› › Longitudinal Stability And Control Characteristics At Transonic Speeds Of A Semispan Airplane Model Having A 45 Degrees Sweptback Wing And Tail As Obtained By The Transonic Bump Method


Longitudinal Stability and Control Characteristics of a Semispan Airplane Model with a Swept-back Tail from Tests at Transonic Speeds by the NACA Wing-flow Method

Author : John A. Zalovcik

Publisher :

Page : 11 pages

File Size : 40,96 MB

Release : 1947

Category : Aerodynamics, Transonic

ISBN :

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Book Description

An investigation was made by the NACA wing-flow method to determine the longitudinal stability and control characteristics at transonic speeds of a semispan airplane model having a wing of conventional plan form and a horizontal tail swept back 45 degrees. The wing and tail had NACA 65-series airfoil sections with thicknesses of 10 and 8 percent chord, respectively. The model was mounted in such a way as to permit it to assume a position of zero pitching moment about a center of gravity at 27 percent of the mean aerodynamic chord. Measurements were made of lift and angle of attack for trim for several stabilizer and elevator settings.











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 :

Page : 64 pages

File Size : 27,15 MB

Release : 1961

Category : Stability of airplanes, Longitudinal

ISBN :

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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.







Longitudinal Stability and Control Characteristics at High Subsonic Speeds of Two Models of a Transonic Research Airplane with Wings and Horizontal Tails of Aspect Ratios 4.2 and 2

Author : Arvo A. Luoma

Publisher :

Page : 134 pages

File Size : 19,32 MB

Release : 1950

Category : Airplanes

ISBN :

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Book Description

An investigation was made in the Langley 8-foot high-speed tunnel of two transonic research airplane models for Mach numbers up to approximately 0.95. The test Reynolds number at the highest speed was 1,600,000 for one model and 2,300,000 for the other model. The models were 1/16-schale and were supported in the tunnel on a sting. The wing and horizontal tail of one model were both of aspect ratio 4.2; the wing and horizontal tail of the other model were both of aspect ratio 2. The same fuselage and vertical tail were used on both models. The sweep of the 50-percent-chord line of the wings was zero degrees; the sweep of the 75-percent-chord line of the horizontal tails was zero degrees. Both wings had NACA 65-110 airfoil sections and both horizontal tails had NACA 65-008 airfoil sections. Lift drag, and pitching moment were determined by means of a strain-gage balance within the fuselage. Tare measurements were made to eliminate the interference effect of the sting.