Progress Toward Generation of a Navier-Stokes Database for a Harrier in Ground Effect

Chaderjian, Neal M.; Ahmad, Jasim; Pandya, Shishir A.; Murman, Scott; Kwak, Dochan

doi:10.2514/6.2002-5966

Cited by 25 publications

(10 citation statements)

References 14 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Although limited by available computing power, these calculations showed how the collision of the turbulent wall jets could create a highly unsteady fountain that was in general agreement with experimental studies. More recently, computations by Chaderjian et al (4) and Pandya et al (5) showed how an unsteady RANS method could predict the large scale unsteadiness in the ground vortex, but this type of method will not improve the prediction of the near field (particularly the impingement and the fountain flow). Page et al (15) used a structured finite volume, pressure-based LES technique to compute two simplified twin impinging jet in cross-flow problems.…”

Section: Introductionmentioning

confidence: 99%

“…Solutions using the Reynolds-averaged Navier-Stokes (RANS) equations with a turbulence model can provide reasonable predictions of the large ground vortex and turbulent mean flow (3,4,5) , but are unable to provide information on important phenomena such as the unsteady fountain and instantaneous flow distortion and swirl in the intake. The ability to predict both the mean flow and unsteady excursions is important for the design and development of future aircraft.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Large-eddy simulation of twin impinging jets in cross-flow

Page

McGuirk

2007

Aeronaut. j.

View full text Add to dashboard Cite

The flow-field beneath a jet-borne vertical landing aircraft is highly complex and unsteady. large-eddy simulation is a suitable tool to predict both the mean flow and unsteady fluctuations. This work aims to evaluate the suitability of LES by applying it to two multiple jet impingement problems: the first is a simple twin impinging jet in cross-flow, while the second includes a circular intake. The numerical method uses a compressible solver on a mixed element unstructured mesh. The smoothing terms in the spatial flux are kept small by the use of a monitor function sensitive to vorticity and divergence. The WALE subgrid scale model is utilised. The simpler jet impingement case shows good agreement with experiment for mean velocity and normal stresses. Analysis of time histories in the jet shear layer and near impingement gives a dominant frequency at a Strouhal number of 0·1, somewhat lower than normally observed in free jets. The jet impingement case with an intake also gives good agreement with experimental velocity measurements, although the expansion of the grid ahead of the jets does reduce the accuracy in this region. Turbulent eddies are observed entering the intake with significant swirl. This is in qualitative agreement with experimental visualisation. The results show that LES could be a suitable tool when applied to multiple jet impingement with realistic aircraft geometry.

show abstract

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Large-eddy simulation of twin impinging jets in cross-flow

Page

McGuirk

2007

Aeronaut. j.

View full text Add to dashboard Cite

show abstract

“…Researchers at NASA Ames, for example, have attempted to perform a "brute force" approach to filling a stability and control database for vehicle design. [7][8][9] They found that a reasonable database for static stability and control derivatives would include on the order of 30 different angles-of-attack, 20 different Mach numbers, and 5 different side-slip angles, each for a number of different geometry configurations or control surface deflections. 7 They envisioned that a few hundred solutions can be obtained automatically and the remainder of the parameter space is filled using an interpolation procedure or neural networks.…”

Section: Nomenclaturementioning

confidence: 99%

Improved Methodologies for Maneuver Design of Aircraft Stability and Control Simulations

Jirasek

Jeans

Martenson

et al. 2010

48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

View full text Add to dashboard Cite

With many modern fighter aircraft experiencing unpredicted flight dynamics during flight tests, recent research has focused on developing methodologies for incorporating computational fluid dynamics into the aircraft development process. The goal of this ap proach is to identify configurations susceptible to stability and control issues early in the design process. Previous research has primarily focused on full aircraft configurations, how ever, to increase the rate of development the current study focused on a two-dimensional NACA0012 airfoil. The two-dimensional NACA0012 airfoil has the advantage of reducing the computational cost by orders of magnitude compared to full scale aircraft simulations, while still providing complicated aerodynamics at high angles of attack. Computationally predicted lift coefficients from a number of newly developed training maneuvers were used to generate reduced order aerodynamic loads models. For evaluation, these models were compared to generated static and dynamic validation data. Methods of improving both the computational training maneuver and the reduced order modeling approach are suggested. Nomenclature

show abstract

Section: -6mentioning

confidence: 99%

Application of Volterra Functions to X-31 Aircraft Model Motion

Cummings

2009

27th AIAA Applied Aerodynamics Conference

View full text Add to dashboard Cite

Recent advances towards an efficient computational method for accurately determining the stability and control characteristics of an aircraft are discussed and critiqued. The present approach with greatest promise is to reduce the number of high-fidelity CFD sim ulations by using Volterra functions Reduced Order Modeling. This type of reduced order model is a predictive model which has a unique training maneuver -a unit impulse. The advantage of such an approach is the fast prediction of the aerodynamic characteristics of an aircraft. This article presents the results of application of the Volterra functions ROM for prediction of linear movement of a 2D airfoil and of an X-31 aircraft model. The Volterra ROM predicted well normal and axial force which are linear or weakly non-linear and was in a fairly good agreement with pitching moment as long as the pitching moment predictions were weakly non-linear.

show abstract

Progress Toward Generation of a Navier-Stokes Database for a Harrier in Ground Effect

Abstract: The Harrier YAV-8B aircraft is capable of vertical and short-field take-off and landing (V/STOL) by directing its four exhaust

Cited by 25 publications

References 14 publications

Large-eddy simulation of twin impinging jets in cross-flow

Large-eddy simulation of twin impinging jets in cross-flow

Improved Methodologies for Maneuver Design of Aircraft Stability and Control Simulations

Application of Volterra Functions to X-31 Aircraft Model Motion

Contact Info

Product

Resources

About