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Accession Number:
AD0880949
Title:
The Laminar Boundary Layer on a Rotating Blade of Symmetrical Airfoil Shape
Corporate Author:
NORTH CAROLINA STATE UNIV AT RALEIGH
Report Date:
1970-12-01
Abstract:
A theoretical study has been conducted to determine the effects of rotation, inflow, and forward flight on the development of the laminar boundary layer on a helicopter blade. Particular emphasis was placed on the determination of the separation line. In order to faciliate the computation of the inviscid flow about the blade, an 11.9-thick symmetrical Joukowski airfoil was used. The essential feature of the analysis was the scaling of the chordwise coordinate so that the separation line is invariant with span and time in the transformed coordinate system. The transformed boundary layer equations were expanded in an asymptotic series in span, and the resulting equations were solved. The major effect of rotation is noted as a delay in separation.
Descriptive Note:
Final rept.
Supplementary Note:
DOI: 10.21236/AD0880949
Pages:
0158
Distribution Statement:
Approved for public release; distribution is unlimited.
Contract Number:
DAAJ02-69-C-0086
File Size:
10.64MB
