NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login

The auto‑search feature has been disabled based on user feedback. Enter a search term/phrase and click “Search” to begin.

Back to Results
A method of distortion pattern synthesis for high response data screeningAn empirically derived method of estimating maximum levels of instantaneous inlet total pressure distortion from steady state measurements is presented. The estimation procedure uses steady state total pressure and root mean square turbulent pressure data measurements to synthesize instantaneous distortion patterns. The synthesis method is tailored to intensify distortion patterns in a manner consistent with the characteristics of the particular index to be used in evaluating inlet/engine compatability. The maximum expected value of distortion, a statistically determined function of the length of time of inlet operation, is used to constrain the amount of pattern intensification. Comparison with an independent set of data is presented for verification of the synthesis method.
Document ID
19760055252
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
King, R. W. (United Technologies Corp. Pratt and Whitney Aircraft Div., East Hartford, Conn., United States)
Neumann, H. E. (NASA Lewis Research Center Cleveland, Ohio, United States)
Date Acquired
August 8, 2013
Publication Date
July 1, 1976
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 76-704
Report Number: AIAA PAPER 76-704
Meeting Information
Meeting: Propulsion Conference
Location: Palo Alto, CA
Start Date: July 26, 1976
End Date: July 29, 1976
Sponsors: American Institute of Aeronautics and Astronautics and Society of Automotive Engineers
Accession Number
76A38218
Distribution Limits
Public
Copyright
Other

Available Downloads

There are no available downloads for this record.

Related Records

There are no records associated with this record.
No Preview Available