Effects Of Sting Support Interference On The Drag Of An Ogive Cylinder Body With And Without A Boattail At 0 6 To 1 4 Mach Number

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Sting Support Interference On Longitudinal Aerodynamic Characteristics Of Cargo Type Airplane Models At Mach 0 70 To 0 84

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Author : Donald L. Loving
language : en
Publisher:
Release Date : 1967

Sting Support Interference On Longitudinal Aerodynamic Characteristics Of Cargo Type Airplane Models At Mach 0 70 To 0 84 written by Donald L. Loving and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1967 with Airplanes categories.

Nasa Technical Paper

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Author :
language : en
Publisher:
Release Date : 1979

Nasa Technical Paper written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1979 with Astronautics categories.

Nasa Technical Note

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Author :
language : en
Publisher:
Release Date : 1967

Nasa Technical Note written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1967 with categories.

Effects Of A Sting Support On The Supersonic Force And Moment Characteristics Of An Apollo Model At Angles From 30 Deg To 185 Deg

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Author :
language : en
Publisher:
Release Date : 1965

Effects Of A Sting Support On The Supersonic Force And Moment Characteristics Of An Apollo Model At Angles From 30 Deg To 185 Deg written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1965 with categories.

Drag Measurements From Different Wind Tunnels

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Author :
language : en
Publisher:
Release Date : 1966

Drag Measurements From Different Wind Tunnels written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1966 with categories.

International Aerospace Abstracts

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Author :
language : en
Publisher:
Release Date : 1991

International Aerospace Abstracts written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1991 with Aeronautics categories.

Effects Of Sting Support Interference On The Drag Of An Ogive Cylinder Body With And Without A Boattail At 0 6 To 1 4 Mach Number

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Author : George Lee
language : en
Publisher:
Release Date : 1957

Effects Of Sting Support Interference On The Drag Of An Ogive Cylinder Body With And Without A Boattail At 0 6 To 1 4 Mach Number written by George Lee and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1957 with Body of revolution categories.

Tests were conducted to determine the effects of sting-support interference on the zero-lift drag of two bodies of revolution (with and without boattailing). The sting support consisted of a constant-diameter sting followed by a sting flare terminating in a cylindrical support. Various sting diameters, sting lengths, and sting flare angles were tested at Mach number of 0.6 to 1.5 and a Reynolds number of 8 million based on model length.

An Experimental Investigation Of Sting Support Effects On Drag And A Comparison With Jet Effects At Transonic Speeds

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Author : Maurice S. Cahn
language : en
Publisher: BiblioGov
Release Date : 2013-06

An Experimental Investigation Of Sting Support Effects On Drag And A Comparison With Jet Effects At Transonic Speeds written by Maurice S. Cahn and has been published by BiblioGov this book supported file pdf, txt, epub, kindle and other format this book has been release on 2013-06 with categories.

This paper presents the results of an investigation of sting-support interference on afterbody drag at transonic speeds. Stings with varying diameter, cone angle, and cylindrical length were tested at the rear of a model with various afterbody shapes. The data were obtained at an angle of attack of O deg. and at Mach numbers from 0.80 to 1.10. It was found that, in general, the addition of a sting caused a drag reduction. A method is presented whereby approximate sting-interference corrections may be made to models with afterbodies and sting supports of similar size and scale to those of this paper provided the boundary layer is turbulent at the model base and the Reynolds numbers are of the same order of magnitude. Reynolds number of the tests presented varied from 15.0 x 10 (exp 6) to 17.4 x 10 (exp 6) based on body length. Sting effects from this investigation are compared with data of jet effects on the same afterbodies. The results of this comparison indicate that for the more gradually contoured afterbodies, a sting shape can be found which will duplicate the jet effects, but that for blunt afterbodies no solid sting shape will duplicate the jet effects.

Effects Of Sting Support Interference On The Base Pressures Of A Model Having A Blunt Nosed Cylinder Body And A Conical Flare At Mach Numbers Of 0 65 To 2 20

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Author :
language : en
Publisher:
Release Date : 1960

Effects Of Sting Support Interference On The Base Pressures Of A Model Having A Blunt Nosed Cylinder Body And A Conical Flare At Mach Numbers Of 0 65 To 2 20 written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1960 with categories.

Experimental Investigation Of The Effects Of Support Interference On The Drag Of Bodies Of Revolution At A Mach Number Of 1 5

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Author : Edward W. Perkins
language : en
Publisher:
Release Date : 1951

Experimental Investigation Of The Effects Of Support Interference On The Drag Of Bodies Of Revolution At A Mach Number Of 1 5 written by Edward W. Perkins and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1951 with Body of revolution categories.

This report contains the results of an experimental investigation to determine the effects of support interference on the base drag and fore drage of two bodies of revolution. The results show that the rear supports affect the drag of a body of revolution through the immediate influence on the pressures acting over the rear portions of the body and thus the magnitude of the interference depends on the afterbody shape of the model, the Reynolds number of flow, and the condition of the boundary layer.