Application of Circulation Control manoeuvre effectors for three axis control of a tailless flight vehicle C.D. Harley * , P.I.A. Wilde * , W.J. Crowther † The School of Mechanical, Aerospace and Civil Engineering, The University of Manchester, Manchester, M60 1QD,UK The application of Circulation Control manoeuvre effectors to a tailless flight vehicle enables the possibility of providing control of moments about three axes without use of conventional flapped control surfaces. This paper develops a low order design methodology for sizing CC effectors based on an extension to existing data sheet methods for estimating pitch and roll control from conventional flight controls. The method relies on input of experimental data for the 2d change in lift and change in pitching moment with blowing coefficient. There is ample data in the extensive CC literature enabling estimation of lift from CC, however there is little data that enables extraction of the pitching moment change due to CC. A case study is presented in which the provision of three axis control moments using CC is evaluated for a tailless 20Kg class gas turbine powered model aircraft. Wind tunnel experiments are used to demonstrate the validity of the aerodynamic design of the vehicle and the ability to produce control moments from CC sufficient to meet basic trim and ࢾ࡯ ࡹ࢕ ࢾ࡯ ࣆ ⁄ are 20 and 12 respectively. The control gain for ࢾ࡯ ࡰ ࢾ࡯ ࣆ ⁄ for use as part of ‘thrust’ based yaw control scheme from blowing from both upper and lower slots is low sideslip at cruise conditions with 10% mass flow bleed from the e Nomenclature and manoeuvre requirements. The peak values of CC control gains achieved for ࢾ࡯ ࡸ ࢾ࡯ ࣆ ⁄ a (approximately 1), however this is sufficient to trim the case study aircraft at 7 degrees of ngine. ܣ aspect ratio, 2 ݏ ҧ ൗ ൌ   ൗ  ଵ wing lift curve slope,  ܥ ௅  ߙ ൗ rad ଵ  ௧ in lift due deflection of a trailing edge flap,  ܥ ௅  ߜ ௧ ൗ rad ଵ  is representative of the wing, i.e. chord at mid span of plain trailing-edge m ′ i.e. chord at mid span of plain trailing- m ܥ ܥ ௅ ܥ ெ coefficient, ܯ ݍ ൗ ܥ ெ௢ om nt coefficient, (taken about the aerodynamic centre) coefficient,  ݍ ൗ ଶ theoretical gain to chord of basic aerofoil which flap panel chord of extended aerofoil which is representative of the wing, edge flap panel ஽ drag coefficient, ܦ ݍ ൗ lift coefficient, ܮ ݍ ൗ pitching moment zero lift pitching m e ܥ ே yawing moment * PhD student, Student Member AIAA. 1 American Institute of Aeronautics and Astronautics † Senior Lecturer, Member AIAA. 47th AIAA Aerospace Sciences Meeting Including The New Horizons Forum and Aerospace Exposition 5 - 8 January 2009, Orlando, Florida AIAA 2009-146 Copyright © 2009 by Christopher Harley. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission.