Effect of Engine Integration on a 4.6%-Scale Flying-V Subsonic Transport

Empelen, S.A. van; Vos, Roelof

doi:10.2514/6.2021-0939

Cited by 2 publications

(2 citation statements)

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“…The contribution of the engines to the forces and moments is quantified by using a model for the thrust coefficient, identified from the wind tunnel data of Ref. [9] using Ordinary Least Squares. The result is subtracted from the estimated forces and moments before the parameter estimation.…”

Section: G Engine Modelmentioning

confidence: 99%

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Aerodynamic Model Identification of the Flying V from Sub-Scale Flight Test Data

García

Brown

Atherstone

et al. 2022

AIAA SCITECH 2022 Forum

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This paper presents the identification of the aerodynamic model of the "Flying-V", a novel aircraft configuration. The aerodynamic model is estimated using flight test data from a 4.6% sub-scale model. The dataset includes longitudinal and lateral-directional maneuvers performed by both the pilot and the autopilot to excite the aircraft dynamic modes. The so-called Two-Step Method is used to decouple and simplify the aerodynamic identification problem; the state estimation step is performed by an Iterated Extended Kalman Filter, and the parameter-estimation step using ordinary least squares. A stepwise regression technique and previous knowledge from wind-tunnel tests are combined to select the model structure, and the identified model is validated using a third of the gathered data. The estimated models are parsimonious and considered adequate in terms of model fit, with a maximum relative Root Mean Square Error of 10% for the worst validation case. For the considered location of the center of gravity and flight conditions, the estimated aerodynamic derivatives confirm that the aircraft is longitudinally stable, both statically and dynamically; and that it is also laterally and directionally statically stable. The analysis of the dynamic modes of the sub-scale model showed stable short period and roll subsidence modes, a lightly damped Dutch roll mode, and lightly damped/unstable phugoid and spiral modes.

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Section: G Engine Modelmentioning

confidence: 99%

“…The effect of engine integration on the aerodynamic interference was studied experimentally in Ref. [9]. It was shown that the interference effects on lift and pitching moment were of the same order of magnitude as the effect of superpositioning the contributions of the isolated wing and engine.…”

Section: Introductionmentioning

confidence: 99%