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Record 11 of 3536
Estimating maximum instantaneous distortion from inlet total pressure rms and PSD measurements. [Root Mean Square and Power Spectral Density methods]
Author and Affiliation:
Melick, H. C., Jr.(LTV Aerospace Corp., Dallas, TX, United States)
Ybarra, A. H.(LTV Aerospace Corp., Vought Systems Div., Dallas, Tex., United States)
Bencze, D. P.(NASA Ames Research Center, Moffett Field, Calif., United States)
Abstract: An inexpensive method is developed to determine the extreme values of instantaneous inlet distortion. This method also provides insight into the basic mechanics of unsteady inlet flow and the associated engine reaction. The analysis is based on fundamental fluid dynamics and statistical methods to provide an understanding of the turbulent inlet flow and quantitatively relate the rms level and power spectral density (PSD) function of the measured time variant total pressure fluctuations to the strength and size of the low pressure regions. The most probable extreme value of the instantaneous distortion is then synthesized from this information in conjunction with the steady state distortion. Results of the analysis show the extreme values to be dependent upon the steady state distortion, the measured turbulence rms level and PSD function, the time on point, and the engine response characteristics. Analytical projections of instantaneous distortion are presented and compared with data obtained by a conventional, highly time correlated, 40 probe instantaneous pressure measurement system.
Publication Date: Sep 01, 1975
Document ID:
19760027295
(Acquired Dec 01, 1995)
Accession Number: 76A10261
Subject Category: AERODYNAMICS
Report/Patent Number: AIAA PAPER 75-1213
Document Type: Conference Paper
Publisher Information: United States
Meeting Information: 11th Propulsion Conference; Sept. 29-Oct. 1, 1975; Anaheim, CA
Meeting Sponsor: American Institute of Aeronautics and Astronautics and Society of Automotive Engineers
Contract/Grant/Task Num: NAS2-6901
Financial Sponsor: NASA; United States
Organization Source: LTV Aerospace Corp.; Dallas, TX, United States
NASA Ames Research Center; Moffett Field, CA, United States
Description: 14p; In English
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: Copyright
NASA Terms: AERODYNAMIC STALLING; ENGINE INLETS; FLOW DISTORTION; INLET PRESSURE; RANDOM LOADS; TURBULENCE EFFECTS; CHANNEL FLOW; EXTREMUM VALUES; INLET FLOW; LOW PRESSURE; MATHEMATICAL MODELS; POWER SPECTRA; PREDICTION ANALYSIS TECHNIQUES; TURBOCOMPRESSORS; TURBULENT FLOW; VORTICES
Imprint And Other Notes: American Institute of Aeronautics and Astronautics and Society of Automotive Engineers, Propulsion Conference, 11th, Anaheim, Calif., Sept. 29-Oct. 1, 1975, AIAA 14 p.
Availability Source: Other Sources
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