Techniques For Measurement Of Dynamic Stability Derivatives In Ground Test Facilities

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Techniques for Measurement of Dynamic Stability Derivatives in Ground Test Facilities

Clarence John Schueler,Linley K. Ward,A. E. Hodapp
Techniques for Measurement of Dynamic Stability Derivatives in Ground Test Facilities Book PDF

Author : Clarence John Schueler,Linley K. Ward,A. E. Hodapp
Publisher : Unknown
Page : 242 pages
File Size : 48,7 Mb
Release : 1967
Category : Aerodynamic measurements
ISBN : UCSD:31822015409758

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Techniques for Measurement of Dynamic Stability Derivatives in Ground Test Facilities by Clarence John Schueler,Linley K. Ward,A. E. Hodapp Pdf

Some of the techniques in current use for measuring dynamic stability derivatives in wind tunnels are described, with emphasis given to the important features of balance system design, data reduction methods, instrumentation and typical balance systems. The use of gas bearings for dynamic stability and roll damping balances is treated and a three-degree-of-freedom balance system employing a spherical gas bearing is described. (Author).

Evaluation of Critical Sting Length on a 7-deg Cone as Determined by Measurements of Dynamic Stability Derivatives and Base Pressure for Mach Numbers 0.2 Through 1.3

Frederick B. Cyran,Bob L. Uselton,Edward J. Marquart
Evaluation of Critical Sting Length on a 7 deg Cone as Determined by Measurements of Dynamic Stability Derivatives and Base Pressure for Mach Numbers 0 2 Through 1 3 Book PDF

Author : Frederick B. Cyran,Bob L. Uselton,Edward J. Marquart
Publisher : Unknown
Page : 58 pages
File Size : 41,9 Mb
Release : 1981
Category : Boundary layer
ISBN : UOM:39015104951804

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Evaluation of Critical Sting Length on a 7-deg Cone as Determined by Measurements of Dynamic Stability Derivatives and Base Pressure for Mach Numbers 0.2 Through 1.3 by Frederick B. Cyran,Bob L. Uselton,Edward J. Marquart Pdf

Wind tunnel tests were conducted to provide sting-support interference information for planning and directing wind tunnel tests at subsonic and transonic Mach numbers. Sting-length effects on dynamic stability derivatives, static pitching moment, and base pressure of a blunt, flat-base 7- deg cone were investigated at Mach numbers 0.2 to 1.3 in the Arnold Engineering Development Center (AEDC) Propulsion Wind Tunnel Facility (PWT). Two frequencies of oscillation, nominally 5.3 and 2.9 Hz, were investigated. The boundary-layer state at the model base was turbulent for all Mach numbers greater than 0.2. The interference effects of two types of model-wake splitter plates were also investigated. The results showed that the critical sting length depended on the Mach number, angle of attack, and type of data used as the interference indicator. A critical sting length of three model diameters was determined to be suitable for all test conditions for the ratio of sting-diameter-to-model-base- diameter (0.22) for this test.

NASA Technical Memorandum

Anonim
NASA Technical Memorandum Book PDF

Author : Anonim
Publisher : Unknown
Page : 296 pages
File Size : 45,6 Mb
Release : 1991
Category : Aeronautics
ISBN : MINN:31951P00218510W

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NASA Technical Memorandum by Anonim Pdf

An Investigation of Sting Interference Effects on an Oscillating Cone in Transonic Flow

Frederick B. Cyran,J. P. Christopher
An Investigation of Sting Interference Effects on an Oscillating Cone in Transonic Flow Book PDF

Author : Frederick B. Cyran,J. P. Christopher
Publisher : Unknown
Page : 92 pages
File Size : 47,5 Mb
Release : 1981
Category : Aerodynamics, Transonic
ISBN : UOM:39015104952042

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An Investigation of Sting Interference Effects on an Oscillating Cone in Transonic Flow by Frederick B. Cyran,J. P. Christopher Pdf

Wind tunnel sting support interference effects on dynamic stability derivatives, static pitching moment and base pressure of a blunt, 7-deg cone were investigated at subsonic and transonic Mach numbers. The cone was tested with sting configurations having a variable effective sting length ranging from 1 to 3.3 model base diameters, at angles of attack ranging from 0 to 30 deg. A forced-oscillation system was utilized to obtain data at a frequency of oscillation of approximately 5.3 Hz, and at an amplitude of 1 deg. The Reynolds number, based on model base diameter, was nominally 1.8 million, which produced a turbulent boundary layer over the aft portion of the model. The nature of the causes of these interference effects is discussed and analyzed with respect to sting length, type of measurement, and Mach number, with emphasis on defining critical sting length and on predicting minimal interference sting configurations for dynamic stability testing. The results showed that the critical sting length depended on the type of measurement used as the interference indicator, Mach number, and angle of attack. A critical sting length of three model diameters was determined to be suitable for all test conditions for the ratio of sting diameter-to-model base diameter (0.22) investigated. (Author).

Scientific and Technical Aerospace Reports

Anonim
Scientific and Technical Aerospace Reports Book PDF

Author : Anonim
Publisher : Unknown
Page : 700 pages
File Size : 46,9 Mb
Release : 1995
Category : Aeronautics
ISBN : UOM:39015038704915

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Scientific and Technical Aerospace Reports by Anonim Pdf

Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.

A Collection of Technical Papers

Anonim
A Collection of Technical Papers Book PDF

Author : Anonim
Publisher : Unknown
Page : 394 pages
File Size : 51,5 Mb
Release : 1980
Category : Aerodynamics
ISBN : PSU:000012120895

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A Collection of Technical Papers by Anonim Pdf

Rotary Balances

Marie H. Tuttle
Rotary Balances Book PDF

Author : Marie H. Tuttle
Publisher : Unknown
Page : 36 pages
File Size : 54,8 Mb
Release : 1989
Category : Stability of airplanes
ISBN : UIUC:30112105195538

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Rotary Balances by Marie H. Tuttle Pdf

Measurement of Unsteady Fluid Dynamic Phenomena

Bryan E. Richards
Measurement of Unsteady Fluid Dynamic Phenomena Book PDF

Author : Bryan E. Richards
Publisher : Unknown
Page : 360 pages
File Size : 44,9 Mb
Release : 1977
Category : Fluid dynamic measurements
ISBN : UOM:39076005403907

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Measurement of Unsteady Fluid Dynamic Phenomena by Bryan E. Richards Pdf

AGARD Index of Publications

North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Technical Information Panel
AGARD Index of Publications Book PDF

Author : North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Technical Information Panel
Publisher : Unknown
Page : 206 pages
File Size : 54,5 Mb
Release : 1972
Category : Electronic
ISBN : MINN:31951P00015044S

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AGARD Index of Publications by North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Technical Information Panel Pdf

AGARD Index of Publications

North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development
AGARD Index of Publications Book PDF

Author : North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development
Publisher : Unknown
Page : 526 pages
File Size : 40,9 Mb
Release : 1989
Category : Aeronautics
ISBN : UIUC:30112008967942

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AGARD Index of Publications by North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development Pdf

An Investigation of the Half-model Reflection-plane Technique for Dynamic Stability Testing at Transonic Mach Numbers

T. O. Shadow
An Investigation of the Half model Reflection plane Technique for Dynamic Stability Testing at Transonic Mach Numbers Book PDF

Author : T. O. Shadow
Publisher : Unknown
Page : 96 pages
File Size : 42,6 Mb
Release : 1977
Category : Aerodynamic heating
ISBN : UOM:39015104954014

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An Investigation of the Half-model Reflection-plane Technique for Dynamic Stability Testing at Transonic Mach Numbers by T. O. Shadow Pdf

An experimental investigation was made to determine the feasibility of the half-model reflection-plane technique for measuring dynamic stability derivatives in the transonic speed range. Three model configurations simulating an aircraft, a missile, and a bluff body were investigated both full and half span at Mach numbers from 0.6 to 1.2 and angles of attack from -2 to 90 deg. The half-model reflection-plane technique fully duplicated the full-span results only at subsonic subcritical speeds and angles of attack up to 20 deg. In tests at higher Mach numbers in the transonic range and higher angles of attack up to 90 deg, it was not demonstrated that the half-model technique can provide better than qualitative, order of magnitude results.