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Author: A. L. Laganelli Publisher: ISBN: Category : Ablative materials Languages : en Pages : 146
Book Description
An experimental program was conducted in the AFWAL Mach 6 and AEDC shock Tube facilities in which acoustic fluctuating pressure data were acquired on flat plate TWCP specimens featuring smooth and rough surfaces. The TWCP specimens were instrumented with five Gulton microphones. The microphones placed in the model consisted of flush, ported, and backface (blind hole) locations. Several l/d ported orifices were examined as well as depths from the boundary layer surface for the backface gages. The AEDC tests were structured to examine optimum ported orifices prior to the AFWAL Mach 6 tests. The TWCP specimens were exposed to turbulent boundary layer conditions at tunnel stagnation pressures of 700, 1400, and 2100 psi with a total temperature of 1100 deg. R, respectively. A correlation was developed for the ported hole sensors that can be related to the flush mounted sensors. Characterizing the backface (blind hole) gages with surface mounted sensors will require further data interpretation due to vibration. In general, rough walls augmented the acoustic energy levels as expected. A biased rough pattern (20 deg, angled to flow) indicated that acoustic measurements could be used as a diagnostic technique to determine the surface characteristics of TWCP ablation patterns.
Author: A. L. Laganelli Publisher: ISBN: Category : Ablative materials Languages : en Pages : 146
Book Description
An experimental program was conducted in the AFWAL Mach 6 and AEDC shock Tube facilities in which acoustic fluctuating pressure data were acquired on flat plate TWCP specimens featuring smooth and rough surfaces. The TWCP specimens were instrumented with five Gulton microphones. The microphones placed in the model consisted of flush, ported, and backface (blind hole) locations. Several l/d ported orifices were examined as well as depths from the boundary layer surface for the backface gages. The AEDC tests were structured to examine optimum ported orifices prior to the AFWAL Mach 6 tests. The TWCP specimens were exposed to turbulent boundary layer conditions at tunnel stagnation pressures of 700, 1400, and 2100 psi with a total temperature of 1100 deg. R, respectively. A correlation was developed for the ported hole sensors that can be related to the flush mounted sensors. Characterizing the backface (blind hole) gages with surface mounted sensors will require further data interpretation due to vibration. In general, rough walls augmented the acoustic energy levels as expected. A biased rough pattern (20 deg, angled to flow) indicated that acoustic measurements could be used as a diagnostic technique to determine the surface characteristics of TWCP ablation patterns.
Author: Publisher: ISBN: Category : Aeronautics Languages : en Pages : 666
Book Description
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.
Author: Anthony L. Laganelli Publisher: ISBN: Category : Ballistic missiles Languages : en Pages : 184
Book Description
An experimental program was conducted at the AEDC von Karman facility, Tunnels A and B, in which acoustic pressure fluctuation data were acquired on a 7 degree half-cone-angle model featuring a control surface. The objective was to define the aeroacoustic environment applicable to re-entry vibration response analysis for both ballistic and maneuvering vehicles. Wind tunnel measurements were obtained at Mach 4 and 8 for several values of freestream Reynolds number and model angle of attack. Stationary zones of laminar, transitional, and turbulent flow over the model were achieved. Acoustic data were reduced to rms fluctuating pressure, and power and cross-power spectral densities. Results were normalized using local boundary layer parameters for comparison with previous high speed measurements. The present study re-examined the aeroacoustic environment prediction capability relative to compressible flow conditions. Moreover, boundary layer characteristic lengths and velocities were reviewed in order to develop normalization procedures required for development of appropriate aeroacoustic scaling laws. It was determined that fluctuating pressure characteristics described by incompressible theory as well as empirical correlations could be modified to a compressible state through a transformation function. In this manner, compressible data were transformed to the incompressible plane where direct use of more tractable prediction techniques are available for engineering design analyses.
Author: T. J. Mueller Publisher: Springer Science & Business Media ISBN: 9783540417576 Category : Science Languages : en Pages : 344
Book Description
The book describes recent developments in aeroacoustic measurements in wind tunnels and the interpretation of the resulting data. The reader will find the latest measurement techniques described along with examples of the results.
Author: Publisher: ISBN: Category : Research Languages : en Pages : 1008
Book Description
Sections 1-2. Keyword Index.--Section 3. Personal author index.--Section 4. Corporate author index.-- Section 5. Contract/grant number index, NTIS order/report number index 1-E.--Section 6. NTIS order/report number index F-Z.
Author: A. L. Laganelli
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Author: Anthony L. Laganelli
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