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SUAVE
2.5.2
An Aerospace Vehicle Environment for Designing Future Aircraft
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SUAVE
2.5.2
An Aerospace Vehicle Environment for Designing Future Aircraft
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Functions | |
| def | SUAVE.Methods.Flight_Dynamics.Static_Stability.Approximations.Supporting_Functions.convert_sweep.convert_sweep (wing, old_ref_chord_fraction=0.0, new_ref_chord_fraction=0.25) |
| def | SUAVE.Methods.Flight_Dynamics.Static_Stability.Approximations.Supporting_Functions.convert_sweep.convert_sweep_segments (old_sweep, seg_a, seg_b, wing, old_ref_chord_fraction=0.0, new_ref_chord_fraction=0.25) |
| def | SUAVE.Methods.Flight_Dynamics.Static_Stability.Approximations.Supporting_Functions.extend_to_ref_area.extend_to_ref_area (surface) |
| def | SUAVE.Methods.Flight_Dynamics.Static_Stability.Approximations.Supporting_Functions.trapezoid_ac_x.trapezoid_ac_x (wing) |
| def | SUAVE.Methods.Flight_Dynamics.Static_Stability.Approximations.Supporting_Functions.trapezoid_mac.trapezoid_mac (wing) |
| trapezoid_mac.py More... | |
| def SUAVE.Methods.Flight_Dynamics.Static_Stability.Approximations.Supporting_Functions.convert_sweep.convert_sweep | ( | wing, | |
old_ref_chord_fraction = 0.0, |
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new_ref_chord_fraction = 0.25 |
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| ) |
This method converts the sweep of a wing planform to refer to a new
chord fraction. Defaults to converting from leading-edge sweep to
quarter-chord sweep.
Assumptions:
Assumes a simple trapezoidal wing shape. If the input wing object does
not have a simple trapezoidal shape, this function will convert sweeps
for an equivalent trapezoid having the same reference sweep, aspect
ratio, and taper ratio.
Source:
Unknown
Inputs:
wing - a data dictionary with the fields:
apsect_ratio - wing aspect ratio [dimensionless]
sweep - wing sweep [radians]
taper - wing taper ratio [dimensionless]
old_ref_chord_fraction - a float value between 0 and 1.0 that
tells what fraction of the local chord
the sweep line follows. (For example,
a value of 0.25 refers to quarter-chord
sweep
new_ref_chord_fraction - a float value between 0 and 1.0 that
tells what fraction of the local chord
is the new reference for sweep.
Outputs:
output - a single float value, new_sweep, which is the sweep
angle referenced to the new_ref_chord_fraction.
Defaults:
Defaults to converting from leading edge sweep to quater-chord sweep.
Properties Used:
N/A
| def SUAVE.Methods.Flight_Dynamics.Static_Stability.Approximations.Supporting_Functions.convert_sweep.convert_sweep_segments | ( | old_sweep, | |
| seg_a, | |||
| seg_b, | |||
| wing, | |||
old_ref_chord_fraction = 0.0, |
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new_ref_chord_fraction = 0.25 |
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| ) |
This method converts the sweep of a section of a wing between two segments
to refer to a new chord fraction. More specifically, it converts the inboard
segment's (seg_a's) outboard sweep. Defaults to converting from leading-edge sweep to
quarter-chord sweep.
Assumptions:
Assumes a simple trapezoidal section shape. If the input section does
not have a simple trapezoidal shape, this function will convert sweeps
for an equivalent trapezoid having the same reference sweep, aspect
ratio, and taper ratio.
Source:
Unknown
Inputs:
old_sweep - sweep angle to convert
seg_a and seg_b - two Segment() objects with:
root_chord_percent - percent of the wing's root chord
wing - a data dictionary with the fields:
chords.root - root chord [m]
span - wingspan [m]
symmetric - symmetry [boolean]
old_ref_chord_fraction - a float value between 0 and 1.0 that
tells what fraction of the local chord
the sweep line follows. (For example,
a value of 0.25 refers to quarter-chord
sweep
new_ref_chord_fraction - a float value between 0 and 1.0 that
tells what fraction of the local chord
is the new reference for sweep.
Outputs:
output - a single float value, new_sweep, which is the sweep
angle referenced to the new_ref_chord_fraction.
Defaults:
Defaults to converting from leading edge sweep to quater-chord sweep.
Properties Used:
N/A
| def SUAVE.Methods.Flight_Dynamics.Static_Stability.Approximations.Supporting_Functions.extend_to_ref_area.extend_to_ref_area | ( | surface | ) |
This method takes inputs describing the exposed portion of a trapezoidal
aerodynamic surface and calculates the dimensions of a corresponding
aerodynamic surface that extends all the way to the fuselage centerline.
Particularly used to get the vertical tail reference area for lateral
stability calculations when the dimensions of the exposed tail are known.
Assumptions:
Assumes a simple trapezoidal half-wing shape.
Source:
Unknown
Inputs:
surface - a SUAVE Wing object with the fields:
spans.projected - projected span (height for a vertical tail) of
the exposed surface [meters]
sweep - leading edge sweep of the aerodynamic surface [radians]
chords.root - chord length at the junction between the tail and
the fuselage [meters]
chords.tip - chord length at the tip of the aerodynamic surface [meters]
symmetric - Is the wing symmetric across the fuselage centerline?
exposed_root_chord_offset - the displacement from the fuselage
centerline to the exposed area's physical root chordline [meters]
Outputs:
ref_surface - a data dictionary with the fields:
spans.projected - The span/height measured from the fuselage centerline [meters]
area.reference - The area of the extended trapezoidal surface [meters**2]
aspect_ratio - The aspect ratio of the extended surface [meters]
chords.root - The chord of the extended trapezoidal surface
where it meets the fuselage centerline [meters]
root_LE_change - The change in the leading edge position of the
surface compared to the smaller surface that only extended to the
fuselage surface. This value is negative for sweptback surfaces [meters]
Properties Used:
N/A
| def SUAVE.Methods.Flight_Dynamics.Static_Stability.Approximations.Supporting_Functions.trapezoid_ac_x.trapezoid_ac_x | ( | wing | ) |
This method computes the aerodynamic center x-position of a linearly
tapered trapezoidal aerodynamic surface
Assumptions:
Assumes a simple trapezoidal wing shape.
Does not account for twist or LE/TE extensions
Assumes the aerodynamic center of the wing is located at the quarter-
chord of the MAC.
Source:
Unknown
Inputs:
wing - a data dictionary with the fields:
areas.reference - planform area of the trapezoidal wing [meters**2]
spans.projected - wing span [meters]
chords.root - wing root chord [meters]
taper - wing taper ratio [dimensionless]
sweep - wing leading edge sweep [radians]
symmetric - wing symmetry [Boolean]
Outputs:
dx_ac - the x-direction distance of the aerodynamic center of the wing
(or equivalent trapezoid) measured from the leading edge of the wing
root [meters]
Properties Used:
N/A
| def SUAVE.Methods.Flight_Dynamics.Static_Stability.Approximations.Supporting_Functions.trapezoid_mac.trapezoid_mac | ( | wing | ) |
trapezoid_mac.py
Created: Mar 2014, T. Momose Modified: Jan 2016, E. Botero
This method computes the mean aerodynamic chord of a linearly tapered
trapezoidal aerodynamic surface
Assumptions:
Assumes a simple trapezoidal wing shape.
Source:
Unknown
Inputs:
wing - a data dictionary with the fields:
areas.reference - the planform area of the trapezoidal wing [meters**2]
spans.projected - wing span [meters]
chords.root - the wing root chord [meters]
{One of the following}
chords.tip - the wing tip chord [meters]
taper - taper ratio of the wing [dimensionless]
Outputs:
mac - the mean aerodynamic chord of the wing (or equivalent trapezoid) [meters]
Properties Used:
N/A
1.8.15