Lanterna Rally
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Preliminary Results for a Free-flight Investigation at Transonic and Supersonic Speeds of Longitudinal Stability and Control Characteristics of an Airplane Configuration with a Thin Straight Wing of Aspect Ratio 3
Determination of Longitudinal Stability and Control Characteristics from Free-flight Model Tests with Results at Transonic Speeds for Three Airplane Configurations
Determination of the Stability and Control Characteristics of Airplanes from Tests of Powered Models
Author: Isidore G. Recant
Publisher:
Published: 1942
Total Pages: 118
ISBN-13:
DOWNLOAD EBOOK →A technique of testing wind-tunnel powered models has been developed as a result of experience gained in the investigation of the static longitudinal and lateral stability and control characteristics of several powered models in the NACA 7- by 10-foot wind tunnel. As an important part of this technique, a minimum program of the tests considered necessary to specify satisfactorily the static stability and control characteristics for present-day airplanes has been tentatively established.
Longitudinal Stability Characteristics at Transonic Speeds of a Rocket-propelled Model of an Airplane Having a 45 Degree Swept Wing of Aspect Ratio 6.0
Determination of Lateral Stability Characteristics from Free-flight Model Tests, with Experimental Results on the Effects of Wing Vertical Position and Dihedral at Transonic Speeds
Author: Clarence L. Gillis
Publisher:
Published: 1960
Total Pages: 48
ISBN-13:
DOWNLOAD EBOOK →A test and analysis method is presented for determining airplane lateral stability characteristics, including aerodynamic derivatives, from flight tests of scale models. The method of analysis utilizes the rotating time-vector concept and also a quasi-static approach. Data are presented at transonic speeds for three swept-wing rocket-propelled models differing only in vertical position and dihedral of the wing. The method proved to be adequate for delineating the major effects of the geometric variations on the aerodynamic lateral stability derivatives. The effects of Reynolds number on the linearity of the static stability data for an unswept wing configuration are illustrated.
Some Data on the Static Longitudinal Stability and Control of Airplanes
Author: A. Martinov
Publisher:
Published: 1940
Total Pages: 672
ISBN-13:
DOWNLOAD EBOOK →In the solution of a number of problems on the stability and controllability of airplanes, there arises the necessity for knowing the characteristics of the tail surfaces of the types in common use today. Of those characteristics, the most important are the effectiveness and hinge moments of the tail surfaces. As has been shown in the present paper, there exists the possibility of determining these characteristics by the formulas obtained with a degree of accuracy sufficient for the purposes of preliminary computation. These formulas take into account a number of fundamental tail characteristics such as tail cut-outs on the control surface and the form of the control surface leading edge.
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:
Published: 1961
Total Pages: 64
ISBN-13:
DOWNLOAD EBOOK →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.
Investigation of the Low-subsonic Stability and Control Characteristics of a Free-flying Model of a Thick 70 Degree Delta Reentrry Configuration
Investigation of the Low-subsonic Stability and Control Characteristics of a 1/3-scale Free-flying Model of a Lifting-body Reentry Configuration
