Obliczenia flatteru prostokątnego płata ze sterem za pomocą MSC Nastran, ZONA ZAERO i ANSYS Fluent - porównanie z wynikami w tunelu aerodynamicznym

Chajec, Wojciech; Dziubiński, Adam

doi:10.5604/05096669.1205243

Cited by 2 publications

(1 citation statement)

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“…An introduction of aerodynamic correction factors is possible in the DLM (Rodden and Johnson, 1994) to make the aerodynamic forces and moments closer to the measured ones. The control surface hinge moments correction can also be received by varying the border between the wing/fin/stabilizer and the control surface in the DLM model (Chajec and Dziubi nski, 2016a). In the final paper, the flutter computation results obtained by means of both MSC NASTRAN and ZONA ZAERO software were compared with wind tunnel flutter test results.…”

Section: Generalized Masses Determinationmentioning

confidence: 99%

Comparison of flutter calculation methods based on ground vibration test result

Chajec

2019

AEAT

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PurposeA low-cost but credible method of low-subsonic flutter analysis based on ground vibration test (GVT) results is presented. The purpose of this paper is a comparison of two methods of immediate flutter problem solution: JG2 – low cost software based on the strip theory in aerodynamics (STA) and V-g method of the flutter problem solution and ZAERO I commercial software with doublet lattice method (DLM) aerodynamic model and G method of the flutter problem solution. In both cases, the same sets of measured normal modes are used. Design/methodology/approachBefore flutter computation, resonant modes are supplied by some non-measurable but existing modes and processed using the author’s own procedure. For flutter computation, the modes are normalized using the aircraft mass model. The measured mode orthogonalization is possible. The flutter calculation made by means of both methods are performed for the MP-02 Czajka UL aircraft and the Virus SW 121 aircraft of LSA category. FindingsIn most cases, both compared flutter computation results are similar, especially in the case of high aspect wing flutter. The Czajka T-tail flutter analysis using JG2 software is more conservative than the one made by ZAERO, especially in the case of rudder flutter. The differences can be reduced if the proposed rudder effectiveness coefficients are introduced. Practical implicationsThe low-cost methods are attractive for flutter analysis of UL and light aircraft. The paper presents the scope of the low-cost JG2 method and its limitations. Originality/valueIn comparison with other works, the measured generalized masses are not used. Additionally, the rudder effectiveness reduction was implemented into the STA. However, Niedbal (1997) introduced corrections of control surface hinge moments, but the present work contains results in comparison with the outcome obtained by means of the more credible software.

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Section: Generalized Masses Determinationmentioning

confidence: 99%