Author: Eugene E. LundquistPublisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 210
Book Description
Critical Compressive Stress for Flat Rectangular Plates Supported Along All Edges and Elastically Restrained Against Rotation Among the Unloaded Edges
Author: Eugene E. LundquistPublisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 210
Book Description
Report
Author: United States. National Advisory Committee for AeronauticsPublisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 24
Book Description
Report - National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for AeronauticsPublisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 444
Book Description
Annual Report of the National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for AeronauticsPublisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 664
Book Description
On Possible Similarity Solutions for Three-dimensional Incompressible Laminar Boundary Layers
Author: Arthur G. HansenPublisher:
ISBN:
Category : Air flow
Languages : en
Pages : 716
Book Description
Solutions of mainstream flow patterns for all possible incompressible laminar-boundary-layer flows having classical similarity with respect to rectangular coordinate systems are derived. These solutions, which apply to a wide range of flows, are summarized in table form.
Technical Note - National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for AeronauticsPublisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 836
Book Description
Index of NACA Technical Publications
Author: United States. National Advisory Committee for AeronauticsPublisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 616
Book Description
A Selected Listing of NASA Scientific and Technical Reports for ...
Author: Influence of Airfoil Trailing-edge Angle and Trailing-edge Thickness Variation on the Effectiveness of a Plain Flap at High Subsonic Mach Numbers
Author: Albert D. HemenoverPublisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 756
Book Description
The effects of variation of trailing-edge angle and trailing-edge thickness on the lift characteristics of a 10-percent-chord thick symmetrical NACA airfoil section with a 25-percent-chord plain flap are appraised from wind-tunnel tests at Mach numbers from 0.3 to 0.9 and Reynolds numbers varying correspondingly from 1 to 2 million. The airfoil trailing-edge angle was varied from approximately 18 to 6 degrees, and the trailing-edge thickness from zero to the thickness at the flap hinge line.
Laminar Boundary Layer on a Circular Cone in Supersonic Flow at a Small Angle of Attack
Author: Franklin K. MoorePublisher:
ISBN:
Category : Angle of attack (Aerodynamics)
Languages : en
Pages : 712
Book Description
The laminar boundary layer on a circular cone at angle of attack to a supersonic stream is discussed. A perturbation analysis was made to show the influence of a small angle of attack on such boundary layer quantities as skin friction, boundary-layer thickness, viscous lift, drag, and pitching moment.