Author: Paul T. Soderman
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 108
Book Description
The aerodynamic characteristics of a full scale executive type jet transport aircraft with a T-tail were investigated in a 40 x 80 ft (12.2 by 24.4 meter) wind tunnel (subsonic). Static, longitudinal, and lateral stability, and control characteristics were determined at angles of attack from -2 deg to 42 deg. The aircraft wing had 13 deg of sweep and an aspect ratio of 5.02. The aircraft was tested power off with various wing leading- and trailing-edge high lift devices. The basic configuration was tested with and without such components as engine nacelles, wing tip tanks, and empannage. Hinge-moment data were obtained and downwash angles in the horizontal-tail plane location were calculated. The data were obtained at Reynolds numbers of 4.1 million and 8.7 million based on mean aerodynamic chord. The model had static longitudinal stability through initial stall. Severe tail buffet occurred near the angle of attack for maximum lift. Above initial stall the aircraft had pronounced pitch-up, characteristic of T-tail configurations. A stable trim point was possible at angles of attack between 30 deg and 40 deg (depending on c.g. location and flap setting). Hinge-moment data showed no regions with adverse effects on stick force. Comparisons of wind-tunnel data and flight-test are presented.
Full-scale Wind-tunnel Tests of a Small Unpowered Jet Aircraft with a T-Tail
Author: Paul T. Soderman
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 108
Book Description
The aerodynamic characteristics of a full scale executive type jet transport aircraft with a T-tail were investigated in a 40 x 80 ft (12.2 by 24.4 meter) wind tunnel (subsonic). Static, longitudinal, and lateral stability, and control characteristics were determined at angles of attack from -2 deg to 42 deg. The aircraft wing had 13 deg of sweep and an aspect ratio of 5.02. The aircraft was tested power off with various wing leading- and trailing-edge high lift devices. The basic configuration was tested with and without such components as engine nacelles, wing tip tanks, and empannage. Hinge-moment data were obtained and downwash angles in the horizontal-tail plane location were calculated. The data were obtained at Reynolds numbers of 4.1 million and 8.7 million based on mean aerodynamic chord. The model had static longitudinal stability through initial stall. Severe tail buffet occurred near the angle of attack for maximum lift. Above initial stall the aircraft had pronounced pitch-up, characteristic of T-tail configurations. A stable trim point was possible at angles of attack between 30 deg and 40 deg (depending on c.g. location and flap setting). Hinge-moment data showed no regions with adverse effects on stick force. Comparisons of wind-tunnel data and flight-test are presented.
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 108
Book Description
The aerodynamic characteristics of a full scale executive type jet transport aircraft with a T-tail were investigated in a 40 x 80 ft (12.2 by 24.4 meter) wind tunnel (subsonic). Static, longitudinal, and lateral stability, and control characteristics were determined at angles of attack from -2 deg to 42 deg. The aircraft wing had 13 deg of sweep and an aspect ratio of 5.02. The aircraft was tested power off with various wing leading- and trailing-edge high lift devices. The basic configuration was tested with and without such components as engine nacelles, wing tip tanks, and empannage. Hinge-moment data were obtained and downwash angles in the horizontal-tail plane location were calculated. The data were obtained at Reynolds numbers of 4.1 million and 8.7 million based on mean aerodynamic chord. The model had static longitudinal stability through initial stall. Severe tail buffet occurred near the angle of attack for maximum lift. Above initial stall the aircraft had pronounced pitch-up, characteristic of T-tail configurations. A stable trim point was possible at angles of attack between 30 deg and 40 deg (depending on c.g. location and flap setting). Hinge-moment data showed no regions with adverse effects on stick force. Comparisons of wind-tunnel data and flight-test are presented.
Full-scale Wind-tunnel Tests of a Small Unpowered Jet Aircraft with a T-tail
Author: Paul T. Soderman
Publisher:
ISBN:
Category :
Languages : en
Pages : 93
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 93
Book Description
Results of Full-scale Wind Tunnel Tests on the H.126 Jet Flap Aircraft
Author: Anthony M. Cook
Publisher:
ISBN:
Category : Jet flaps (Airplanes)
Languages : en
Pages : 66
Book Description
Publisher:
ISBN:
Category : Jet flaps (Airplanes)
Languages : en
Pages : 66
Book Description
Large-scale Wind-tunnel Tests of a Circulation Plan-form Aircraft with a Peripheral Jet for Lift, Thrust, and Control
Author: Richard K. Grief
Publisher:
ISBN:
Category : Jet planes
Languages : en
Pages : 112
Book Description
Publisher:
ISBN:
Category : Jet planes
Languages : en
Pages : 112
Book Description
Low-Speed Wind Tunnel Testing
Author: Alan Pope
Publisher: Wiley-Interscience
ISBN:
Category : Science
Languages : en
Pages : 562
Book Description
Good,No Highlights,No Markup,all pages are intact, Slight Shelfwear,may have the corners slightly dented, may have slight color changes/slightly damaged spine.
Publisher: Wiley-Interscience
ISBN:
Category : Science
Languages : en
Pages : 562
Book Description
Good,No Highlights,No Markup,all pages are intact, Slight Shelfwear,may have the corners slightly dented, may have slight color changes/slightly damaged spine.
Large-scale Wind-tunnel Tests of an Airplane Model with an Unswept, Tilt Wing of Aspect Ration 5.5, and with Four Propellers and Blowing Flaps
Author: James A. Weiberg
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 38
Book Description
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 38
Book Description
Large-Scale Wind-Tunnel Tests of a Wingless Vertical Take-Off and Landing Aircraft: Preliminary Results
Author: David G. Koenig
Publisher:
ISBN:
Category :
Languages : en
Pages : 46
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 46
Book Description
Full-scale Wind-tunnel Tests of a Swept-wing Airplane with a Cascade-type Thrust Reverser
Author: Mark W. Kelly
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 36
Book Description
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 36
Book Description
Full-scale Wind-tunnel Tests of a Low-aspect-ratio, Straight-wing Airplane with Blowing Boundary-layer Control on Leading- and Trailing-edge Flaps
Author: Mark W. Kelly
Publisher:
ISBN:
Category : Trailing edge flaps
Languages : en
Pages : 32
Book Description
Publisher:
ISBN:
Category : Trailing edge flaps
Languages : en
Pages : 32
Book Description
Low Speed Wind Tunnel Tests on a One-seventh Scale Model of the H.126 Jet Flap Aircraft
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 94
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 94
Book Description