This is a set of basic aircraft performance estimation functions.
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| def | SUAVE.Methods.Performance.electric_payload_range.electric_payload_range (vehicle, mission, cruise_segment_tag, display_plot=True) |
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| def | SUAVE.Methods.Performance.electric_V_h_diagram.electric_V_h_diagram (vehicle, analyses, CL_max, delta_isa=0., grid_points=20., altitude_ceiling=2e4 *Units.ft, max_speed=130 *Units['m/s'], test_omega=800. *Units.rpm, display_plot=True) |
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| def | SUAVE.Methods.Performance.estimate_landing_field_length.estimate_landing_field_length (vehicle, analyses, airport) |
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| def | SUAVE.Methods.Performance.estimate_stall_speed.estimate_stall_speed (vehicle_mass, reference_area, altitude, maximum_lift_coefficient) |
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| def | SUAVE.Methods.Performance.estimate_take_off_field_length.estimate_take_off_field_length (vehicle, analyses, airport, compute_2nd_seg_climb=0) |
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| def | SUAVE.Methods.Performance.find_take_off_weight_given_tofl.find_take_off_weight_given_tofl (vehicle, analyses, airport, target_tofl) |
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| def | SUAVE.Methods.Performance.payload_range.payload_range (vehicle, mission, cruise_segment_tag, reserves=0.) |
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| def | SUAVE.Methods.Performance.propeller_single_point.propeller_single_point (energy_network, analyses, pitch, omega, altitude, delta_isa, speed, i_prop=0, plots=False, print_results=False) |
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| def | SUAVE.Methods.Performance.V_n_diagram.V_n_diagram (vehicle, analyses, weight, altitude, delta_ISA) |
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This is a set of basic aircraft performance estimation functions.
It includes field length and range calculations.
◆ electric_payload_range()
| def SUAVE.Methods.Performance.electric_payload_range.electric_payload_range |
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vehicle, |
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mission, |
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cruise_segment_tag, |
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display_plot = True |
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electric_payload_range(vehicle,
mission,
cruise_segment_tag,
display_plot=True):
Calculates and optionally displays a payload range diagram for a
Variable Cruise Distance - State of Charge SUAVE Mission and Vehicle.
Sources:
N/A
Assumptions:
Assumes use of Battery Propeller Energy Network
Inputs:
vehicle SUAVE Vehicle Structure
.mass_properties SUAVE Mass Properties Structure
.operating_empty Vehicle Operating Empty Mass [kg]
.max_payload Vehicle Maximum Payload Mass [kg]
.max_takeoff Vehicle Maximum Takeoff Mass [kg]
mission SUAVE Mission Structure
.Variable_Range_Cruise Mission Type
.Given_State_of_Charge Convergence Criteria
.cruise_tag Mission Segment Tag [String]
.target_state_of_charge End Mission State of Charge [Unitless]
cruise_segment_tag mission.cruise_tag [String]
Outputs:
payload_range = Data()
.range [0, Max PLD Range, Ferry Range] [m]
.payload [Max PLD, Max PLD , 0] [kg]
.takeoff_weight [MTOW, MTOW, OEW] [kg]
◆ electric_V_h_diagram()
| def SUAVE.Methods.Performance.electric_V_h_diagram.electric_V_h_diagram |
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vehicle, |
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analyses, |
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CL_max, |
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delta_isa = 0., |
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grid_points = 20., |
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altitude_ceiling = 2e4 * Units.ft, |
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max_speed = 130 * Units['m/s'], |
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test_omega = 800. * Units.rpm, |
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display_plot = True |
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electric_V_h_diagram(vehicle,
analyses,
delta_isa = 0.,
grid_points = 20.,
altitude_ceiling = 2e4 * Units.ft,
max_speed = 130 * Units['m/s'],
test_omega = 800. * Units.rpm,
display_plot = True,
climb_rate_contours = [0.]
):
Calculates and optionally displays climb rate and contours thereof over
a specified airspeed and altitude range. Climb rate determination ref.
Raymer, "Aircraft Design: A Conceptual Approach"
Sources:
D. Raymer, "Aircraft Design: A Conceptual Approach"
Assumptions:
Assumes use of Battery Propeller Energy Network
Inputs:
vehicle SUAVE Vehicle Structure
.mass_properties
.takeoff [kg]
analyses SUAVE Analyses Structure
.atmosphere
.planet
.sea_level_gravity [m/s^2]
delta_isa ISA Temperature Offset [deg. K/C]
grid_points Num. Test Points per Dim. [Int]
altitude_ceiling Maximum Test Altitude [User Set]
max_speed Maximum Test Speed [User Set]
test_omega Maximum Power Prop Speed [User Set]
display_plot Flag for Plot Generation [Boolean]
Outputs:
climb_rate Climb Rates at Test Points [ft/min]
◆ estimate_landing_field_length()
| def SUAVE.Methods.Performance.estimate_landing_field_length.estimate_landing_field_length |
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vehicle, |
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analyses, |
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airport |
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Computes the landing field length for a given vehicle configuration in a given airport.
Assumptions:
See source
Two wheel trucks (code needed for four wheel trucks also included)
Source:
Torenbeek, E., "Advanced Aircraft Design", 2013 (equation 9.25)
Inputs:
airport.
atmosphere [SUAVE data type]
altitude [m]
delta_isa [K]
vehicle.
mass_properties.landing [kg]
reference_area [m^2]
maximum_lift_coefficient (optional) [Unitless]
Outputs:
landing_field_length [m]
Properties Used:
N/A
◆ estimate_stall_speed()
| def SUAVE.Methods.Performance.estimate_stall_speed.estimate_stall_speed |
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vehicle_mass, |
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reference_area, |
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altitude, |
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maximum_lift_coefficient |
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Calculates the stall speed of an aircraft at a given altitude and a maximum lift coefficient.
Sources:
N/A
Assumptions:
None
Inputs:
vehicle_mass vehicle mass [kg]
reference_area vehicle reference area [m^2]
altitude cruise altitude [m]
maximum_lift_coefficient maximum lift coefficient [unitless]
Outputs:
V_stall stall speed [m/s]
◆ estimate_take_off_field_length()
| def SUAVE.Methods.Performance.estimate_take_off_field_length.estimate_take_off_field_length |
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vehicle, |
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analyses, |
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airport, |
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compute_2nd_seg_climb = 0 |
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Computes the takeoff field length for a given vehicle configuration in a given airport.
Also optionally computes the second segment climb gradient.
Assumptions:
For second segment climb gradient:
One engine inoperative
Only validated for two engine aircraft
Source:
http://adg.stanford.edu/aa241/AircraftDesign.html
Inputs:
analyses.base.atmosphere [SUAVE data type]
airport.
altitude [m]
delta_isa [K]
vehicle.
mass_properties.takeoff [kg]
reference_area [m^2]
V2_VS_ratio (optional) [Unitless]
maximum_lift_coefficient (optional) [Unitless]
networks.*.number_of_engines [Unitless]
Outputs:
takeoff_field_length [m]
Properties Used:
N/A
◆ find_take_off_weight_given_tofl()
| def SUAVE.Methods.Performance.find_take_off_weight_given_tofl.find_take_off_weight_given_tofl |
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vehicle, |
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analyses, |
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airport, |
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target_tofl |
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Estimates the takeoff weight given a certain takeoff field length.
Assumptions:
assumptions per estimate_take_off_field_length()
Source:
N/A
Inputs:
vehicle.mass_properties.
operating_empty [kg]
max_takeoff [kg]
analyses [SUAVE data structure]
airport [SUAVE data structure]
target_tofl [m]
Outputs:
max_tow [kg]
Properties Used:
N/A
◆ payload_range()
| def SUAVE.Methods.Performance.payload_range.payload_range |
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vehicle, |
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mission, |
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cruise_segment_tag, |
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reserves = 0. |
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Calculates a vehicle's payload range diagram. Includes plotting.
Assumptions:
Constant altitude cruise
Source:
N/A
Inputs:
vehicle.mass_properties.
operating_empty [kg]
max_zero_fuel [kg]
max_takeoff [kg]
max_payload [kg]
max_fuel [kg]
takeoff [kg]
mission.segments[0].analyses.weights.
vehicle.mass_properties.takeoff [kg]
cruise_segment_tag <string>
Outputs:
payload_range.
range [m]
payload [kg]
fuel [kg]
takeoff_weight [kg]
PayloadRangeDiagram.dat (text file)
Properties Used:
N/A
◆ propeller_single_point()
| def SUAVE.Methods.Performance.propeller_single_point.propeller_single_point |
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energy_network, |
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analyses, |
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pitch, |
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omega, |
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altitude, |
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delta_isa, |
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speed, |
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i_prop = 0, |
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plots = False, |
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print_results = False |
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propeller_single_point(energy_network,
analyses,
pitch,
omega,
altitude,
delta_isa,
speed,
plots=False,
print_results=False):
Uses SUAVE's BEVW propeller model to evaluate propeller performance at a
single altitude, pitch command, and angular velocity. Can be used indep-
endently, or as part of creation of a propller maps or flight envelopes.
Sources:
N/A
Assumptions:
Assumes use of Battery Propeller Energy Network, All Assumptions of
the BEVW model.
Inputs:
energy_network SUAVE Energy Network
.propeller SUAVE Propeller Data Structure
analyses SUAVE Analyses Structure
.atmosphere SUAVE Atmosphere Analysis Object
pitch Propeller Pitch/Collective [User Set]
omega Test Angular Velocity [User Set]
altitude Test Altitude [User Set]
delta_isa Atmosphere Temp Offset [K]
speed Propeller Intake Speed [User Set]
HFW Flag for use of helical fixed wake for rotor [Boolean]
plots Flag for Plot Generation [Boolean]
print_results Flag for Terminal Output [Boolean]
Outputs:
results SUAVE Data Object
.thrust BEVW Thrust Prediction [N]
.torque BEVW Torque Prediction [N-m]
.power BEVW Power Prediction [W]
.power_coefficient BEVW Cp Prediction [Unitless]
.efficiency BEVW Efficiency Prediction [Unitless]
.induced_axial_velocity BEVW Ind. V_a Prediction [m/s]
.induced_tangential_velocity BEVW Ind. V_tPrediction [m/s]
.radial_distribution BEVW Radial Stations [m]
.thrust_distribution BEVW T Dist. Prediction [N/m]
.torque_distribution BEVW Q Dist. Prediction [(N-m)/m]
.tangential_velocity BEVW V_t Prediction [m/s]
.axial_velocity BEVW V_a Prediction [m/s]
◆ V_n_diagram()
| def SUAVE.Methods.Performance.V_n_diagram.V_n_diagram |
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vehicle, |
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analyses, |
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weight, |
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altitude, |
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delta_ISA |
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Computes a V-n diagram for a given aircraft and given regulations for ISA conditions
Source:
S. Gudmundsson "General Aviation Aircraft Design: Applied Methods and Procedures", Butterworth-Heinemann; 1 edition
CFR FAR Part 23: https://www.ecfr.gov/cgi-bin/text-idx?SID=0e6a13c7c1de7f501d0eb0a4d71418bd&mc=true&tpl=/ecfrbrowse/Title14/14cfr23_main_02.tpl
CFR FAR Part 25: https://www.ecfr.gov/cgi-bin/text-idx?tpl=/ecfrbrowse/Title14/14cfr25_main_02.tpl
Inputs:
analyses.base.atmosphere [SUAVE data type]
vehicle.
reference_area [m^2]
maximum_lift_coefficient [Unitless]
minimum_lift_coefficient [Unitless]
chords.mean_aerodynamic [m]
envelope.FARpart_number [Unitless]
limit_loads.positive [Unitless]
limit_loads.negative [Unitless]
cruise_mach [Unitless]
weight [kg]
altitude [m]
delta_ISA [deg C]
Outputs:
V_n_data
Properties Used:
N/A
Description:
The script creates an aircraft V-n diagram based on the input parameters specified by the user.
Depending on the certification flag, an appropriate diagram, output and log files are created.
1.8.15