Dynamic Stability Characteristics of a Lo-deg Cone at Mach Number 20 PDF Download
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Author: R. H. Urban
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 14
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Book Description
Tests were conducted in the 30-Inch Hypersonic Tunnel on the Aerospace Research Laboratories, Wright-Patterson Air Force Base, Ohio to determine the effects of Reynolds number and frequency of oscillation on the damping-in-pitch derivatives of a 10-deg half-angle cone. Free oscillation data were obtained at a nominal Mach number of 20, at Reynolds numbers, based on model base diameter, from 50,000 to 100,000, and at model oscillation frequencies from 8 to 45 cps. Test results are presented, and comparisons are made with modified Newtonian impact theory and an unsteady flow field theory. (Author).
Author: R. H. Urban
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 14
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Book Description
Tests were conducted in the 30-Inch Hypersonic Tunnel on the Aerospace Research Laboratories, Wright-Patterson Air Force Base, Ohio to determine the effects of Reynolds number and frequency of oscillation on the damping-in-pitch derivatives of a 10-deg half-angle cone. Free oscillation data were obtained at a nominal Mach number of 20, at Reynolds numbers, based on model base diameter, from 50,000 to 100,000, and at model oscillation frequencies from 8 to 45 cps. Test results are presented, and comparisons are made with modified Newtonian impact theory and an unsteady flow field theory. (Author).
Author: R. H. Urban
Publisher:
ISBN:
Category : Hypersonic wind tunnels
Languages : en
Pages : 28
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Book Description
Author: A. E. Hodapp (Jr.)
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 32
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Book Description
Author: B. L. Uselton
Publisher:
ISBN:
Category :
Languages : en
Pages : 23
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Book Description
Tests were conducted in the 50-in. Mach 10 wind tunnel of the von Karman Gas Dynamics Facility to determine the dynamic stability characteristics of a 10-deg half-angle cone at large amplitudes of oscillation. Support interference effects were also investigated. A free oscillation, high-amplitude (+ or - 35 deg) gas bearing balance supported by a transverse rod and yoke system was used. Data were obtained at a nominal Mach number of 10 at Reynolds numbers, based on the model base diameter, ranging from 0.46 to 1.84 x 10 to the 6th power. The dynamic and static stability data are compared with data obtained with a sting-supported model, range data, flow field theory, and conical flow theory. Selected test results are presented. (Author).
Author: Peter F. Intrieri
Publisher:
ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 36
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Book Description
Author: L. K Ward (Jr)
Publisher:
ISBN:
Category :
Languages : en
Pages : 24
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Book Description
Wind tunnel tests were conducted at Mach number 10 on a 9-deg half-angle cone model using a unique dynamic stability balance having three angular degrees of freedom. Data obtained at Re = 1,970,000 on models having different types of compound asymmetries revealed vast differences in the developed motion. A model with a center-of-gravity offset and a small, out-of-plane nose slice as the second asymmetry was found to have a totally unexpected type of instability. The instability was the rapid divergence of the precession arm caused by a Magnus-type moment resulting from an out-of-plane force generated by the nose slice. When the slice was removed (sharp nose model) and the second asymmetry applied by uing a small tab at the base, the classical roll resonance was found. (Author).
Author: Peter F. Intrieri
Publisher:
ISBN:
Category : Noses (Space vehicles)
Languages : en
Pages : 40
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Book Description
Author: William R. Wehrend
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 28
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
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Book Description
Wind tunnel tests were conducted at Mach number 10 on a 9-deg half-angle cone model using a unique dynamic stability balance having three angular degrees of freedom. Data obtained at Re = 1,970,000 on models having different types of compound asymmetries revealed vast differences in the developed motion. A model with a center-of-gravity offset and a small, out-of-plane nose slice as the second asymmetry was found to have a totally unexpected type of instability. The instability was the rapid divergence of the precession arm caused by a Magnus-type moment resulting from an out-of-plane force generated by the nose slice. When the slice was removed (sharp nose model) and the second asymmetry applied by uing a small tab at the base, the classical roll resonance was found. (Author).
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 44
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Book Description
