Experimental Investigation Base Pressure on Blunt-trailing-edge Wings at Supersonic Velocities
Title | Experimental Investigation Base Pressure on Blunt-trailing-edge Wings at Supersonic Velocities PDF eBook |
Author | Dean R. Chapman |
Publisher | |
Pages | 852 |
Release | 1952 |
Genre | Aerodynamics, Supersonic |
ISBN |
The pressres acting on the base of blunt-trailing-edge airfoils have been measured at Mach numbers of 1.25, 1.5, 2.0, and 3.1 and at Reynolds numbers from 0.2 to 3.8 million. Data are presented for 29 profiles both with laminar and with turbulent boundary layers approaching the trailing edges of the wings. The base pressure is found to be a function primarily of Mach number and the ratio of the boundary layer thickeness at the trailing edge to the trailing-edge thickness.
Experimental Investigation of Base Pressure on Blunt-trailing-edge Wings at Supersonic Velocities
Title | Experimental Investigation of Base Pressure on Blunt-trailing-edge Wings at Supersonic Velocities PDF eBook |
Author | Dean R. Chapman |
Publisher | |
Pages | 62 |
Release | 1952 |
Genre | Aerodynamics, Supersonic |
ISBN |
The pressres acting on the base of blunt-trailing-edge airfoils have been measured at Mach numbers of 1.25, 1.5, 2.0, and 3.1 and at Reynolds numbers from 0.2 to 3.8 million. Data are presented for 29 profiles both with laminar and with turbulent boundary layers approaching the trailing edges of the wings. The base pressure is found to be a function primarily of Mach number and the ratio of the boundary layer thickeness at the trailing edge to the trailing-edge thickness.
Technical Note - National Advisory Committee for Aeronautics
Title | Technical Note - National Advisory Committee for Aeronautics PDF eBook |
Author | United States. National Advisory Committee for Aeronautics |
Publisher | |
Pages | 1026 |
Release | 1956 |
Genre | Aeronautics |
ISBN |
NASA Technical Note
Title | NASA Technical Note PDF eBook |
Author | |
Publisher | |
Pages | 686 |
Release | 1973 |
Genre | |
ISBN |
Reduction of Profile Drag at Supersonic Velocities by the Use of Airfoil Sections Having a Blunt Trailing Edge
Title | Reduction of Profile Drag at Supersonic Velocities by the Use of Airfoil Sections Having a Blunt Trailing Edge PDF eBook |
Author | Dean R. Chapman |
Publisher | |
Pages | 31 |
Release | 1949 |
Genre | Aerofoils |
ISBN |
A preliminary theoretical and experimental investigation has been made of the supersonic aerodynamic characteristics of blunt-trailing-edge airfoils with finite trailing-edge airfoils. Calculations of the drag of a family of airfoils with finite trailing-edge thickness are presented for various values of the base pressure. Theoretical expressions for the lift, pitching moment, and maximum lift-drag ratio are developed using the Buseman second-order theory for two-dimensional supersonic flow. In order to compare the theoretical estimates with experimental data, measurements were taken on the lift and drag on wings of various airfoil sections at Mach numbers of 1.5 and 2.0 and at Reynolds numbers varying from 0.2 to 1.2 million. Rectangular plan forms with an aspect ratio of 4 and a thickness ratio of either 10 or 9.1 percent were used throughout the experiments.
Report
Title | Report PDF eBook |
Author | |
Publisher | |
Pages | 1180 |
Release | 1957 |
Genre | Aeronautics |
ISBN |
Report - National Advisory Committee for Aeronautics
Title | Report - National Advisory Committee for Aeronautics PDF eBook |
Author | United States. National Advisory Committee for Aeronautics |
Publisher | |
Pages | 1208 |
Release | 1952 |
Genre | Aeronautics |
ISBN |