Sting Interference Effects On A 7 Deg Cone As Determined By Measurements Of Dynamic Stability Derivatives And Base Pressure For Mach Numbers 0 2 Through 1 3
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Sting Interference Effects As Determined By Measurements Of Dynamic Stability Derivatives Surface Pressure And Base Pressure For Mach Numbers 2 Through 8
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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.
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
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Author : Frederick B. Cyran
language : en
Publisher:
Release Date : 1981
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 written by Frederick B. Cyran and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1981 with Boundary layer categories.
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.
An Investigation Of Sting Interference Effects On An Oscillating Cone In Transonic Flow
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Author : Frederick B. Cyran
language : en
Publisher:
Release Date : 1981
An Investigation Of Sting Interference Effects On An Oscillating Cone In Transonic Flow written by Frederick B. Cyran and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1981 with Aerodynamics, Transonic categories.
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
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Author :
language : en
Publisher:
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.
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 : 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.
Government Reports Annual Index
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Author :
language : en
Publisher:
Release Date : 199?
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 199? with categories.
Government Reports Announcements Index
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Author :
language : en
Publisher:
Release Date : 1981
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 1981 with Science categories.
Technical Abstract Bulletin
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Author :
language : en
Publisher:
Release Date : 1968
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 1968 with Science categories.
Sting Interference Effects On A 7 Deg Cone As Determined By Measurements Of Dynamic Stability Derivatives And Base Pressure For Mach Numbers 0 2 Through 1 3
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Author : F. B. Cyran
language : en
Publisher:
Release Date : 1979
Sting Interference Effects On A 7 Deg Cone As Determined By Measurements Of Dynamic Stability Derivatives And Base Pressure For Mach Numbers 0 2 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 1979 with categories.
The effects of sting support interference were investigated on the measurements of pitch damping, yaw damping, pitching moment slope, pitching moment and base pressure. The model was a 15 percent spherically blunt 7 deg cone. The forced oscillation technique was used to obtained data at Mach numbers 0.2 to 1.3 and Reynolds numbers, based on model based diameter, of 0.2 million to 3.6 million. The amplitude of oscillation was + or - 1 deg, and the reduced frequency parameters ranged from 0.006 to 0.049. The test was conducted at two oscillation frequencies, nominally 3.1 and 5.6 Hz. Pitch damping data were obtained at angles of attack of 0 to 28 deg, and yaw damping data were obtained at angles of attack of 0 to 20 deg. The effective sting length was varied from 1 to 3.4 model diameters. The interference effects of two types of model wake splitter plates were also investigated. The data obtained from this test at the transonic test conditions agreed with the results extrapolated from previous tests at AEDC at supersonic-hypersonic test conditions. (Author).
Nasa Sp
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Author :
language : en
Publisher:
Release Date : 1978
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 1978 with Aeronautics categories.