Author: Eugene N. Brooks
Publisher:
ISBN:
Category :
Languages : en
Pages : 44
Book Description
Static Aerodynamic Characteristics of a Model of a Typical Subsonic Jet-transport Airplane at Mach Numbers from 0.40 to 1.20
Author: Eugene N. Brooks
Publisher:
ISBN:
Category :
Languages : en
Pages : 44
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 44
Book Description
The Subsonic Static Aerodynamic Characteristics of an Airplane Model Having a Triangular Wing of Aspect Ratio 3
Author: Howard F. Savage
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 662
Book Description
An investigation has been conducted to determine the effects of vertical-tail location and size on the subsonic aerodynamic characteristics of a model having a triangular wing. The wing had an aspect ratio of 3, an NACA 0003.5-63 section in the streamwise direction, and plain, trailing-edge ailerons. The wing was attached to the fuselage in either a mid or high position and an unswept horizontal tail was located on the fuselage center line. Two vertical tails were tested which had areas of 26.7 or 20.3 percent of the wing area. Each vertical tail was equipped with a rudder and had a geometric aspect ratio of 1.5, a taper ratio of 0.16, and 54 degrees of sweepback of the leading edge. Each vertical tail was tested at two different tail lengths. The wind-tunnel tests were conducted at a Reynolds number of 2.5 milMon at Mach numbers from 0.25 to 0.95.
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 662
Book Description
An investigation has been conducted to determine the effects of vertical-tail location and size on the subsonic aerodynamic characteristics of a model having a triangular wing. The wing had an aspect ratio of 3, an NACA 0003.5-63 section in the streamwise direction, and plain, trailing-edge ailerons. The wing was attached to the fuselage in either a mid or high position and an unswept horizontal tail was located on the fuselage center line. Two vertical tails were tested which had areas of 26.7 or 20.3 percent of the wing area. Each vertical tail was equipped with a rudder and had a geometric aspect ratio of 1.5, a taper ratio of 0.16, and 54 degrees of sweepback of the leading edge. Each vertical tail was tested at two different tail lengths. The wind-tunnel tests were conducted at a Reynolds number of 2.5 milMon at Mach numbers from 0.25 to 0.95.
Longitudinal Aerodynamic Characteristics of a High-subsonic-speed Transport Airplane Model with a Cambered 40° Sweptback Wing of Aspect Ratio 8 at Mach Numbers to 0.96
Author: Atwood R. Heath
Publisher:
ISBN:
Category : Mach number
Languages : en
Pages : 92
Book Description
Publisher:
ISBN:
Category : Mach number
Languages : en
Pages : 92
Book Description
Longitudinal Aerodynamic Characteristics of a High-subsonic-speed Transport Airplane Model with a Cambered 40 Deg Sweptback Wing of Aspect Ratio 8 at Mach Numbers to 0.96
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 96
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 96
Book Description
Static Longitudinal Characteristics at High Subsonic Speeds of a Complete Airplane Model with a Highly Tapered Wing Having the 0.80 Chord Line Unswept and with Several Tail Configurations
Author: Kenneth W. Goodson
Publisher:
ISBN:
Category : Stability of airplanes, Longitudinal
Languages : en
Pages : 64
Book Description
An investigation was made at high subsonic speeds of a complete model having a highly tapered wing and several tail configurations. The basic aspect-ratio-4.00 wing had a zero taper and an unswept 0.80 chord line. Several aspect-ratio modifications to the basic wing were made by clipping off portions of the wing tips. The complete model was tested with a chord-plane tail, a T-tail, and a biplane tail (combined T-tail and chord-plane tail). The model was tested in the Langley high-speed 7- by 10-foot tunnel at Mach numbers from 0.60 to 0.92. The data show that, when reduced to the same static margin, all the tail configurations tested on the model provided fairly good stability characteristics, the biplane tail giving the best overall characteristics as regards pitching-moment linearity. Changes in static margin at zero lift coefficient with Mach number were small for the model with these tails over the Mach number range investigated.
Publisher:
ISBN:
Category : Stability of airplanes, Longitudinal
Languages : en
Pages : 64
Book Description
An investigation was made at high subsonic speeds of a complete model having a highly tapered wing and several tail configurations. The basic aspect-ratio-4.00 wing had a zero taper and an unswept 0.80 chord line. Several aspect-ratio modifications to the basic wing were made by clipping off portions of the wing tips. The complete model was tested with a chord-plane tail, a T-tail, and a biplane tail (combined T-tail and chord-plane tail). The model was tested in the Langley high-speed 7- by 10-foot tunnel at Mach numbers from 0.60 to 0.92. The data show that, when reduced to the same static margin, all the tail configurations tested on the model provided fairly good stability characteristics, the biplane tail giving the best overall characteristics as regards pitching-moment linearity. Changes in static margin at zero lift coefficient with Mach number were small for the model with these tails over the Mach number range investigated.
Static Lateral Characteristics at High Subsonic Speeds of a Complete Airplane Model with a Highly Tapered Wing Having the 0.80 Chord Line Unswept and with Several Tail Configuration
Author: Kenneth W. Goodson
Publisher:
ISBN:
Category : Stability of airplanes, Lateral
Languages : en
Pages : 102
Book Description
An investigation was made at high subsonic speeds of a complete model having a highly tapered wing and several tail configurations. The aspect-ratio-3.50 wing had a taper of 0.067 and an unswept 0.80 chord line. The complete model was tested with a wing-chord-plane tail, a T-tail, and a biplane tail (combined T-tail and wing-chord-plane tail). The model was tested in the Langley high-speed 7- by 10-foot tunnel at Mach numbers from 0.60 to 0.92 over a range of angle of attack of about ±20° and a range of sideslip of -15° to 13°. Some data were obtained with the horizontal stabilizer deflected. A few tests were also made with the wing tips clipped to an aspect ratio of 3.00.
Publisher:
ISBN:
Category : Stability of airplanes, Lateral
Languages : en
Pages : 102
Book Description
An investigation was made at high subsonic speeds of a complete model having a highly tapered wing and several tail configurations. The aspect-ratio-3.50 wing had a taper of 0.067 and an unswept 0.80 chord line. The complete model was tested with a wing-chord-plane tail, a T-tail, and a biplane tail (combined T-tail and wing-chord-plane tail). The model was tested in the Langley high-speed 7- by 10-foot tunnel at Mach numbers from 0.60 to 0.92 over a range of angle of attack of about ±20° and a range of sideslip of -15° to 13°. Some data were obtained with the horizontal stabilizer deflected. A few tests were also made with the wing tips clipped to an aspect ratio of 3.00.
Longitudinal Aerodynamic Characteristics at Mach Numbers from 0.50 to 1.19 of a Supersonic Transport Model with a Modified M Wing
Author: Edward J. Ray
Publisher:
ISBN:
Category :
Languages : en
Pages : 84
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 84
Book Description
Aerodynamic Characteristics of a Canard and an Outboard-tail Airplane Model at High Subsonic Speeds
Author: Paul G. Fournier
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 72
Book Description
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 72
Book Description
Transonic Aerodynamic Characteristics of a Model of a Supersonic Fighter-bomber Airplane with External Fuel Tanks and Other Modifications
Author: James C. Ferris
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 66
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 66
Book Description
The Subsonic Static Aerodynamic Characteristics of an Airplane Model Having a Triangular Wing of Aspect Ratio 3
Author: Bruce E. Tinling
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 85
Book Description
An investigation has been conducted to determine the effects of horizontal-tail location and size on the longitudinal aerodynamic characteristics of an airplane model having a triangular wing. The wing had an aspect ratio of 3 and the NACA 0003.5-63 section in the streamwise direction. Two horizontal tails were tested which had areas of either 16.7 or 21.9 percent of the wing area. Each of the horizontal tails had an aspect ratio of 4, a taper ratio of 0.33, the NACA 0004-64 section, and no sweepback of the 50-percent-chord line. Tests were conducted with the horizontal.tails located -0.10, 0, 0.10, and 0.20 wing semispans above the chord plane of the wing at longitudinal distances of 1.2 and 1.5 mean aerodynamic chord lengths behind the moment center. The wind-tunnel tests were conducted at a Reynolds number of 2.5 miJJion at Mach numbers from 0.25 to 0.95.
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 85
Book Description
An investigation has been conducted to determine the effects of horizontal-tail location and size on the longitudinal aerodynamic characteristics of an airplane model having a triangular wing. The wing had an aspect ratio of 3 and the NACA 0003.5-63 section in the streamwise direction. Two horizontal tails were tested which had areas of either 16.7 or 21.9 percent of the wing area. Each of the horizontal tails had an aspect ratio of 4, a taper ratio of 0.33, the NACA 0004-64 section, and no sweepback of the 50-percent-chord line. Tests were conducted with the horizontal.tails located -0.10, 0, 0.10, and 0.20 wing semispans above the chord plane of the wing at longitudinal distances of 1.2 and 1.5 mean aerodynamic chord lengths behind the moment center. The wind-tunnel tests were conducted at a Reynolds number of 2.5 miJJion at Mach numbers from 0.25 to 0.95.