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AES=O=
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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 |
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Inspection
of calculated Cp and wave elevation due to a
spheroide moving at various Froude numbers
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Inspection
of calculated Cp and wave elevation due to a
Wigley hull moving at various Froude numbers
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- 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 &
transonic
elements (coming
soon)
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- 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
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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 )
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Inspection
of calculated Cp and wave elevation due to a
sphere moving at various Froude numbers and at
various depths.
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Inspection/generation
panelling
(changing dihedral & thickness of a thick
wing)
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Warped
modes on a wing-body combination
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SPL levels on
finite cylinder and observerplane
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- 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.
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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 |
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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
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Inspection
of calculated steady Cp distribution at
upperside of a
thick wing at Mach = 0.9 and AOA=20 deg.
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Inspection
of calculated unsteady Cp distriibutions at
spanwise sections of
a thick wing at the first modeshape.
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Inspection
of calculated steady Cp distriibutions
at spanwise sections
of a thick wing at Mach = 0.9 and
AOA=0.32 deg. |
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Inspection
of calculated generalized forces on thick win at
Mach=0.9
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Inspection
of calculated Cl-Cd curves at
mach =0.2 .. 0.9 of
a thick wing. |
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Inspection
of calculated forces on ellipsoide |
Inspection
of geometry at spanwise sections of
a thick wing. |
