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dis dcp

Inspection of calculated Cp and velocities on a composition of 8 payloads at AOA=30 deg, AOS ==30 deg and Msch=0.9 Inspection of calculated   Cp and velocities on a composition of 4 rings at AOA=50 deg, AOS ==30 deg and Mach=0.34  

spheroide wigley

Inspection of calculated Cp and wave elevation due to  a spheroide moving at various Froude numbers
 Inspection of calculated Cp and wave elevation due to  a Wigley hull moving at various Froude numbers

  • Calculation & Analysis of 2D & 3D steady and unsteady aerodynamic forces on deformed/trimmed and oscillating  platforms( AirCraft & WaterCraft)
  • Incompressible, Subsonic(Transonic) and Supersonic
  • Efficient integration of Havelock sources & doublets (implicit linearized free-surface  BC)  for Froude >=0. and frequency >=0 with a unique propiertor integration method.
  • True surface BVM methods for realistic geometry (wings/T-tails/Winglets/fuselages/payloads et cetera ) and  lifting surface  methods.
  • Accurate suction force model for induced drag prediction  on lifting surface models.
  • Arbitrary configurations
  • Symmetric, anti-symmetric, ground & wall models.
  • Permeability model for inlets/outlets & bluff body parts modelling
  • Shockpatches  for approximate transonic modelling & ( )
  • Observer surfaces (interference analysis)
  • Free-surface patches for hydroelastic modelling (explicit Rankine model).
  • Acoustic modelling. Easy modeling of incident sound potential & impedance distributions.
  • Rigid, sub-rigid (effectors)  & arbitrary motions/deformations, gusts & waves
  • Warping of arbitrary deformation (eg. FEM)  by efficient volume spline class methods.    
  • Geometry  correction (Mach (Froude) number, angle of attack, Reynolds number & position dependent!) to accommodate boundary layer and edge effects.
  • Trim vector to model static deformation and effector settings.
  • Harmonic and exponentially growing unsteady motions and gusts.
  • Pressure, force, moment and generalised force coefficients
  • H continuation of harmonic generalised forces
  • Data, xls and graphical output

spheroide spheroide

nspection of calculated Cp and wave elevation due to Coene's deltawing moving at various Froude numbers and angle of attack (R. Coene, A SLENDER DELTAWING OSCILATING IN SURFACE WAVES. An example in unsteady propulsion,  DEPARTMENT OF AEROSPACE ENGINEERING, REPORT LR -257, Dec. 1977 )
 Inspection of calculated Cp and wave elevation due to  a sphere moving at various Froude numbers and at various depths.
geometry
dis+

Inspection/generation panelling (changing dihedral & thickness of a thick wing)
Warped modes on a wing-body combination


SPL levels on finite  cylinder and observerplane
geometry  
  • 3D inspection/analysis  of panelling, trim state (static deformation & effector settings), displacement modes, pressure distribution & warping.
  • Generation and editing of paneling (including sweep, taper, dihedral, thickness &  twist).
  • Transparant Input&Output & ease of use
  • Aerodynamic  geometry can be edited in the app
  • Structural data (geometry & modeshapes) is efficiently warped to the aerodynamic geometry.
  • Warpings can be stored for reuse, accommodating follow on stages of a design cycle ( Mach number and/or frequency changes).
  • The solution matrices can be stored for reuse  accommodating follow on stages of a design cycle ( mode shape changes). Also it is made possible to coarsen the paneling in one button click  to reduce computational work.
  • The calculated pressure distribution can be factored with a correction (Mach (Froude) number, frequency and position dependent!) to accommodate transonic, boundary layer and edge effects. 
  • The  calculations can also be performed in batch.

Inspection of calculated imaginary part of unsteady Cp jump  distribution of a  rectangular lifting surface with a shock patch at 70%  chord at Mch 0.875 and reduced frequency=1.0 demostrating approximate transonic modelling 

gains
gains

Inspection of calculated real part of unsteady Cp distribution at upperside  of a  thick wing at extreme position of the modeshapes at Mch 0.9 and reduced frequency=1.0
 Inspection of calculated steady Cp distribution at upperside  of a  thick wing at Mach = 0.9 and AOA=20 deg.

gains gains

Inspection of calculated unsteady  Cp distriibutions at spanwise sections of a  thick wing at the first modeshape.
 Inspection of calculated steady   Cp distriibutions at spanwise sections of a  thick wing at Mach = 0.9 and AOA=0.32  deg.

gafs gains

Inspection of calculated generalized forces on thick win at Mach=0.9
 Inspection of  calculated  Cl-Cd curves   at mach =0.2 .. 0.9 of a  thick wing.

gafs gains

Inspection of calculated  forces on ellipsoide Inspection of  geometry  at spanwise sections of a  thick wing.

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