A Wind-tunnel Test Technique for Measuring the Dynamic Rotary Stability Derivatives Including the Cross Derivatives at High Mach Numbers PDF Download
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Author: Benjamin H. Beam
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 44
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Book Description
A method is described for measuring the dynamic stability derivatives of a model airplane in a wind tunnel. The characteristics features of this system are that single-degree-of-freedom oscillations were used to obtain combinations of rolling, yawing, and pitching motions; that the oscillations were excited and controlled by velocity feedback which permitted operation under conditions unfavorable for more conventional types of oscillatory testing; and that data processing was greatly simplified by using analog computer elements in the strain-gage circuitry.
Author: Benjamin H. Beam
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 44
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Book Description
A method is described for measuring the dynamic stability derivatives of a model airplane in a wind tunnel. The characteristics features of this system are that single-degree-of-freedom oscillations were used to obtain combinations of rolling, yawing, and pitching motions; that the oscillations were excited and controlled by velocity feedback which permitted operation under conditions unfavorable for more conventional types of oscillatory testing; and that data processing was greatly simplified by using analog computer elements in the strain-gage circuitry.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 528
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Author: John DeYoung
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 688
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Book Description
A rapid method for estimating the downwash behind swept-wing airplanes is presented. The basic assumption is that of a flat horizontal sheet of vortices trailing behind the wing. The integrations for the downwash are handled in a manner similar to both Multhopp's and Weissinger's approximate integrations in their span-loading calculations. The principal effects of rolling-up of the wake are treated as corrections to the flat-sheet wake. A simple approximate correction for the effect of the fuselage is applied. The agreement with available experimental data taken behind airplane models is good. Computing forms are included together with charts of pertinent functions, so as to enable simple direct application.
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1276
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Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 48
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Author: R. J. Volluz
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 512
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Author: Johns Hopkins University. Applied Physics Laboratory, Silver Spring, Md
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 516
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Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages :
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Book Description
Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.
Author: Benjamin H. Beam
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 14
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 962
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