Author: George H. Holdaway
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 62
Book Description
Investigation at Mach Numbers of 0.20 to 3.50 of a Blended Diamond Wing and Body Combination of Sonic Design But with Low Wave-drag Increase with Increasing Mach Number
Author: George H. Holdaway
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 58
Book Description
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 58
Book Description
Investigation at Mach Numbers of 0.20 to 3.50 of Blended Wing-body Combinations of Sonic Design with Diamond, Delta and Arrow Plan Forms
Author: George H. Holdaway
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 82
Book Description
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 82
Book Description
Investigation at Mach Numbers of 0.20 to 3.50 of Blended Wing-body Combinations of Sonic Design with Diamond, Delta, and Arrow Plan Forms [with List of References]
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 77
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 77
Book Description
Investigation at Mach Numbers of 0.60 to 3.50 of Blended Wing-body Combinations with Cambered and Twisted Wings with Diamond, Delta and Arrow Plan Forms [with List of References]
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 76
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 76
Book Description
The Flow Past a Straight- and a Swept-wing-body Combination and Their Equivalent Bodies of Revolution at Mach Numbers Near 1.0
Author: W. F. Lindsey
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 24
Book Description
Abstract: The complete flow fields past a straight and a swept wing-body combination and their equivalent bodies of revolution at Mach numbers around 1.0 have been observed by means of motion-picture schlieren photography. The results of these observations indicate that the shock growth and positions on the wing-body combinations are closely reproduced in the flow past their respective equivalent bodies.
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 24
Book Description
Abstract: The complete flow fields past a straight and a swept wing-body combination and their equivalent bodies of revolution at Mach numbers around 1.0 have been observed by means of motion-picture schlieren photography. The results of these observations indicate that the shock growth and positions on the wing-body combinations are closely reproduced in the flow past their respective equivalent bodies.
Free-flight Measurements of the Zero-lift Drag of Several Wings at Mach Numbers from 1.4 to 3.8
Author: H. Herbert Jackson
Publisher:
ISBN:
Category : Mach number
Languages : en
Pages : 32
Book Description
Publisher:
ISBN:
Category : Mach number
Languages : en
Pages : 32
Book Description
Investigation at Mach Numbers of 0.60 to 3.50 of Blended Wing-body Combinations with Cambered and Twisted Wings with Diamond, Delta and Arrow Plan Forms
Author: George H. Holdaway
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 80
Book Description
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 80
Book Description
A Supersonic Area Rule and an Application to the Design of a Wing-body Combination with High Lift-drag Ratios
Author: Richard T. Whitcomb
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 20
Book Description
Summary: As an extension of the transonic area rule, a concept for interrelating the wave drags of wing-body combinations at moderate supersonic speeds with axial developments of cross-sectional area has been derived. The wave drag of a combination at a given supersonic speed is related to a number of developments of cross-sectional areas as intersected by Mach planes. On the basis of this concept and other design procedures, a structurally feasible, swept-wing--indented-body combination has been designed to have relatively high maximum lift-drag ratios over a range of transonic and moderate supersonic Mach numbers. The wing of the combination has been designed to have reduced drag associated with lift and, when used with an indented body, to have low zero-lift wave drag. Experimental results have been obtained for this configuration at Mach numbers from 0.80 to 2.01. Maximum lift-drag ratios of approximately 14 and 9 were measured at Mach numbers of 1.15 and 1.41, respectively.
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 20
Book Description
Summary: As an extension of the transonic area rule, a concept for interrelating the wave drags of wing-body combinations at moderate supersonic speeds with axial developments of cross-sectional area has been derived. The wave drag of a combination at a given supersonic speed is related to a number of developments of cross-sectional areas as intersected by Mach planes. On the basis of this concept and other design procedures, a structurally feasible, swept-wing--indented-body combination has been designed to have relatively high maximum lift-drag ratios over a range of transonic and moderate supersonic Mach numbers. The wing of the combination has been designed to have reduced drag associated with lift and, when used with an indented body, to have low zero-lift wave drag. Experimental results have been obtained for this configuration at Mach numbers from 0.80 to 2.01. Maximum lift-drag ratios of approximately 14 and 9 were measured at Mach numbers of 1.15 and 1.41, respectively.
An Investigation at Mach Numbers from 0.20 to 4.63 of the Aerodynamic Performance, Static Stability, and Trimming Characteristics of a Canard Configuration Designed for Efficient Supersonic Cruise Flight
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 88
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 88
Book Description
Investigation of the Drag of Blunt-nosed Bodies of Revolution in Free Flight at Mach Numbers from 0.6 to 2.3
Author: Harvey A. Wallskog
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 32
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 32
Book Description