on a closed circuit and heated externally. Increase of the pressure level of the circulating air permits a great increase of limit load of the unit. This also affords a possibility of regulation for which the internal efficiency of the unit changes but slightly. The effect of pressure and temperature losses is investigated. A general discussion is given of the experimental installation operating at the Escher Wyss plant in Zurich for a considerable time at high temperatures.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic heating and the deflection of drops by an obstacle in an air stream in relation to aircraft icing

Aerodynamic heating and the deflection of drops by an obstacle in an air stream in relation to aircraft icing

Date: October 1, 1940
Creator: Kantrowitz, Arthur
Description: Two topics of interest to persons attempting to apply the heat method of preventing ice formation on aircraft are considered. Surfaces moving through air at high speed are shown, both theoretically and experimentally, to be subject to important aerodynamic heating effects that will materially reduce the heat required to prevent ice. Numerical calculations of the path of water drops in an air stream around a circular cylinder are given. From these calculations, information is obtained on the percentage of the swept area cleared of drops.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic measurements made during Navy investigation of human tolerance to wind blasts

Aerodynamic measurements made during Navy investigation of human tolerance to wind blasts

Date: March 11, 1947
Creator: Loving, Donald L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic problems in the design of efficient propellers

Aerodynamic problems in the design of efficient propellers

Date: August 1, 1942
Creator: Feldman, Lewis
Description: None
Contributing Partner: UNT Libraries Government Documents Department