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Numerical Stall Behavior Investigation of an Aircraft Equipped with Coanda Flap and Droop Nose Read chapter Read first chapter

2016 | OriginalPaper | Chapter

CFD Study on a Pitching Missile with Respect to Reduce the Phantom Yaw Effect

Authors : Christian Schnepf, Erich Schülein

Published in: New Results in Numerical and Experimental Fluid Mechanics X

Publisher: Springer International Publishing

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Abstract

This numerical study is about the alleviation of the Phantom Yaw Effect on a pitching missile. A pair of slit shaped side jets, so called aerostrakes is used to force a symmetric separation at the shoulder of the missile. The unsteady Reynolds averaged Navier-Stokes equations are solved with a two equation turbulence model for a case with and without aerostrakes. The missile is pitching sinusoidally at a frequency of 5 Hz between \(0^\circ \le \alpha \le 44^\circ \) at Mach 0.8. The results show that the magnitude of the side force, resulting from Phantom Yaw, is reduced by the aerostrakes and the onset angle for the PYE is shifted to higher angle of attack. A reversal of sign of both the side force and yawing moment is also prevented when using the aerostrakes. Furthermore, the influence of the pitching motion on the relevant aerodynamic coefficients is less profound in the case with aerostrakes.

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Metadata
Title
CFD Study on a Pitching Missile with Respect to Reduce the Phantom Yaw Effect
Authors
Christian Schnepf
Erich Schülein
Copyright Year
2016
Book
New Results in Numerical and Experimental Fluid Mechanics X

Print ISBN: 978-3-319-27278-8

Electronic ISBN: 978-3-319-27279-5

Copyright Year: 2016

DOI
https://doi.org/10.1007/978-3-319-27279-5_73

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