Mathematical Modelling of Aircraft Unsteady Aerodynamics at High Incidence with Account of Wing-Tail Interaction

AIAA Atmospheric Flight Mechanics Conference and Exhibit

2008

“…Data compatibility was checked by comparing measured and computed C N and C m using Eqs. (1) to (4). The results are presented in Fig.…”

Section: Analysis Of Steady Datamentioning

confidence: 70%

“…An extension to a nonlinear unsteady aerodynamic formulation and parameter estimation from wind tunnel data appeared in Ref. 4. In this analysis both steady and oscillatory data were used.…”

mentioning

confidence: 99%

Transport Aircraft System Identification from Wind Tunnel Data

AIAA Atmospheric Flight Mechanics Conference and Exhibit

2008

“…It is represented by Eqs. (8)(9)(10)(11)(12)(13)(14)(15). The unknown parameters in these equations are the two damping derivatives and the time constant, ε τ , characterizing time dependency of downwash at the tail.…”

Section: Bwt Model Identificationmentioning

confidence: 99%

“…8 and aerodynamic model equations based on those of Ref. 7 and 8 for model identification, i.e., model structure determination and parameter estimation.…”

Section: Introductionmentioning

confidence: 99%

Estimation of Longitudinal Unsteady Aerodynamics of a Wing-Tail Combination from Wind Tunnel Data

AIAA Atmospheric Flight Mechanics Conference and Exhibit

2006

This paper presents an initial step toward model identification from wind tunnel data for an airliner configuration. Two approaches to modeling a transport configuration are considered and applied to both steady and large-amplitude forced-oscillation wind tunnel data taken over a wide range of angles of attack. Only limited conclusions could be drawn from this initial data set. Although model estimated time histories of normal force and pitching moment agree reasonably well with the corresponding measured values, model damping parameters did not, for some cases, have values consistent with small amplitude oscillatory data. In addition, large parameter standard errors implied poor information content for model structure determination and parameter estimation. Further investigation of the modeling problem for more general aerodynamic models is recommended with close attention to experiment design for obtaining parameters with high accuracy.

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“…The measured data were obtained from static and dynamic testing of an airliner in the Central AeroHydrodynamic Institute (TsAGI) low subsonic wind tunnel 11 . The steady data included the normal force and the pitching moment of four different configurations, i.e., body alone (B), body-tail (BT), body-wing (BW) and the complete model (BWT).…”

Section: Measured Datamentioning

confidence: 99%

On Problems Associated with Modeling Wing-Tail Configurations from Wind Tunnel Data

AIAA Atmospheric Flight Mechanics Conference and Exhibit

2007