Software
Scientific, Technical and Aviation Research and Software services
SOFTWARE SERVICES
The following services are offered for aircraft design. These are services for which
software is available from our own design studies. A complete description of the method
used is
detailed with each study. Prior and post analysis consultation is advised, and
coordination with other agencies can be arranged. On going project service as well as cad
drawings can be undertaken. Custom software writing can be undertaken at modest cost.
These include initial and detail design in aviation and the physical sciences.
WING PERFORMANCE AND LOAD ANALYSIS
The wing load analysis is based on non linear lifting line wing theory and gives complete
load distributions for vertical bending and shear, horizontal bending and shear and
torsion. The wing can be analysed throughout the performance envelope with variables of
speed,load factor,altitude,roll and yaw rates and flaps and/or ailerons deflected.
Reynolds number corrections are performed at each spanwise station. The local
lift coefficient distribution is given so that stall initiation and progression can be
estimated. Also detailed are the wing performance coefficients. This service is supplied
at
a cost of $500 and requires the wing geometry, the airfoil sectional data at the required
Reynolds numbers, the aircraft weight (for performance estimates), and the required flight
envelope (see below). In the absence of definitive Reynolds number corrections for the
airfoil section or if the data is in doubt then a statistical correction is applied.
Analysis results
are provided through out the flight envelope so that both structural and performance
optimisation can be performed. Optimisation of the wing can be performed subsequent to the
initial analysis. I keep a reasonably complete data base of airfoil data so that I can use
this source if you do not have airfoil data. This study can be extended to deflected flaps
and ailerons in
both level and rolling and/or yawing flight so that stall speeds, roll rates and damping
and aileron reversal speeds (needs wing stress analysis) can be estimated.
WING STRESS ANALYSIS (also control surfaces)
The wing stress analysis is based on beam bending theory applied to the wing as a whole
and the shear stresses for single or multiple shear cells. Stresses , deflections and
safety factors are given for each structural element at each wing spanwise location. The
torsional center, center of mass (for flutter estimates), vertical and torsional
deflection and weight are also given at each
spanwise location. This service is performed subsequent to the above load analysis. It
needs the wing structural details as regards placing of structural elements and their
material
properties . Prior discussion and consultation is advised to ensure correct use of
material properties when composite materials are used. Optimisation of the structure can
be performed.
Consult for unusual structures, mixed materials,large cutouts and wing joints.
AIRFOIL SELECTION
Using published airfoil data selects those section best suited for the range of aircraft
tasks. Enables inclusion of non numeric considerations such as construction simplicity,
stall character and performance under rough conditions due to ice,spray,dirt etc.
LONGITUDINAL STABILITY AND CONTROL
This service includes static longitudinal stability and control analyses and is run under
close consultation to give custom calculations and include details pertinent to the
subject aircraft. Standard features included, throughout the flight envelope and C of G
positions, are trim terms, control surface angles (including landing and nose wheel lift
off) and lift coefficients, neutral points stick fixed and stick free, effect of control
friction, stick force gradients, stick force per g , elevator angle per g etc. The service
cost is $200 for conventional aircraft and may be extended to optimise stabiliser
area,incidences, cg range etc. This service may be of
particular use for persons desiring to use their homebuilt aircraft for IFR flight. If
required dynamic stability analysis can be performed. Consult for costs.
DIRECTIONAL and LATERAL STABILITY AND CONTROL and STICK FORCE ESTIMATES.
Caries out directional and lateral stability and control of single or multi engined
aircraft with similar complete computational coverage as detailed in the longitudinal
analysis. A number of analysis of the spin behavior are made from different studies.
Rudder fixed and free and rudder lock behaviors are estimated. Estimates of the lateral
control power and dihedral effects are made. If performed in conjunction with a wing load
and stress analysis it can be used to estimate aileron reversal speeds. Dynamic stability
calculations are performed according to requirements. The service cost depends on
complexity and may be extended to resolve any problems uncovered.
FREE OR DUCTED PROPELLER ANALYSIS
Carries out propeller analysis by three methods. Initial study using constant or radial
graded momentum theory with subsequent initial blade design and optimisation by blade
element - momentum theory. Corrections for blade section mach and reynolds numbers are
made. Nacelle, fuselage and shroud affects can be included where required. Final studies
and optimisation using vortex theory throughout the flight envelope are used to conclude
the study.
PERFORMANCE ANALYSIS
Estimates aircraft performance using conventional methods. Includes trim drag,
interference estimates, reynolds number corrections and protruberences. Calculates maximum
speeds, take
off and climb performance for various fixed pitch or controllable pitch propellers.
Assumes conventional cooling drag estimates.
FLYING BOAT HULL ANALYSIS
Calculates hull stability and spray factors. Static flotation depths and angles at various
weights. Estimates hull drag and trim angles. Analysis of take of time,distance and power.
RIB PLOTTING
This service is usually used for multiple ribs in non uniform wings. It can cope with any
planform including double or multiple taper,and elliptical. The airfoil section or it's
relative thickness may be changed proportionately from root to tip. In addition an
external or internal line parallel
to the wing surface may be included to facilitate the preparation of templates for final
fairing of composite wings or internal lines for allowance for cap strips or sandwich skin
thickness. There is no limit on rib size. For ribs of greater depth than 8 inches the top
and bottom parts are plotted separately and joined at the chord line. This is usually
sufficient for personal type aircraft . For a large order this limit could be extended to
11 inches and 22 inches. There is no limit to the chordwise length of the ribs. The
present price is $ 5 per rib per copy for ribs under
8" depth with an additional charge of $3 for internal or external lines. For ribs
over 8" depth there is an additional charge of $4. The minimum charge of $100 covers
set up procedure.
FUSELAGE SECTION PLOTTING
Fuselage cross sections for preparation of composite molds or plugs and wood or aluminium
bulkheads. Uses a general cross section equation to produce well faired fuselage designs.
Cost is
$20 per section per copy. Consult for fuselage forms or send complete shape details. Your
fuselage side view and cross section can be mathematically faired so that the shape is
well defined and
reproducible. The shape can be examined for continuity to any degree so that all rates of
change of cross section magnitude and form are smooth. The minimum charge of $100 covers
set up
procedure.
FUSELAGE LOAD ANALYSIS
Details the wing, tail, power and inertia loads. Landing loads and estimates of impact
loads are included. Used prior to structural analysis.
ANALYSIS OF WOODEN SHELL FUSELAGE
Analysis and stress examination of a cold molded plywood semi monocoque fuselage
constructed of cross laminated spruce wood veneer. This is a beautiful way of constructing
complex curved
structures. The male mold does not require the extensive fairing,finishing and polishing
that fiber glass does. This set includes documentation and description of the complete
process of building a wooden wonder.
LANDING GEAR LOADS AND DEFLECTIONS
ANALYSIS OF SPRING STEEL OR GLASS U.C LEGS
Design and analysis of composite laminations and parts Uses standard stress strain
relations for angle ply lamina and laminates. Calculates various failure estimates ,
performs critical buckling stress estimates