An improved immersed boundary method for turbulent flow simulation on Cartesian grids is proposed. To determine the appropriate conditions, near-wall approximation of mean-flow equation and Spalart–Allmaras turbulence model investigated. A modified velocity profile that linear with respect to distance from wall can be resolved by a numerical scheme second-order spatial accuracy derived. As profile, eddy-viscosity maintain balance shear stress. obtain as solution, condition tangential damping...

To predict the deformation and aerodynamic performance of a passive morphing airfoil with novel compliant structure, aeroelastic simulation methods were developed. The static problem was solved by loosely coupling finite-element-method solver hierarchical Cartesian grid-based flow solver. viscous effect investigated comparing results using Euler Reynolds-averaged Navier–Stokes (RANS) equations in simulations. accuracies structural solvers validated through wind-tunnel experiments,...

Three-dimensional unsteady flow structure inside a deployed slat of high-lift configuration is simulated numerically to investigate the cause noise. Because Reynolds number high and geometry complex, zonal large eddy simulation/Reynolds-averaged Navier-Stokes hybrid method used reduce overall computational cost. The power spectral density pressure coefficient compared experiment, some issues regarding grid resolution, order numerical scheme, subiterations for implicit time integration are...

Transonic turbulent flows around the NASA Common Research Model are simulated to investigate capability of Cartesian-grid-based flow solver UTCart in three-dimensional high-Reynolds-number simulations. consists an automatic Cartesian grid generator based on octree structure and a compressible that uses immersed boundary method with wall function for condition. Using generator, medium (approximately 50 million cells) is generated 43 min. For prediction drag coefficient at cruise condition,...

The purpose of this study is to design noise reduction devices for leading-edge slat which called as a cove filler (SCF), from both aerodynamic and acoustic points view. From the previous studies, SCF seems have an effect on reducing broadband by forming substantially continuous shape instead cusp configuration. However, there are some studies indicate decrease performance when attached. Since primary feature high-lift-devices increase performance, maximum lift coefficient or stall angle...

Airframe noise generation at the flap-edge is investigated on a simplified three elements high-lift configuration wing model. Lowspeed wind tunnel experiments for aerodynamics measurements in JAXA-LWT2 and Large scale anechoic facility of Railway Technical Research Institute as well steady-state Reynolds-Average NavierStokes computation (RANS) has been implemented. Cross spectrum analysis computational results connect far-field near-field unsteadiness, then show mechanism around flap-edge....

This paper deals with results of noise measurements for a 40% two-wheel type aircraft main landing gear in lowspeed wind tunnel experiments. In order to accurately assess source location and far-field characteristics during the approach phase, scale model complex geometry which was equipped small components such as link mechanism, hydraulic tubes electrical wiring well tire, cylinder, piston, doors, sidebrace used. Model based on LEG (Landing Evaluation Geometry) designed by manufacturer...

Flow simulations around an airfoil (NACA0012) using Lattice Boltzmann Method (LBM) are performed in this paper. Originally, LBM is incompressible flow solver on orthogonal coordinates. However, order to resolve the boundary layer of accurately, algorithm extended generalized Also, suitable wall condition introduced for First all, present numerical method validated at relatively small Reynolds number (Re=500). The velocity profile compared detail with CFL3D results and consistent obtained....

Landing gear noise is one of the dominant sources from an aircraft during approach phase due to low engine rate setting. Two different computational fluid dynamics (CFD) codes are used understand flow physics around a two-wheel main landing gear. First, solver for unstructured grid simulate steady-state field complex The basic pattern investigated and potential sources, such as separation, wake accelerated regions observed. Additionally, effects wind tunnel wall, both closed open test...

精米の袋に品種,産地,生産年を表示することが義務づけられたため,客観的方法によって表示の正否を確かめるための技術開発が必要とされている.そこで,農業試験場の基準品種を試料とし, PCR法による実験に供試した.有望なRAPDプライマーを用いて品種識別バンドを選定し,アガロースゲルから切り出したDNAを大腸菌に組み込んで増幅し,その塩基配列を決定した.その配列のRAPDプライマー部分から延長して15～29量体のフォワードプライマーおよびリバースプライマーを設計した.こうして作成したSTS化プライマーを組み合わせることにより,「コシヒカリ」を他の品種と識別するためのポジティブプライマーセットおよびネガティブプライマーセットを開発した.これらのセットを用いるPCRにより,全国の33産地の「コシヒカリ」では同一のDNAパターンが得られ,「コシヒカリ」と他の49品種との識別が可能であることが明らかとなった.このプライマーセットの開発により, 1粒の米試料による「コシヒカリ」の同定が可能であるばかりでなく,他品種米の混入も簡易かつ明瞭に検出することが可能となった.

Rice (Oryza sativa var. Nipponbare) was transformed with an artificial avidin gene. The features of this construct are as follows: (1) a signal peptide sequence derived from barley alpha amylase added at the N-terminal region, (2) codon usage gene optimized for rice, and (3) driven by rice glutelin GluB-1, endosperm-specific promoter. Avidin produced in grain transgenic but not leaves. concentration kernels about 1,800 ppm. All larvae confused flour beetle (Tribolium confusum) Angoumois moth...

Proper orthogonal decomposition (POD) or dynamic mode (DMD) are useful analytical techniques for describing the behavior of a complicated flow by decomposing into several components called modes. In POD analysis, is most efficiently decomposed orthonormal modes in terms energy, so energy can be extracted using small number On other hand, DMD structures that have specific frequencies observed managing sequence given time series data. this study, and analyses were applied to experimental...

This paper presents computational and experimental studies on the flap side-edge noise using a three-element rectangular high-lift wing model with full-span slat part-span for device research in JAXA. The main purpose of this is focused numerical investigation change flowfield far-field by sideedge shapes. Several configurations rounded side-edges, cavity side-edge, protruding-type lower surface are investigated paper. By computations wind tunnel tests, mechanisms generation reduction discussed.

Flow structures around a NACA0012 wingtip are investigated using zonal LES/RANS hybrid method in order to understand the noise generation mechanism flap-edge. It is known from previous studies that flow blunt similar of Grid dependency performed for both time-averaged and unsteady components, results assessed via comparison with experimental data. became apparent more sensitive chordwise grid resolution, compared these RANS. Based on validated data, discussed. The near-field relevant...