Aerodynamic Characteristics Over a Mach Number Range of 1.40 to 2.78 of a Rocket-propelled Airplane Configuration Having a Low 52.2© Delta Wing and an Unswept Horizontal Tail PDF Download
Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download Aerodynamic Characteristics Over a Mach Number Range of 1.40 to 2.78 of a Rocket-propelled Airplane Configuration Having a Low 52.2© Delta Wing and an Unswept Horizontal Tail PDF full book. Access full book title Aerodynamic Characteristics Over a Mach Number Range of 1.40 to 2.78 of a Rocket-propelled Airplane Configuration Having a Low 52.2© Delta Wing and an Unswept Horizontal Tail by Alan B. Kehlet. Download full books in PDF and EPUB format.
Author: Alan B. Kehlet
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 30
Get Book
Book Description
Author: Alan B. Kehlet
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 30
Get Book
Book Description
Author: Alan B. Kehlet
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 30
Get Book
Book Description
Author: Alan B. Kehlet
Publisher:
ISBN:
Category :
Languages : en
Pages : 26
Get Book
Book Description
Author: Alan B. Kehlet
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 42
Get Book
Book Description
Author:
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 80
Get Book
Book Description
A free-flight rocket-propelled-model investigation was conducted at Mach numbers of 1.2 to 1.9 to determine the longitudinal and lateral aero-dynamic characteristics of a low-drag aircraft configuration. The model consisted of an aspect-ratio -1.86 arrow wing with 67.5 deg. leading-edge sweep and NACA 65A004 airfoil section and a triangular vertical tail with 60 deg. sweep and NACA 65A003 section in combination with a body of fineness ratio 20. Aerodynamic data in pitch, yaw, and roll were obtained from transient motions induced by small pulse rockets firing at intervals in the pitch and yaw directions. From the results of this brief aerodynamic investigation, it is observed that very slender body shapes can provide increased volumetric capacity with little or no increase in zero-lift drag and that body fineness ratios of the order of 20 should be considered in the design of long-range supersonic aircraft. The zero-lift drag and the drag-due-to-lift parameter of the test configuration varied linearly with Mach number. The maximum lift-drag ratio was 7.0 at a Mach number of 1.25 and decreased slightly to a value of 6.6 at a Mach number of 1.81. The optimum lift coefficient, normal-force-curve slope, lateral-force-curve slope, static stability in pitch and yaw, time to damp to one-half amplitude in pitch and yaw, the sum of the rotary damping derivatives in pitch and also in yaw, and the static rolling derivatives all decreased with an increase in Mach number. Values of certain rolling derivatives were obtained by application of the least-squares method to the differential equation of rolling motion. A comparison of the experimental and calculated total rolling-moment-coefficient variation during transient oscillations of the model indicated good agreement when the damping-in-roll contribution was included with the static rolling-moment terms.
Author: Clarence L. Gillis
Publisher:
ISBN:
Category : Mach number
Languages : en
Pages : 46
Get Book
Book Description
Author: William John Small
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 36
Get Book
Book Description
Author: Louis E. Clark
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 68
Get Book
Book Description
Author: Gerald V. Foster
Publisher:
ISBN:
Category : Airplanes, Tailless
Languages : en
Pages : 54
Get Book
Book Description
Author: Walter P. Nelms
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 108
Get Book
Book Description
Aerodynamic characteristics of a model designed to represent an all body, hypersonic cruise aircraft are presented for Mach numbers from 0.65 to 10.6. The configuration had a delta planform with an elliptic cone forebody and an afterbody of elliptic cross section. Detailed effects of varying angle of attack (-2 to 15 deg), angle of sideslip (-2 to 8 deg), Mach number, and configuration buildup were considered. In addition, the effectiveness of horizontal tail, vertical tail, and canard stabilizing and control surfaces was investigated. The results indicate that all configurations were longitudinally stable near maximum lift drag ratio. The configurations with vertical tails were directionally stable at all angles of attack. Trim penalties were small at hypersonic speeds for a center of gravity location representative of the airplane, but because of the large rearward travel of the aerodynamic center, trim penalties were severe at transonic Mach numbers.
