fly/fgdata
1
0
Fork 0
Code Activity

s/gif/png/

Browse source
This commit is contained in:
mfranz 2006-08-14 22:42:51 +00:00
parent eeeea44805
commit 37e810a805
1 changed files with 14 additions and 14 deletions
Show stats Download patch file Download diff file Expand all files Collapse all files

28
Docs/README.yasim
View file

@ -166,7 +166,7 @@ jet: A turbojet/fan engine. It accepts a <control> subelement to map a
afterburner: Maximum total thrust with afterburner/reheat,
in pounds [defaults to "no additional
thrust"].
rotate: Vector angle of the thrust in degrees about the
rotate: Vector angle of the thrust in degrees about the
Y axis [0].
n1-idle: Idling rotor speed [55].
n1-max: Maximum rotor speed [102].
@ -212,13 +212,13 @@ propeller: A propeller. This element requires an engine subtag.
min-rpm: The minimum operational RPM for a constant speed
propeller. This is the speed to which the
prop governor will seek when the blue lever
is at minimum. The coarse-stop attribute
is at minimum. The coarse-stop attribute
limits how far the governor can go into trying
to reach this RPM.
max-rpm: The maximum operational RPM for a constant speed
propeller. See above. The fine-stop attribute
limits how far the governor can go in trying
to reach this RPM.
to reach this RPM.
fine-stop: The minimum pitch of the propeller (high RPM) as a
ratio of ideal cruise pitch. This is set to 0.25
by default -- a higher value will result in a
@ -280,7 +280,7 @@ turbine-engine: A turbine engine definition. This must be a subelement
max-n2: N2 (percent) turbine speed at max throttle.
bsfc: Specific fuel consumption, in lbs/hr per
horsepower.
actionpt: Defines an "action point" for an enclosing jet or propeller
element. This is the location where the force from the thruster
@ -316,7 +316,7 @@ gear: Defines a landing gear. Accepts <control> subelements to map
launchbar: Defines a catapult launchbar or strop.
x,y,z: The location of the mount point of the launch bar or
strop on the aircraft.
length: The length of the launch bar from mount point to tip
length: The length of the launch bar from mount point to tip
down-angle: The max angle below the horizontal the
launchbar can achieve.
up-angle: The max angle above the horizontal the launchbar
@ -442,12 +442,12 @@ control: This element, which can appear in two different contexts,
rotor: A rotor. Used for simulating helicopters. You can have one, two
or even more.
There is a drawing of a rotor in the Doc-directory
(README.yasim.rotor.gif) Please find the measures from this drawing
(README.yasim.rotor.png) Please find the measures from this drawing
for several parameters in square brackets [].
If you specify a rotor, you do not need to specify a wing or hstab,
the settings for approach and cruise will be ignored then. You have
to specify the solver results manually. See below.
name: The name of the rotor.
(some data is stored at /rotors/name/)
The rpm, cone angle, yaw angle and roll angle are stored
@ -486,13 +486,13 @@ rotor: A rotor. Used for simulating helicopters. You can have one, two
you need a point where to measure the incidence angle.
Zero means at the base, 1 means at the tip. Typically
it should be something near 0.7
rel_len_blade_start: Typically the blade is not mounted in the
rel_len_blade_start: Typically the blade is not mounted in the
center of the rotor [a/R]
rpm: rounds per minute.
ccw: determines if the rotor rotates clockwise (="0") or
counterclockwise (="1"), (if you look on the top of the
normal, so the bo105 has counterclockwise rotor).
"true" and "false" are not any longer supported to
"true" and "false" are not any longer supported to
increase my lifespan. ;-)
maxcollective: The maximum of the collective incidence in degree
mincollective: The minimum of the collective incidence in degree
@ -532,13 +532,13 @@ rotor: A rotor. Used for simulating helicopters. You can have one, two
For incidence>(incidence_stall+stall_change_over) there is
stall. In the range between this incidences it is
interpolated linear.
The airfoil of the rotor can be described in two ways. First you
can define the needed power for different pitch values and the
total lift force at a user-defined pitch value. Don't use pitch
values greater than the stall incidence. You could get strange
results.
pitch_a: A collective incidence angle, used for the next token
forceatpitch_a: The force, the rotor is producing when the incident
angle is equal pitch_a. Without ground effect and with
@ -551,7 +551,7 @@ rotor: A rotor. Used for simulating helicopters. You can have one, two
poweratpitch_0: the power the rotor needs at zero pitch.
In kW. Used for calculation of the airfoil coefficients.
In near future you can define them directly.
The second way is to define the lift and drag coefficients directly.
Without stall the c_lift of the profile is assumed to be
sin(incidence-airfoil_incidence_no_lift)*liftcoef;
@ -570,7 +570,7 @@ rotor: A rotor. Used for simulating helicopters. You can have one, two
you will get a value larger than the measured one. This seems to be
valid for this simulation. If you use values for the lift
coefficient from real airfoils you will get unrealistic high lift as
result (approx. a factor of 2). As starting parameters you can use
result (approx. a factor of 2). As starting parameters you can use
airfoil_lift_coefficient="1.9"
airfoil_drag_coefficient0="0.0075"
airfoil_drag_coefficient1="0.2"
@ -608,7 +608,7 @@ rotor: A rotor. Used for simulating helicopters. You can have one, two
translift_maxfactor: Helicopters have "translational lift", which
is due to turbulence. In forward flying the rotor gets less
turbulence air and produces more lift. The factor is the
quotient between lift at high airspeeds to the lift at
quotient between lift at high airspeeds to the lift at
hover (with same pitch).
translift_ve: the speed, where the translational lift reaches 1/e of
the maximum value. In m/s.