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Use of potential flow theory to evaluate subsonic inlet data from a simulator-powered nacelle at cruise conditionsIncompressible potential flow theory corrected for compressibility effects, using the Lieblein-Stockman compressibility correction, was used to predict surface and flow field static pressures for a subsonic inlet at cruise conditions. The calculated internal and external surface static pressures were in good agreement with data at most conditions. The analysis was used to determine the capture stream-tube location and static-pressure distribution. Additive drag coefficients obtained from these results were consistently higher than those obtained using one-dimensional compressible flow theory. Increasing the distance between the inlet and boattail increased the cowl drag force. The effect of the boundary layer on internal and external surface static-pressure distributions was small at the design cruise condition. The analytical results may be used as an aid to data reduction and for predicting inlet mass flow, stagnation point location, and inlet additive drag.
Document ID
19750005121
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Technical Note (TN)
Authors
Bober, L. J.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
December 1, 1974
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
E-7472
NASA-TN-D-7850
Accession Number
75N13193
Funding Number(s)
PROJECT: RTOP 501-24
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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