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jet-planes-fly-in-python A jet aircraft (or simply jet) is an aircraft (nearly always a fixed-wing aircraft) propelled by jet engines. Whereas the engines in propeller-powered aircraft generally achieve their maximum efficiency at much lower speeds and altitudes, jet engines achieve maximum efficiency at speeds close to or even well above the speed of sound. Jet aircraft generally cruise most efficiently at about Mach ( km/h ( mph)) and at altitudes around 10,–15, m (33,–49, ft) or more. How Airplanes Fly Airplanes fly because they are able to generate a force called Lift which normally moves the airplane upward. Lift is generated by the forward motion of the airplane through the air. This motion is produced by the Thrust of the engine(s). The figure below is a simple diagram of the four forces acting on an airplane – Thrust, Lift, Drag and Weight. Drag is the force produced by the resistance of the air to the forward motion of the airplane.  This page provides an explanation of how airplanes fly in simple terms, and is meant as a brief introduction to the topic. No attempt will be made to discuss all of the real-life factors involved in flight or the mathematical formulas needed to compute the results of these factors on an airplane in flight. Source. Открыть Страницу «Jet Planes» на Facebook. Вход. или. Создать аккаунт. Открыть Страницу «Jet Planes» на Facebook. Вход. Забыли аккаунт?  Связаться со Страницей Jet Planes в Messenger. www.- Туристическая компания. Прозрачность СтраницыПодробнее. Facebook показывает информацию, которая поможет вам лучше понять цель Страницы. Просматривайте действия людей, которые управляют контентом и публикуют его. Страница создана 11 октября г. Specifies the propulsion system type. A list of two lists and an integer of jet planes fly in python form [[fig width, fig height, dpi], [axes label font size, tick font size, legend font size], colourscheme]. This is indeed one of the main strengths of Vaex: one can do numerous selections, filters, groupings, and various calculations without having to worry about RAM, as I will show throughout this article. Contains the following key names:. Wikimedia Commons has media related to Avro Lincoln. II G All for you.

It covers the first 50km of the atmosphere. Float or numpy array of floats. Equivalent airspeed any unit, returned TAS value will be in the same unit. We approximate this relationship with the expression:. See also mpseas2mpscas. The reverse conversion is slightly more complicated, as their relationship depends on the Mach number. The unit- specific nature of the function is also the result of the need for computing the Mach number.

International Civil Aviation Organisation code of the airport. Required if the user wishes to equip this object with the attributes of a specific, existing runway, e. Runway data is obtained from an off-line image of the ourairports. Specifies which of the runways at the airport specified by the ICAO code above we want to associate with the runway object. The number of runways can be found in the nrways attribute of the runway object:.

Parameters of bespoke, user-defined runways. The recommended use of these is as indicated by their names, though the user may wish to adopt their own definitions to suit particular applications for example, surf can be any string describing the runway surface. List of floats. Wind directions expressed in degrees true e. Scalar or numpy array. The runway direction component of the wind sign convention: headwinds are positive.

The cross component of the wind sign convention: winds from the right are positive. Definition of a basic aircraft concept.

An object of this class defines an aircraft design in terms of the brief it is aiming to meet, high level design variables that specify it, key parameters that describe its performance , as well as the atmosphere it operates in. These are the four arguments that define an object of the AircraftConcept class.

The first three are dictionaries, as described below, the last is an object of Atmosphere class. Definition of the design brief, that is, the requirements the design seeks to meet. Contains the following key names:. The altitude in metres where the climb rate requirement is specified. Optional, defaults to zero sea level.

The fraction nondimensional of the maximum available thrust at which the cruise speed requirement must be achieved. The required service ceiling in meters that is, the altitude at which the maximum rate of climb drops to feet per minute. The speed knots indicated airspeed at which the service ceiling must be reached. This should be an estimate of the best rate of climb speed. The elevation in metres of the runway againts which the take-off constraint is defined.

The speed of the take-off headwind in knots , parallel to the runway. Optional, defaults to zero. The percent gradient of the runway in the direction of travel. Altitude in metres where the turn requirement is defined. True airspeed in knots at which the turn requirement above has to be met. Since the dynamics of turning flight is dominated by inertia, which depends on ground speed, the turn Jet Planes Are Flying In Python speed is specified here as TAS on the zero wind assumption.

Main wing sweep angle measured at the maximum thickness point. Main wing sweep angle measured at the quarter chord point. Standard definition of wing tip chord to root chord ratio, zero for sharp, pointed wing-tip delta wings. Optional, defaults to the theoretical optimal value as a function of the quarter-chord sweep angle. The ratio of altitude h to wingspan b, used for the calculation of ground effect.

Optional, defaults to produces a ground effect factor of near unity. Specifies the propulsion system type. Throttle ratio for gas turbine engines.

Higher tr values mean thrust decay starting at higher altitudes. Specifies at what fraction of the maximum take-off weight do various constraints have to be met. It should contain the following keys: take-off , climb , cruise , turn , servceil. Optional, each defaults to 1. Propeller efficiency in various phases of the mission. Optional, unspecified entries in the dictionary default to the following values:.

Atmosphere class object. Specifies the virtual atmosphere in which all the design calculations within the AircraftConcept class will be performed. Optional, defaults to the International Standard Atmosphere. Contains at maximum two objects of the ADRpy propulsion module, specifying the nature of the aircraft propulsion system.

Optional, defaults to methods 2 and 4. Optional, defaults to 0. Optional, provided that an aircraft weight and wing area are specified in the design definitions dictionary. Optional, defaults to cl at cruise. Several methods for calculating supersonic and subsonic lift-slopes are aggregated to produce a model for the lift curve with changing free-stream Mach number.

Care must be used when interpreting this function in the transonic flight regime. Before going any further, we need to establish the difference between drag and lift. Lift and drag coefficients, which are used to describe how easily the flow goes around the shape, are proportional to the angle of attack.

Another important phenomenon is the impact of velocities close to the speed of sound on the drag and lift coefficient. As the plane gets closer to the speed of sound, turbulences start to appear on the wing and impact drag and lift. M, the Mach number represents the ratio of the velocity over the speed of sound. We will, once more, approximate this relation :. The reference surfaces , needed to compute drag and lift, are the surfaces orthogonal to the direction of the force we are interested in.

For drag the reference surface is the one opposed to the relative wind, whereas for lift the reference surface is the one parallel to the relative wind. The surfaces we are interested in are the one relative to the relative wind. It is obtained by rotating our initial frame of reference by the value of the slope. During takeoff and landing, planes use flaps to increase the amount of lift at the expense of increased drag and therefore shorten the take-off and landing distance.

The take-off distance is defined as the distance between the starting point on the runway and the point at which the plane reaches 25m of altitude above the runway. We will define the take-off angle as the pitch angle between the ground and the plane to be used once the plane has reached its take-off speed.

Here are the take-off distances of our plane with no flaps We will only be plotting the values of take-off distances inferior to 5km, i. The take-off distance for an A is supposed to be around 2km.

At that point the plane is not generating enough lift, so we need to use flaps. With flaps out, we get the following take-off distances, much closer to a real A Now that we have the basic formulas for weight, thrust, lift, and drag, we need to talk about the impact of their orientations.

We thus get the equations to solve in order to get the sum of forces on the x and z-axis. To finish our model, we need to make it able to prevent the plane from going through the ground and to detect collisions. These collisions are prevented by setting back to 0 any negative vertical positions as well as setting the velocity back to 0 as well for those situations.

To account for future crash detections, if the plane is to have a negative vertical position while also having a negative vertical velocity before being set back to 0 , we will compute the kinetic energy of the plane that will be used to check if colliding with the ground leads to a crash. Otherwise, it will be considered as a safe landing. This feature will be used later for the reinforcement learning part. For fuel consumption, we will be using a simple model based on thrust-specific fuel consumption SFC which links thrust and time to fuel consumption.

To simplify the problem, we will always assume the cruise level SFC and neglect the sea-level SFC since we will spend most of our time at cruise level. To estimate SFC, we will assume that the relation between sea-level thrust the maximal available thrust for the reactor and cruise SFC is linear.

With this assumption, we can estimate the parameters of the relation between thrust and SFC based on the figures for the A engines, and we get an SFC of As a consequence of fuel consumption, the mass of the plane will vary, we will take this variation into account for the dynamics. In order to check our simulation, we will analyze and compare the results of our simulation of an A to reality. On these 3 graphs, we can see the evolution over time of acceleration, velocity, and position during the take-off phase.

The phenomenon can be seen in similar ways for velocity, where vertical speed starts going up at 25s and the increase rate of horizontal speed horizontal acceleration lowers. Additionally, we can also notice that the acceleration values stay well under displeasing values reaching a max of 0. We want to assess that our plane does not exceed speeds dangerous for its structural integrity getting too close to Mach 1 creates important turbulences and stress on the structure of the plane.

In order to measure the max speed our aircraft can reach, we will set the thrust to its maximum value and observe the speed at which the plane stabilizes. It is, however, higher than the max speed of a real A of Mach 0.

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