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 Decade: 1940-1949
 Year: 1947
 Collection: National Advisory Committee for Aeronautics Collection
Some Recent Contributions to the Study of Transition and Turbulent Boundary Layers

Some Recent Contributions to the Study of Transition and Turbulent Boundary Layers

Date: April 1947
Creator: Dryden, Hugh L.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Considerations of the Total Drag of Supersonic Airfoil Sections

Considerations of the Total Drag of Supersonic Airfoil Sections

Date: July 1947
Creator: Ivey, H. Reese & Klunker, E. Bernard
Description: The results of calculations of the viscous and pressure drags of some two-dimensional supersonic airfoils at zero lift are presented. The results indicate that inclusion of viscous drag alters many previous results regarding the desirability of certain airfoil shapes for securing low drags at supersonic speeds. At certain Reynolds and Mach numbers, for instance, a circular-arc airfoil may theoretically have less drag than the previously advocated symmetrical wedge-shape profile; although under different conditions, the circular-arc airfoil may have a higher drag.
Contributing Partner: UNT Libraries Government Documents Department
The stability of the laminar boundary layer in a compressible fluid

The stability of the laminar boundary layer in a compressible fluid

Date: January 1, 1947
Creator: Lees, Lester
Description: Report is a continuation of a theoretical investigation of the stability of the laminar boundary layer in a compressible fluid. An approximate estimate for the minimum critical Reynolds number, or stability limit, is obtained in terms of the distribution of the kinematic viscosity and the product of the mean density and mean vorticity across the boundary layer. The extension of the results of the stability analysis to laminar boundary-layer gas flows with a pressure gradient in the direction of the free stream is discussed. (author).
Contributing Partner: UNT Libraries Government Documents Department
A Ram-Jet Engine for Fighters

A Ram-Jet Engine for Fighters

Date: October 1, 1947
Creator: Sanger, E & Bredt, I
Description: Simple and accurate calculations are made of the flow process in a continuous compressorless Lorin jet-propulsion unit. Experimental confirmation is given from towing tests on an airplane at flying speeds up to 200 miles per second. An analysis is made of the performance of a fighter-type airplane designed for utilization of this propulsion system.
Contributing Partner: UNT Libraries Government Documents Department
Force and pressure-distribution measurements on a rectangular wing with a slotted droop nose and with either plain and split flaps in combination or a slotted flap.

Force and pressure-distribution measurements on a rectangular wing with a slotted droop nose and with either plain and split flaps in combination or a slotted flap.

Date: March 1, 1947
Creator: Lemme, H G
Description: Force measurements and pressure distribution measurements on the midsection were made on a rectangular wing with slotted droop nose and end plates, on which could be placed a choice of either a plain flap-split flap combination or a slotted flap. (author).
Contributing Partner: UNT Libraries Government Documents Department
Effects of a Fuselage on the Aerodynamic Characteristics of a 42 Degree Sweptback Wing at Reynolds Numbers to 8,000,000

Effects of a Fuselage on the Aerodynamic Characteristics of a 42 Degree Sweptback Wing at Reynolds Numbers to 8,000,000

Date: June 10, 1947
Creator: Salmi, Reino J.; Conner, D. William & Graham, Robert R.
Description: Wind-tunnel investigations were made in pitch and yaw with and without split flaps. Presence of the fuselage had negligible effect on values of maximum lift coefficient and slope of lift curve, but caused a destabilizing shift in the rate of change of pitching moment with lift. Effects of fuselage position on drag characteristics were small for wings without flaps, but were appreciable when split flaps were on.
Contributing Partner: UNT Libraries Government Documents Department
Investigation of pressure losses in several turbosupercharger nozzle hoses

Investigation of pressure losses in several turbosupercharger nozzle hoses

Date: February 11, 1947
Creator: Lord, Albert M & Donnola, Joseph
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Investigation of shock diffusers at Mach number 1.85 I :  projecting single-shock cones

Investigation of shock diffusers at Mach number 1.85 I : projecting single-shock cones

Date: June 17, 1947
Creator: Moeckel, W E; Connors, J F & Schroeder, A H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An investigation at low speed of a large-scale triangular wing of aspect ratio two I : characteristics of a wing having a double-wedge airfoil section with maximum thickness at 20-percent chord

An investigation at low speed of a large-scale triangular wing of aspect ratio two I : characteristics of a wing having a double-wedge airfoil section with maximum thickness at 20-percent chord

Date: November 13, 1947
Creator: Anderson, Adrien, E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Investigation of the dynamic response of airplane wings to gusts

Investigation of the dynamic response of airplane wings to gusts

Date: June 1, 1947
Creator: Pierce, Harold B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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