UNT Libraries Government Documents Department - 1,438 Matching Results

Search Results

prev Results: 1431 - 1438
open access

Theoretical Investigation of Drag Reduction in Maintaining the Laminar Boundary Layer by Suction

Description: "Maintenance of a laminar boundary layer by suction was suggested recently to decrease the friction drag of an immersed body, in particular an airfoil section. The present treatise makes a theoretical contribution to this question in which, for several cases of suction and blowing, the stability of the laminar velocity profile is investigated. Estimates of the minimum suction quantities for maintaining the laminar boundary layer and estimates of drag reduction are thereby obtained" (p. 1).
Date: June 1947
Creator: Ulrich, A.
Item Type: Refine your search to only Report
open access

NACA Conference on Aerodynamics of High Speed Aircraft

Description: "This document contains reproductions of technical papers presented by staff members of the NACA Laboratories at the NACA Conference on Aerodynamics of High-Speed Aircraft held at the Langley Aeronautical Laboratory November 1, 2, and 3, 1955. The primary purpose of the conference was to convey to contractors of the military services and others concerned with the design of aircraft the results of recent research and to provide those attending with an opportunity to discuss these results. The pa… more
Date: 1955-11-01/1955-11-03
Item Type: Refine your search to only Report
open access

On the Design of Airfoils in Which the Transition of the Boundary Layer Is Delayed

Description: Memorandum examining the phenomenon of airfoil drag, which is related almost exclusively to skin friction at high speed flight conditions. The primary way to reduce drag is to delay the transition from laminar to turbulent flow in the boundary layer along the surface. A particular airflow design that may delay transition and therefore have fewer problems related to drag are provided.
Date: October 1952
Creator: Tani, Itiro
Item Type: Refine your search to only Report
open access

Investigation of an Afterburning Ramjet Using Gaseous Hydrogen as Fuel at Mach Number of 3.0

Description: Memorandum presenting an investigation conducted in the supersonic wind tunnel on a 16-inch ramjet that was equipped with an afterburner and used gaseous hydrogen for both the primary and afterburner fuels. The primary nozzle had a contraction ratio of 0.6 while the exit nozzle had a contraction ratio of 0.9. Data were obtained at a free-stream Mach number of 3.0 and zero angle of attack.
Date: June 17, 1957
Creator: Wasserbauer, Joseph F.
Item Type: Refine your search to only Report
Back to Top of Screen