1 def specify_inputs () -> tuple [tuple [float, .], tuple [float, .], 2 tuple [float, .]]: Returns a tuple containing three tuples: the first is a tuple of runway attributes, the second is a tuple of plane attributes and the third is a tuple of user specified input parameters.

Database System Concepts
7th Edition
ISBN:9780078022159
Author:Abraham Silberschatz Professor, Henry F. Korth, S. Sudarshan
Publisher:Abraham Silberschatz Professor, Henry F. Korth, S. Sudarshan
Chapter1: Introduction
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1 def specify_inputs () -> tuple [tuple [float, .], tuple [float,
tuple [float, .]]:
2
Returns a tuple containing three tuples: the first is a tuple of runway attributes, the second is
a tuple of plane attributes and the third is a tuple of user specified input parameters.
Example
2
>>> runway_attributes, plane_attributes, inputs
Input the length of the runway (km): 2
Input the slope of the runway (rad): 0
Input the mass of the plane (in kg): 45_000
Input the engine thrust (in N): 550_000
Input the reference area (in m^2): 750
Input the lift-off velocity (m/s): 70
Input the drag coefficient: 0.1
Input the air density (in kg/m^3): 1
...],
=
specify_inputs ()
Input the initial velocity (v_0) at start of runway (in m/s): 0
Input the position (x_0) at the start of the runway (in m): 0
Input the time increment (in secs): 0.1
>>> runway_attributes
(2.0, 0.0)
>>> plane_attributes
(45000.0, 550000.0, 750.0, 70.0, 0.1)
>>> inputs
(1.0, 0.0, 0.0, 0.1)
Note: In the Example above, the mass of the plane is 45, 000kg and the engine thrust is 550, 000N.
Transcribed Image Text:1 def specify_inputs () -> tuple [tuple [float, .], tuple [float, tuple [float, .]]: 2 Returns a tuple containing three tuples: the first is a tuple of runway attributes, the second is a tuple of plane attributes and the third is a tuple of user specified input parameters. Example 2 >>> runway_attributes, plane_attributes, inputs Input the length of the runway (km): 2 Input the slope of the runway (rad): 0 Input the mass of the plane (in kg): 45_000 Input the engine thrust (in N): 550_000 Input the reference area (in m^2): 750 Input the lift-off velocity (m/s): 70 Input the drag coefficient: 0.1 Input the air density (in kg/m^3): 1 ...], = specify_inputs () Input the initial velocity (v_0) at start of runway (in m/s): 0 Input the position (x_0) at the start of the runway (in m): 0 Input the time increment (in secs): 0.1 >>> runway_attributes (2.0, 0.0) >>> plane_attributes (45000.0, 550000.0, 750.0, 70.0, 0.1) >>> inputs (1.0, 0.0, 0.0, 0.1) Note: In the Example above, the mass of the plane is 45, 000kg and the engine thrust is 550, 000N.
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