Computation and evaluation of dynamic derivatives using CFD

This paper focuses on the computation of dynamic derivatives for full aircraft configurations. The flow is modelled using the Euler and RANS equations and an unsteady time-domain solver is used for the computation of aerodynamic loads for forced periodic motions. The study investigates the variation of damping values through the transonic regime and for several permutations of motion parameters for the Standard Dynamics Model geometry. A benchmark against experimental data is presented for the Transonic CRuiser wind tunnel geometry. For the SDM, strake vortices and their breakdown are observed when increasing the mean angle of attack during the applied pitch sinusoidal motion. A good agreement is obtained with available experimental data. For the TCR, a validation of longitudinal aerodynamic characteristics is first considered. Numerical experiments for the estimation of damping derivatives and for large amplitude forced oscillations in pitch axis are compared to wind tunnel data. Simulations are in agreement with experimental data up to high angles of attack.

[1]  G. H. Bryan,et al.  Stability in Aviation , 1911, Aeronautical journal (London, England : 1897).

[2]  M. E. Beyers,et al.  Subsonic roll oscillation experiments on the Standard Dynamics Model , 1983 .

[3]  K. J. Orlik-Rückemann,et al.  Dynamic stability testing of aircraft—needs versus capabilities , 1975 .

[4]  D. Wilcox.  Reassessment of the scale-determining equation for advanced turbulence models , 1988 .

[5]  P. Spalart.  A One-Equation Turbulence Model for Aerodynamic Flows , 1992 .

[6]  Henry Dol,et al.  Leading edge vortex flow computations and comparison with DNW-HST wind tunnel data , 2001 .

[7]  Mark S. Smith,et al.  Analysis of Wind Tunnel Oscillatory Data of the X-31A Aircraft , 1999 .

[8]  Douglas I. Greenwell,et al.  Frequency Effects on Dynamic Stability Derivatives Obtained from Small-Amplitude Oscillatory Testing , 1998 .

[9]  B. V. Leer,et al.  Towards the ultimate conservative difference scheme. II. Monotonicity and conservation combined in a second-order scheme , 1974 .

[10]  Mikhail Goman,et al.  State-Space Representation of Aerodynamic Characteristics of an Aircraft at High Angles of Attack , 1994 .

[11]  O. J. Boelens,et al.  Comparison of Measured and Block Structured Simulation Results for the F-16XL Aircraft , 2009 .

[12]  Stanley Osher,et al.  Upwind schemes and boundary conditions with applications to Euler equations in general geometries , 1983 .

[13]  Giorgio Guglieri,et al.  Determination Of Dynamic Stability Derivatives Using Forced Oscillation , 2002 .

[14]  Peder Eliasson,et al.  Virtual Aircraft Design of TransCruiser - Computing Break Points in Pitch Moment Curve , 2010 .

[15]  Alan R. Jones,et al.  Fast Fourier Transform , 1970, SIGP.

[16]  L. Rabiner,et al.  The chirp z-transform algorithm and its application , 1969 .

[17]  L. Filon.  III.—On a Quadrature Formula for Trigonometric Integrals. , 1930 .

[18]  L. B. Schiff,et al.  Aerodynamic characteristics of the standard dynamics model in coning motion at Mach 0.6 , 1985 .

[19]  B. Richards,et al.  Elements of computational fluid dynamics on block structured grids using implicit solvers , 2000 .