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Axisymmetric afterbody experiments for CFD validation

Published online by Cambridge University Press:  04 July 2016

P. Miller ,
J. Agrell ,
J. Olsson  and
K. Sjörs
P. Miller
Affiliation:
Miller and Wilson, Aerodynamics Research, Bath
J. Agrell
Affiliation:
FFA, The Aeronautical Research Institute of Sweden
J. Olsson
Affiliation:
FFA, The Aeronautical Research Institute of Sweden
K. Sjörs
Affiliation:
FFA, The Aeronautical Research Institute of Sweden
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Summary

An experiment is described which was undertaken specifically to provide CFD validation data for the case of transonic flow over nozzle afterbodies. The tests were undertaken with the AGARD standard 10° and 15° axisymmetric boat-tail geometries. Onset Mach numbers in the range 0·80-0·99 and subsonic and under-expanded jet plumes were employed in the tests. Test conditions were selected which provided a range of afterbody flow features from largely attached to shock-induced separated flows. A uniquely detailed set of surface pressure and flowfield data are presented. The flow data were acquired with a two-component laser Doppler anemometer (LDA) and define the mean and fluctuating flow components at about 500 spatial locations for each of these complex transonic flowfields. Additional information was recorded which fully defines the required computational boundary conditions.

Also presented is a detailed study of the necessary attributes of windtunnel CFD validation data. It is demonstrated that relatively high blockage experiments using cost-effective windtunnels can be used to generate CFD validation data if proper account is taken of the model/tunnel interference.

Type
Research Article
Information
The Aeronautical Journal , Volume 98 , Issue 974 , April 1994 , pp. 137 - 146
Copyright
Copyright © Royal Aeronautical Society 1994 

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Footnotes

‡

Now DRA, Bedford

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