Author: Joseph L. Francis
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 82
Book Description
Hypersonic Flow Over Delta Wings at High Angles of Attack
Author: Joseph L. Francis
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 82
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 82
Book Description
Hypersonic Longitudinal Trim, Stability, and Control Characteristics of a Delta-wing Configuration at High Angles of Attack
Author: William H. Close
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 54
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 54
Book Description
On the Hypersonic Flow Over a Delta Wing with Very Supersonic Leading Edges
Author: Norman D. Malmuth
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 66
Book Description
For the case of very supersonic leading edges, the inviscid hypersonic flow over the windward side of a symmetrical flat-plate delta wing at incidence is analyzed. The limit selected is that the incidence is of higher order than the aspect ratio as the incidence tends to zero at infinite Mach number. In this framework, the flow regions consist of a two-dimensional domain adjacent to the leading edges and a central conefield. The flow quantities in the central region represent small linear, rotational perturbations about the zero sweep flow. A Riemann-Poincare boundary value problem for the pressure perturbation is formulated. An additional condition involving the sidewash at the shock is found to be required to resolve the indeterminacy of the foregoing boundary value problem. Series solutions and numerical results are presented for the shock shape and the pressure. The behavior of the latter quantity is found to be similar to that given by the irrotational linear solution for the supersonic leading edge case. Finally, the relationship between the present application and others involving diffraction problems and corner flows is indicated.
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 66
Book Description
For the case of very supersonic leading edges, the inviscid hypersonic flow over the windward side of a symmetrical flat-plate delta wing at incidence is analyzed. The limit selected is that the incidence is of higher order than the aspect ratio as the incidence tends to zero at infinite Mach number. In this framework, the flow regions consist of a two-dimensional domain adjacent to the leading edges and a central conefield. The flow quantities in the central region represent small linear, rotational perturbations about the zero sweep flow. A Riemann-Poincare boundary value problem for the pressure perturbation is formulated. An additional condition involving the sidewash at the shock is found to be required to resolve the indeterminacy of the foregoing boundary value problem. Series solutions and numerical results are presented for the shock shape and the pressure. The behavior of the latter quantity is found to be similar to that given by the irrotational linear solution for the supersonic leading edge case. Finally, the relationship between the present application and others involving diffraction problems and corner flows is indicated.
An Analysis of the Delta-wing Hypersonic Stability and Control Behavior at Angles of Attack Between 30° and 90°
Author: David E. Fetterman
Publisher:
ISBN:
Category : Delta wing airplanes
Languages : en
Pages : 72
Book Description
Publisher:
ISBN:
Category : Delta wing airplanes
Languages : en
Pages : 72
Book Description
Research on Hypersonic Flow of Blunt Delta Wings. Part I. Theoretical and Experimental Study of a 70-degree Blunt Delta Wing for Low Angles of Attack at Supersonic and Hypersonic Speeds
Author: Bernard Mazelsky
Publisher:
ISBN:
Category :
Languages : en
Pages : 82
Book Description
The object of the present analysis is to investigate the high-speed aerodynamic properties of a blunt delta wing at low angles of attack where the maximum lift to drag ratio occurs. Oguchi's solution of hypersonic flow over a blunt leading edge flat plate at zero incidence is extended to three dimensional delta wings at angle of attack. The shock wave shapes and pressure distributions were obtained by employing the oblique shock relations at the windward sides of the Prandtl-Meyer equations at the leeward side of the wing. The total lift and drag of the wing due to pressure and skin friction were computed by numerical integration using the IBM 7094 computer. The present calculated aerodynamic forces generally agree with the experimental data at the high supersonic Mach numbers (M approx.> or = 4) and lower thickness ratio of the wing which is a 70-degree swept slab sided delta wing with a cylindrical leading edge. (Author).
Publisher:
ISBN:
Category :
Languages : en
Pages : 82
Book Description
The object of the present analysis is to investigate the high-speed aerodynamic properties of a blunt delta wing at low angles of attack where the maximum lift to drag ratio occurs. Oguchi's solution of hypersonic flow over a blunt leading edge flat plate at zero incidence is extended to three dimensional delta wings at angle of attack. The shock wave shapes and pressure distributions were obtained by employing the oblique shock relations at the windward sides of the Prandtl-Meyer equations at the leeward side of the wing. The total lift and drag of the wing due to pressure and skin friction were computed by numerical integration using the IBM 7094 computer. The present calculated aerodynamic forces generally agree with the experimental data at the high supersonic Mach numbers (M approx.> or = 4) and lower thickness ratio of the wing which is a 70-degree swept slab sided delta wing with a cylindrical leading edge. (Author).
The Aerodynamic Characteristics of Several Thick Delta Wings at Mach Numbers to 6 and Angles of Attack 50°
Author: John B. McDevitt
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 114
Book Description
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 114
Book Description
On the Hypersonic Flow Past Blunted, Flat Delta Wings
Author: Arnold Polak
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 48
Book Description
The flow of a perfect gas over the slab portion of a blunted delta wing flying at hypersonic speeds is studied. A set of approximate equations is derived and a solution - for an inviscid flow - is obtained. Using this solution as a representation for the inviscid flow problem, a formulation to the laminar boundary-layer equations is presented; one which is applicable to the flow field's azimuthal planes where the crossflow gradients are not too large. Numerical solutions to these boundary-layer equations have been obtained; however, these are restricted to the azimuthal planes and near to the leading edges. The results indicate the presence of a dividing surface streamline since a numerical solution could not be obtained near the centerplane of the wing, where the crossflow velocity is large. (Author).
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 48
Book Description
The flow of a perfect gas over the slab portion of a blunted delta wing flying at hypersonic speeds is studied. A set of approximate equations is derived and a solution - for an inviscid flow - is obtained. Using this solution as a representation for the inviscid flow problem, a formulation to the laminar boundary-layer equations is presented; one which is applicable to the flow field's azimuthal planes where the crossflow gradients are not too large. Numerical solutions to these boundary-layer equations have been obtained; however, these are restricted to the azimuthal planes and near to the leading edges. The results indicate the presence of a dividing surface streamline since a numerical solution could not be obtained near the centerplane of the wing, where the crossflow velocity is large. (Author).
Hypersonic Aerodynamic Characteristics of Two Delta-wing X-15 Airplane Configurations
Author: Theodore J. Goldberg
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 108
Book Description
Hypersonic aerodynamic characteristics of delta wing x- 15 airplane configurations.
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 108
Book Description
Hypersonic aerodynamic characteristics of delta wing x- 15 airplane configurations.
Hypersonic Flow of Blunt Delta Wings at Low Angles of Attack. I. Shock Wave Shape and Surface Pressure Distribution
Author: Bernard Mazelsky
Publisher:
ISBN:
Category :
Languages : en
Pages : 62
Book Description
This report covers a portion of a research program on the aerodynamic characteristics of a cylindrical-leading-edge 70 degrees swept delta wing at high supersonic and moderate hypersonic Mach numbers, and for small values of angle of attack. Prior to the calculation of the lift and drag characteristics of the wing, a semi-empirical method was developed to predict the shock wave shape surrounding the wing as well as the corresponding pressure distribution on the wing surface. The theoretical shock shape and pressure distribution results are compared with experiments available from the open literature as well as with experimental pressure distributions obtained in the present program on the tip portion of a blunt 70 degrees swept delta wing. Within the range of applicability of the semi-empirical method, the predicted shock wave shapes are in good agreement with experiment. The calculated pressure distributions agree quite well with experiment, provided the angle of attack is below 15 degrees and the Mach number is above M = 3.0.
Publisher:
ISBN:
Category :
Languages : en
Pages : 62
Book Description
This report covers a portion of a research program on the aerodynamic characteristics of a cylindrical-leading-edge 70 degrees swept delta wing at high supersonic and moderate hypersonic Mach numbers, and for small values of angle of attack. Prior to the calculation of the lift and drag characteristics of the wing, a semi-empirical method was developed to predict the shock wave shape surrounding the wing as well as the corresponding pressure distribution on the wing surface. The theoretical shock shape and pressure distribution results are compared with experiments available from the open literature as well as with experimental pressure distributions obtained in the present program on the tip portion of a blunt 70 degrees swept delta wing. Within the range of applicability of the semi-empirical method, the predicted shock wave shapes are in good agreement with experiment. The calculated pressure distributions agree quite well with experiment, provided the angle of attack is below 15 degrees and the Mach number is above M = 3.0.
An Experimental Study of the Pressure and Heat-transfer Distribution on a 70° Sweep Slab Delta Wing in Hypersonic Flow
Author: Mitchel H. Bertram
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 134
Book Description
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 134
Book Description