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 PDF Download
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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.
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.
Author: Kenneth W. Goodson
Author: Kenneth W. Goodson
Author: United States. National Advisory Committee for Aeronautics
Author: 
Author: United States. Wright Air Development Division
Author: Kenneth P. Spreemann
Author: 
Author: United States. National Advisory Committee for Aeronautics
Author: United States. National Aeronautics and Space Administration
Author: Paul G. Fournier
Author: United States. National Aeronautics and Space Administration