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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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.
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.
Strut Support Interference On A Cylindrical Model With Boattail At Mach Numbers From 0 6 To 1 4
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Author : R. C. German
language : en
Publisher:
Release Date : 1976
Strut Support Interference On A Cylindrical Model With Boattail At Mach Numbers From 0 6 To 1 4 written by R. C. German and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1976 with categories.
An investigation was conducted in the Aerodynamic Wind Tunnel (1T), with a sting-mounted, ogive-cylinder model and various dummy strut designs, to provide further information on sources of nozzle afterbody (NAB) interference and to determine how incremental changes in afterbody boattail and base pressures are affected by changes in support strut design and location. The investigation also included the effect of changing local wall porosity on the NAB interference. An analysis of pressure data obtained on the model, boattail, base, and tunnel wall surfaces at Mach numbers from 0.6 to 1.4 indicates that interference occurs above Mach 0.99 as the result of disturbances generated by the strut leading edge which are reflected from the tunnel wall to the NAB. This interference can be minimized by using a swept strut; however, the optimum strut sweep angle and strut location is a function of Mach number and NAB geometry. (Author).
Critical Sting Length As Determined By The Measurement Of Pitch Damping Derivatives For Laminar Transitional And Turbulent Boundary Layers At Mach Number 3 For Reduced Frequencies Of 0 0033 And 0 0056
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Author :
language : en
Publisher:
Release Date : 1977
Critical Sting Length As Determined By The Measurement Of Pitch Damping Derivatives For Laminar Transitional And Turbulent Boundary Layers At Mach Number 3 For Reduced Frequencies Of 0 0033 And 0 0056 written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1977 with categories.
A research program was initiated for the purpose of investigating some of the problem areas in regard to support interference in supersonic wind tunnels. The critical sting length at alpha = 0 was determined by the measurement of pitch-damping derivatives for laminar, transitional, and turbulent boundary layers at the model base. The effect of wedge splitter plates on sting interference was also investigated. By utilizing the small amplitude forced oscillation technique, data were obtained at Mach number 3 on a blunt 7-deg cone for reduced frequencies of 0.0033 and 0.0056. The results showed that the critical sting length with respect to sting interference on pitch-damping data was two model diameters for the two reduced frequencies investigated and was independent of the type of boundary layer at the model base. Decreasing the effective sting length from 3.3 to one model diameter increased the model base pressure substantially and the model surface pressure slightly. The critical sting length for minimal base pressure interference is 2.5 model diameters for this model and these test conditions.
Sting Interference Effects On The Sdm Aircraft As Determined By Measurements Of Dynamic Stability Derivatives And Base Pressure For Mach Numbers 0 3 Through 1 3
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Author : F. B. Cyran
language : en
Publisher:
Release Date : 1980
Sting Interference Effects On The Sdm Aircraft As Determined By Measurements Of Dynamic Stability Derivatives And Base Pressure For Mach Numbers 0 3 Through 1 3 written by F. B. Cyran and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1980 with categories.
An investigation was conducted to determine the effects of sting-support interference on the measurement of pitch damping, yaw-damping, pitching-moment slope, yawing-moment slope, pitching moment, and base pressure. The model was the Standard Dynamics Model (SDM). The forced oscillation technique was used to obtain data at Mach numbers 0.3 to 1.3 and Reynolds numbers, based on the model mean aerodynamic chord (MAC), of 0.3 million to 3.1 million. Amplitudes of oscillation were 1.0, 1.5, and 2.0 deg, and the reduced frequency parameter ranged from 0.009 to 0.032 radians.
An Investigation Of Sting Support Interference On Base Pressure And Forebody Chord Force At Mach Numbers From 0 60 To 1 30
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Author : Phillips J. Tunnell
language : en
Publisher:
Release Date : 1955
An Investigation Of Sting Support Interference On Base Pressure And Forebody Chord Force At Mach Numbers From 0 60 To 1 30 written by Phillips J. Tunnell and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1955 with categories.
Characteristics Of A Blunt Nosed Cylindrical Flared Body In Pitch At Transonic March Numbers
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Author :
language : en
Publisher:
Release Date : 1960
Characteristics Of A Blunt Nosed Cylindrical Flared Body In Pitch At Transonic March Numbers 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.
Subsonic Sting Interference On The Aerodynamic Characteristics Of A Family Of Slanted Base Ogive Cylinders
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Author : Colin P. Britcher
language : en
Publisher:
Release Date : 1990
Subsonic Sting Interference On The Aerodynamic Characteristics Of A Family Of Slanted Base Ogive Cylinders written by Colin P. Britcher and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1990 with Aerodynamics categories.
An Investigation Of The Interference Effects Of A Sting Support System On The Pressure Distribution Over A Body Of Revolution
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Author : Harris M. Schurmeier
language : en
Publisher:
Release Date : 1949
An Investigation Of The Interference Effects Of A Sting Support System On The Pressure Distribution Over A Body Of Revolution written by Harris M. Schurmeier and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1949 with Electronic dissertations categories.