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Calculation of three-dimensional unsteady transonic flows past helicopter bladesA finite difference code for predicting the high speed flow over the advancing helicopter rotor is presented. The code solves the low frequency, transonic small disturbance equation and is suitable for modeling the effects of advancing blade unsteadiness on blades of nearly arbitrary planform. The method employs a quasi-conservative mixed differencing scheme and solves the resulting difference equations by an alternating direction scheme. Computed results showed good agreement with experimental blade pressure data and illustrate some of the effects of varying the rotor planform. The flow unsteadiness is shown to be an indispensible part of a transonic solution. Close to the tip at high advance ratio, cross flow effects can significantly affect the solution.
Document ID
19800024848
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Chattot, J. J. (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
September 4, 2013
Publication Date
October 1, 1980
Subject Category
Aerodynamics
Report/Patent Number
A-8024
NASA-TP-1721
Accession Number
80N33356
Funding Number(s)
PROJECT: RTOP 505-42-21
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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