Dataset of numerical simulations for aeroelastic control of an aero engine compressor cascade using plasma actuators

The dataset presented here regard the analysis reported in the research article entitled “Comparison of different plasma actuation strategies for aeroelastic control on a linear compressor cascade” De Giorgi et al. (2021) [1]. These data are related to the Computational Fluid Dynamics (CFD) assessment of different plasma actuation strategies for the aeroelastic control of an aero engine compressor cascade in subsonic flow conditions. The authors evaluated the accuracy of numerical computations using experimental results. Here, both experimental and raw data of the CFD simulations are presented.


Specifications
Aerospace Engineering, Mechanical Engineering Specific subject area Flow control techniques, Active Flow Control, Turbomachinery, Aeroelasticity, Aerodynamics Type of data Text file (Excels Data) How data were acquired Ansys FLUENT ® R1 Data format Raw, Analyzed Parameters for data collection Presented data regard a NACA65 compressor cascade in steady and unsteady flow. As performed in Motta et al. [2] , inlet flow conditions are: velocity of U ∞ = 34.36 m/s (Re ≈350,0 0 0) and U ∞ = 19.65 m/s (Re ≈20 0,0 0 0), pressure equal to 101325 Pa, temperature equal to 288.15 K and density equal to ρ∞ = 1.225 kg/m 3 . Geometric model and boundary conditions employed for the numerical simulations are those real of aircraft engines compressors. Two AC voltage Dielectric Barrier Discharge (AC-DBD) plasma actuators are placed at the trailing edge of the central blades. The influence of AC-DBD plasma actuators on the aeroelastic control has been analysed through a proper phasing of the actuation switching law. Description of data collection Different 2D geometric domains of seven NACA65 blades were realized and imported into Ansys FLUENT ® R1. Realistic operating conditions have been set and 2D Reynolds-averaged Navier-Stokes (RANS) equations have been resolved with the hypothesis of incompressible flow. Several steady runs have been executed in order to perform grid independent studies. Once the reference grid has been obtained, transient simulations of the pitching blades with and without plasma actuators have been carried out. The cosinusoidal actuation switching law for the suction and pressure side used for the assessment is as follows: Data source location University of Salento, Lecce, Italy Data accessibility Data available with the article Related research article "Comparison of different plasma actuation strategies for aeroelastic control on a linear compressor cascade" [1] Value of the Data • The data are important for the since they allow to evaluate the effect of the active flow control technique based on AC-DBD Plasma Actuators in order to achieve aeroelastic control on a linear compressor cascade in unsteady flow conditions. • The data can be useful for engineers and researchers which work in the turbomachinery research area with particular focus on active flow control.

Data Description
The CFD dataset of a linear compressor cascade ( Fig. 1 ) presented in the article provides the steady pressure distribution (C p ) ( Fig. 2 ), lift coefficient (C l ) and moment coefficient (C m,c/2 ) time history curves ( Fig. 3 ) and standard deviation of the 4th blade in both clean and actuated  configuration ( Fig. 4 ). Steady simulation result of the pressure coefficient is compared with the experimental data of Ref. [2] , also provided in this article. As regards the C l and C m,c/2 aerodynamic coefficients, temporal evolution of the raw signals of these coefficients in both clean and actuated configuration are reported. Furthermore, standard deviation values of these coefficients in both clean and actuated configuration are also included in this article.  to 101325 Pa, temperature equal to 288.15 K and density equal to ρ ∞ = 1.225 kg/m 3 . Numerical computations have been carried out using the commercial solver Ansys FLUENT ® R1. The k-ω turbulence model has been employed as closure for the Reynolds-averaged Navier-Stokes (RANS) equations and convergence criteria have been set to 6.35 ·10 −5 . Load response, evaluated in terms of lift coefficient (C l ) and moment coefficient (C m,c/2 ) have been analysed. Pitching motion of the blades, positive clockwise, has been realized by loading a UDF macro in the solver containing the kinematic formulation of the oscillation:

Subsonic
(1) where α(t) is the blade angle of attack, α 0 is the average angle of attack, ω= 2 π f is the frequency, n is the nth blade (starting from the top of the cascade) and IBPA is the inter-blade phase angle. Validation of the reference grid has been carried out by comparing experimental results of Ref. [2] , both in steady and unsteady flow. Dielectric barrier discharge (DBD) driven by an alternating current (AC) plasma actuator have been modelled based on Shyy's approximation [3] . The cosinusoidal actuation law employed to control the aeroelastic response of the cascade is defined as follows: where ϕ indicates the force phase (in degrees) used to shift the electrical signal of the plasma actuators.
The standard deviation values of the aerodynamic coefficients signal is calculated as follows: (3)

Ethics Statement
The authors followed generally expected standards of ethical behavior in scientific publishing throughout article construction.