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.
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.
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).
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
Pressure Distributions on Blunt-delta Wings at Angles of Attack Up to 90 Degrees and Mach Number of 6.85
Author: Peter T. Bernot
Publisher:
ISBN:
Category : Mach number
Languages : en
Pages : 48
Book Description
Publisher:
ISBN:
Category : Mach number
Languages : en
Pages : 48
Book Description
Pressure Distributions on Blunt Delta Wings at a Mach Number of 2.91 and Angles of Attack Up to 90 Deg
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 120
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 120
Book Description
A Study of the Blunt Slab Delta Wing at Hypersonic Speeds and Angles of Attack
Author: Gerald L. Burke
Publisher:
ISBN:
Category :
Languages : en
Pages : 74
Book Description
This report presents information obtained during an extensive AFFDL study of the flow field about blunt, slab delta wings. Data taken during the study include surface heat transfer and pressure, pitot surveys, oil flows, schlierens, shadowgraphs, and vapor screens. The main lesson of the study is the three-dimensionality of the flow field in addition to the documented effects of inflow and outflow. The most unexpected phenomenon was the appearance of a hot streak on the lower surface off the center line. It is proposed that this region of higher heating is due to a slip line originating at the point of inflection in the shock wave between the bow shock and the leading edge shock. This proposition is supported by pitot pressure surveys and surface pressure distributions. Other qualitative features of the flow field which are presented include the movement of the leading edge stagnation line onto the lower surface. The relative entropy levels of the flow field and the use of vapor screens in hypersonic tunnels are discussed. (Author).
Publisher:
ISBN:
Category :
Languages : en
Pages : 74
Book Description
This report presents information obtained during an extensive AFFDL study of the flow field about blunt, slab delta wings. Data taken during the study include surface heat transfer and pressure, pitot surveys, oil flows, schlierens, shadowgraphs, and vapor screens. The main lesson of the study is the three-dimensionality of the flow field in addition to the documented effects of inflow and outflow. The most unexpected phenomenon was the appearance of a hot streak on the lower surface off the center line. It is proposed that this region of higher heating is due to a slip line originating at the point of inflection in the shock wave between the bow shock and the leading edge shock. This proposition is supported by pitot pressure surveys and surface pressure distributions. Other qualitative features of the flow field which are presented include the movement of the leading edge stagnation line onto the lower surface. The relative entropy levels of the flow field and the use of vapor screens in hypersonic tunnels are discussed. (Author).
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 : Aerodynamics, Hypersonic
Languages : en
Pages : 136
Book Description
Results are presented for a study of the pressure and heat-transfer distributions and force characteristics of slab delta wings of 70° sweep at Mach numbers of 6.8 and 9.6 in air and 18 in helium. The wings had cylindrical leading edges and were tested with two different noses. One was sharp in plan view and the other was a tangent sphere with the same diameter as the cylindrical leading edge. Simple approaches to predicting the heat transfer are shown to be successful if the flow pattern peculiar to the angle-of-attack range under consideration is taken into account.
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 136
Book Description
Results are presented for a study of the pressure and heat-transfer distributions and force characteristics of slab delta wings of 70° sweep at Mach numbers of 6.8 and 9.6 in air and 18 in helium. The wings had cylindrical leading edges and were tested with two different noses. One was sharp in plan view and the other was a tangent sphere with the same diameter as the cylindrical leading edge. Simple approaches to predicting the heat transfer are shown to be successful if the flow pattern peculiar to the angle-of-attack range under consideration is taken into account.
Flow Fields, Pressure Distributions, and Heat Transfer for Delta Wings at Hypersonic Speeds
Author: Mitchel H. Bertram
Publisher:
ISBN:
Category :
Languages : en
Pages : 36
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 36
Book Description
Scientific and Technical Aerospace Reports
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 978
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 978
Book Description
Local Pressure Distribution on a Blunt Delta Wing for Angles of Attack Up to 35 Degrees at Mach Numbers of 3.4 and 4.7
Author: Marvin Kussoy
Publisher:
ISBN:
Category : Mach number
Languages : en
Pages : 32
Book Description
Publisher:
ISBN:
Category : Mach number
Languages : en
Pages : 32
Book Description