Sting Interference Effects On The Modified Basic Finner Missile At Mach Numbers 0 3 Through 1 3

DOWNLOAD
Download Sting Interference Effects On The Modified Basic Finner Missile At Mach Numbers 0 3 Through 1 3 PDF/ePub or read online books in Mobi eBooks. Click Download or Read Online button to get Sting Interference Effects On The Modified Basic Finner Missile At Mach Numbers 0 3 Through 1 3 book now. This website allows unlimited access to, at the time of writing, more than 1.5 million titles, including hundreds of thousands of titles in various foreign languages. If the content not found or just blank you must refresh this page
Sting Interference Effects On The Modified Basic Finner Missile At Mach Numbers 0 3 Through 1 3
DOWNLOAD
Author : Edward J. Marquart
language : en
Publisher:
Release Date : 1982
Sting Interference Effects On The Modified Basic Finner Missile At Mach Numbers 0 3 Through 1 3 written by Edward J. Marquart and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1982 with Ballistic missiles categories.
Technical Abstract Bulletin
DOWNLOAD
Author :
language : en
Publisher:
Release Date : 1982
Technical Abstract Bulletin written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1982 with Science categories.
Sting Interference Effects On The Modified Basic Finner Missile At Mach Numbers 0 3 Through 1 3
DOWNLOAD
Author : Edward J. Marquart
language : en
Publisher:
Release Date : 1982
Sting Interference Effects On The Modified Basic Finner Missile At Mach Numbers 0 3 Through 1 3 written by Edward J. Marquart and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1982 with Ballistic missiles categories.
Sting Interference Effects As Determined By Measurements Of Dynamic Stability Derivatives Surface Pressure And Base Pressure For Mach Numbers 2 Through 8
DOWNLOAD
Author : Bob L. Uselton
language : en
Publisher:
Release Date : 1980
Sting Interference Effects As Determined By Measurements Of Dynamic Stability Derivatives Surface Pressure And Base Pressure For Mach Numbers 2 Through 8 written by Bob L. Uselton and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1980 with Hypersonic wind tunnels categories.
Wind tunnel tests were conducted to provide support interference information for planning and directing wind tunnel tests at supersonic and hypersonic Mach numbers. Sting-length and sting-diameter effects on base and surface pressures of a blunt 6-deg cone with a sliced base were investigated at Mach numbers 2, 3, 5, and 8. Dynamic stability tests on a blunt 7-deg cone were also conducted at Mach numbers 2, 5, and 8. The objectives of the 7-deg cone tests were to define critical sting lengths as determined by the measurement of dynamic stability derivatives, static pitching moment, and base pressure. Two frequencies of oscillation were investigated, and data were obtained for laminar, transitional, and turbulent boundary-layer conditions at the model base. The data from the 6- and 7-deg cone tests showed that the critical sting length depended on the interference indicator, Mach number, angle of attack, state of the model boundary layer, and frequency of oscillation. The critical sting length was generally less for models with turbulent boundary layers than for those with laminar boundary layers. A critical sting length of 2.5 model diameters was determined to be suitable for all test conditions that produced a turbulent boundary layer at or ahead of the model base.
Aristo E Temira E Orfeo Ed Euridice Drammi Per Musica
DOWNLOAD
Author :
language : en
Publisher:
Release Date : 1776
Aristo E Temira E Orfeo Ed Euridice Drammi Per Musica written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1776 with categories.
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
DOWNLOAD
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.
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
DOWNLOAD
Author : Bob L. Uselton
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 Bob L. Uselton and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1977 with Pitching (Aerodynamics) 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
DOWNLOAD
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.
Sting Effects In Hypersonic Base Pressure Measurements
DOWNLOAD
Author :
language : en
Publisher:
Release Date : 1971
Sting Effects In Hypersonic Base Pressure Measurements written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1971 with categories.
Sting interference effects were investigated at nominal Mach numbers of 6.3 and 9.9. Sting mounted and instrumented free flight sharp cone mocels were used at a unit Reynolds number of about 1,000,000/ft. Measurements showed that the base pressure distribution changes little below angle of attack = 15 degrees but becomes highly nonuniform and sensitive to angle of attack changes at high angles of incidence. Sting interference effects are not very severe at M = 6.3 when angle of attack less than 20 degrees, but as the angle of attack increases, the flow becomes progressively more distorted. Consequently, the base pressure values of the sting mounted model deviate from the free flight interference free model measurements. Beyond about 40 degrees, due to the severe effects of sting interference, no steady base pressure value could be reached with the sting mounted model in either of the tested Mach numbers. For the free flight model at Mach number 9.9, the magnitude of the measured base pressure ratios at corresponding flow conditions and angles of attack were about 70 percent above the sting mounted model showing how serious sting interference can be.
Aerodynamic Interference Effects Caused By Parallel Staged Simple Aerodynamic Configurations At Mach Numbers Of 3 And 6
DOWNLOAD
Author : John P. Decker
language : en
Publisher:
Release Date : 1969
Aerodynamic Interference Effects Caused By Parallel Staged Simple Aerodynamic Configurations At Mach Numbers Of 3 And 6 written by John P. Decker and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1969 with Launch vehicles (Astronautics) categories.
Aerodynamic characteristics effected by parallel- staged simple aerodynamic configurations at Mach numbers of 3 and 6.