Reduced-Order Dynamic Stall Modeling with Swept Flow Effects Using a Surrogate-Based Recurrence Framework

Glaz, Bryan; Friedmann, Peretz P.; Liu, Li; Cajigas, Juan; Bain, Jeremy; Sankar, Lakshmi N.

doi:10.2514/1.j051817

Cited by 20 publications

(7 citation statements)

References 22 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Using a CFD code removes the ad hoc assumptions made on separation and reattachment in the semiempirical models, and it is also capable of replicating 3D effects (Refs. [53][54][55]. However, generation of the CFD database for a specific airfoil/blade configuration requires a substantial investment of computer time and effort.…”

Section: G(s) = Q(s)h(s)mentioning

confidence: 99%

On-Blade Control of Rotor Vibration, Noise, and Performance: Just Around the Corner? The 33rd Alexander Nikolsky Honorary Lecture

Friedmann¹

2014

j am helicopter soc

Self Cite

View full text Add to dashboard Cite

A concise review of the active control approaches for vibration reduction in rotorcraft is presented. Next, the evolution and status of higher harmonic control and pitch link actuated individual blade control is presented since these serve as the foundations of on blade control. Despite the success of these approaches, demonstrated by both full-scale wind tunnel and flight tests, higher harmonic control and pitch link actuated individual blade control have not managed to earn their way onto a production helicopter. An alternative, on blade control, is defined as a special implementation of individual blade control, where the control surfaces are located on the rotating blade and each blade has its own controller. A concise description of four on blade devices: (1) the actively controlled flap, (2) the active twist rotor, (3) the active tip rotor, and the (4) deployable Gurney flap, or microflap, is presented. An outline of an aeroelastic response modeling capability used to simulate active vibration and noise reduction using flaps or microflaps is presented. The simulation is a thread that links the various parts of the paper. Next, selected results from simulations and scale wind tunnel model tests on active flaps are used to provide insight on the operational and modeling aspects of these systems. Full-scale wind tunnel and flight tests are presented as culmination of the research effort invested in active flap rotors. Then, the evolution and application of the active twist rotor, and deployable Gurney flaps, or microflaps, is presented. The paper concludes with lessons learned and speculation about the potential implementation of on blade control on production rotorcraft.

show abstract

Section: G(s) = Q(s)h(s)mentioning

confidence: 99%

On-Blade Control of Rotor Vibration, Noise, and Performance: Just Around the Corner? The 33rd Alexander Nikolsky Honorary Lecture

Friedmann¹

2014

j am helicopter soc

Self Cite

View full text Add to dashboard Cite

show abstract

“…Glaz and co-workers used a surrogate-based recurrence framework ROM to model the unsteady aerodynamics on a 2-D rotating airfoil 5 as well as the dynamic stall effects of a helicopter rotor blade. 6,7 Crowell and McNamara 8 combined steady CFD modeling with an unsteady piston theory correction term in modeling unsteady hypersonic aerodynamics. Other efforts for parameter-independent ROMs have focused on the analysis of flight test data.…”

Section: Introductionmentioning

confidence: 99%

Toward an Unsteady Aerodynamic ROM for Multiple Mach Regimes

Skujins

Cesnik²

2012

53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference

9
0
4
0

View full text Add to dashboard Cite

The accurate prediction of unsteady aerodynamic loads is of utmost importance in an aeroelastic simulation framework, which often times will be used to simulate a vehicle passing through multiple Mach regimes on a single flight path. In terms of computational efficiency, it is beneficial for an unsteady aerodynamic model to have a single mathematical form for the aerodynamic loads through the different Mach regimes for an entire simulation. An unsteady aerodynamic reduced-order modeling methodology based on linear convolution combined with a nonlinear correction factor is developed to fulfill this need. Though each Mach regime presents unique modeling challenges, the transonic regime is particularly challenging in this regard due to moving shocks and other nonlinear flow field effects. The purpose of this paper is to characterize both the error of the reduced-order model within the transonic regime as well the applicability of a simplified calculation procedure for the nonlinear correction which can replace, at times, full CFD simulations within the modeling framework. The reduced-order model results show generally good agreement with computational simulations of the AGARD 445.6 wing undergoing oscillation of multiple elastic modes. Also, at higher oscillation frequencies, a distinct phase shift which develops between the model and full-order simulation results has been quantified. Finally, one factor which appears to adversely affect the model's accuracy is the increasing memory length of the system being modeled.

show abstract

“…Furthermore, dynamic models based on this technique require a large matrix of high-fidelity simulations or experimental tests to ensure that the potential behavior is captured (Ref. 12), precluding the use of the model to minimize overall certification costs.…”

Section: Introductionmentioning
confidence: 99%

A Physics-Based, Reduced-Order Aerodynamics Model for Bluff Bodies in Unsteady, Arbitrary Motion
Prosser¹,
Smith²
2015
J Am Helicopter Soc
6
0
3
0
View full text Add to dashboard Cite

A novel reduced-order model for the simulation of bluff bodies in unsteady, arbitrary motion has been developed. The model is physics-based, meaning that it is derived from known fundamental aerodynamic phenomena of bluff bodies instead of response fitting of experimental data. This physics-based approach is essential to ensure that the model is applicable to new, untested configurations. We describe the development of a physics-based model, including detailed explanations of the fundamental aerodynamic phenomena and how they are modeled in simulation. The reduced-order model is evaluated by application to rotorcraft-tethered loads and validated against much more expensive high-fidelity computational fluid dynamics simulations and flight tests. Excellent correlation in the predictions of aerodynamic forces and moments, as well as the dynamic response, is observed, while the computational cost has been reduced by several orders of magnitude relative to high-fidelity computational-fluid-dynamics-based simulations. Additionally, the important role that unsteady aerodynamics play in bluff body dynamics and instability is demonstrated.

show abstract

Reduced-Order Dynamic Stall Modeling with Swept Flow Effects Using a Surrogate-Based Recurrence Framework

Cited by 20 publications

References 22 publications

On-Blade Control of Rotor Vibration, Noise, and Performance: Just Around the Corner? The 33rd Alexander Nikolsky Honorary Lecture

On-Blade Control of Rotor Vibration, Noise, and Performance: Just Around the Corner? The 33rd Alexander Nikolsky Honorary Lecture

Toward an Unsteady Aerodynamic ROM for Multiple Mach Regimes

A Physics-Based, Reduced-Order Aerodynamics Model for Bluff Bodies in Unsteady, Arbitrary Motion

Contact Info

Product

Resources

About