Abstract:
An adequate modelling of nonlinear and unsteady aerodynamics at high incidence flight
is important for design of future agile and stealth fighters as well as for improved prediction
of high angle of attack dynamics of normal aircraft configurations.
The limitations for conventional aerodynamic model based on aerodynamic derivatives
concept are analyzed considering the longitudinal motion of a hypothetical aircraft with
the 65 degree delta wing and thrust vectoring control.
The dynamic unsteady aerodynamic model approximating the vortical and separated
flow time lag effects is considered along with the conventional aerodynamic model and
their impact on aircraft dynamics and control law design is discussed.
Description:
An invited paper with the results of collaboration between TsAGI, Russia and DMU, UK, funded by DERA/QinetiQ, Bedford UK. The phenomenological approach formulated to nonlinear unsteady aerodynamics modelling is adopted in DLR/Germany (R.V. Jategaonkar jategaonkar@dlr.de), ADA/India (Program Director T. G. Pai tgpai@iitk.ac.in ), presented in “Aircraft System Identification: Theory and Practice” by V.Klein and E.A.Morelli, AIAA Education Series, 2006, pp.484 (see p.59 and 72). The experimental technology for real-time unsteady loads measurements using hot-film sensors has been “...inspired by Goman and Khrabrov’s work…” (see NASA/TM-2004-212854, pp. 3-4, http://www.nasa.gov/centers/dryden/pdf/88785main_H-2568.pdf).
