Author: Dennis E. Fuller
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 38
Book Description
Effect of Afterbody Geometry and Sting Diameter on the Aerodynamic Characteristics of Slender Bodies at Mach Number from 1.57 to 2.86
Author: Dennis E. Fuller
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 38
Book Description
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 38
Book Description
Effect of Afterbody Geometry and Sting Diameter on the Aerodynamic Characteristics of Slender Bodies at Mach Number from 1.57 to 2.86
Author: Dennis E. Fuller
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 0
Book Description
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 0
Book Description
Effect of Afterbody Geometry on Aerodynamic Characteristics of Isolated Nonaxisymmetric Afterbodies at Transonic Mach Numbers
Author: Linda S. Bangert
Publisher:
ISBN:
Category : Drag (Aerodynamics)
Languages : en
Pages : 272
Book Description
Publisher:
ISBN:
Category : Drag (Aerodynamics)
Languages : en
Pages : 272
Book Description
The Effect of Afterbody Geometry on the Aerodynamic Characteristics of Rectangular Afterbodies at Transonic Mach Numbers
Author: Linda S. Bangert
Publisher:
ISBN:
Category :
Languages : en
Pages : 224
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 224
Book Description
Calculated Pressure Distributions and Components of Total-drag Coefficients for 18 Constant-volume Slender Bodies of Revolution at Zero Incidence for Mach Numbers from 2.0 to 12.0, with Experimental Aerodynamic Characteristics for Three of the Bodies
Author: Louis S. Stiver
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 108
Book Description
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 108
Book Description
Effect of Afterbody Geometry on Aerodynamic Characteristics of Isolated Nonaxisymmetric Afterbodies at Transonic Mach Numbers
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781723563997
Category :
Languages : en
Pages : 272
Book Description
A parametric study was conducted in the Langley 16-Foot Transonic Tunnel on an isolated nonaxisymmetic fuselage model that simulates a twin-engine fighter. The effects of aft-end closure distribution (top/bottom) nozzle-flap boattail angle versus nozzle-sidewall boattail angle) and afterbody and nozzle corner treatment (sharp or radius) were investigated. Four different closure distributions with three different corner radii were tested. Tests were conducted over a range of Mach numbers from 0.40 to 1.25 and over a range of angles of attack from -3 to 9 degrees. Solid plume simulators were used to simulate the jet exhaust. For a given closure distribution in the range of Mach numbers tested, the sharp-corner nozzles generally had the highest drag, and the 2-in. corner-radius nozzles generally had the lowest drag. The effect of closure distribution on afterbody drag was highly dependent on configuration and flight condition. Bangert, Linda S. and Carson, George T., Jr. Langley Research Center NASA-TP-3236, L-17034, NAS 1.60:3236 RTOP 505-62-30-01...
Publisher: Createspace Independent Publishing Platform
ISBN: 9781723563997
Category :
Languages : en
Pages : 272
Book Description
A parametric study was conducted in the Langley 16-Foot Transonic Tunnel on an isolated nonaxisymmetic fuselage model that simulates a twin-engine fighter. The effects of aft-end closure distribution (top/bottom) nozzle-flap boattail angle versus nozzle-sidewall boattail angle) and afterbody and nozzle corner treatment (sharp or radius) were investigated. Four different closure distributions with three different corner radii were tested. Tests were conducted over a range of Mach numbers from 0.40 to 1.25 and over a range of angles of attack from -3 to 9 degrees. Solid plume simulators were used to simulate the jet exhaust. For a given closure distribution in the range of Mach numbers tested, the sharp-corner nozzles generally had the highest drag, and the 2-in. corner-radius nozzles generally had the lowest drag. The effect of closure distribution on afterbody drag was highly dependent on configuration and flight condition. Bangert, Linda S. and Carson, George T., Jr. Langley Research Center NASA-TP-3236, L-17034, NAS 1.60:3236 RTOP 505-62-30-01...
The Aerodynamic Characteristics of a Body in the Flow Field Near the Tip of a Circular-arc Wing of Rectangular Plan Form at a Mach Number of 2.01
Author: John P. Gapcynski
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 44
Book Description
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 44
Book Description
Effect of Cross-section Shape on the Aerodynamics Characteristics of Bodies at Mach Numbers from 2.50 to 4.63
Author: Dennis E. Fuller
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 40
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 40
Book Description
Longitudinal Aerodynamic Characteristics of Several High-drag Bodies at Mach Numbers from 1.50 to 4.63
Author: James F. Campbell
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 44
Book Description
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 44
Book Description
Effects of Afterbody Shape on the Aerodynamic Characteristics of a Fineness-ratio-10 Cone- Cylinder Configuration at Mach Numbers from 1.57 to 4.65 Including Design Parameter Curves for Circular Afterbody Flares
Author: A. B. Carraway
Publisher:
ISBN:
Category :
Languages : en
Pages : 124
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 124
Book Description