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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Scientific And Technical Aerospace Reports
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Author :
language : en
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Release Date : 1981
Scientific And Technical Aerospace Reports written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1981 with Aeronautics categories.
Nasa Sp
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Author :
language : en
Publisher:
Release Date : 1981
Nasa Sp written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1981 with Aeronautics categories.
Aeronautical Engineering
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language : en
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Release Date : 1981
Aeronautical Engineering written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1981 with Aeronautics categories.
A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA)
Government Reports Announcements Index
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language : en
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Release Date : 1982
Government Reports Announcements Index 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.
Government Reports Annual Index
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language : en
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Release Date : 1982
Government Reports Annual Index 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 Government reports announcements & index categories.
A Collection Of Technical Papers
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language : en
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Release Date : 1982
A Collection Of Technical Papers 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 Aerodynamics categories.
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.
Hosmer S Interest And Discount Table
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language : en
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Release Date : 1839*
Hosmer S Interest And Discount Table written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1839* with Interest 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
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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.
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.