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Verifica motori (II)

Pubblicato da Giuliano Deledda in data maggio 16, 2016

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Verifiche 2015/2016

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Etichette

Amelia Earhart
Bibliografia
Centraggio
CLIL
Cruising performances
DataBank-Quesiti
Decollo
Diagramma di manovra
Endoreattori
Esercitazioni

Esercizi
Esercizi IV
Esercizi V
Gliding flight
Moduli
Programmi A.S 2014/2015
Programmi A.S 2015/2016
Python
Regime supersonico
Ripasso
Salita
Simulatori di volo
Stabilità
Temi d'esame
Turning Flight
Verifiche
Verifiche 2015/2016
Videoteca

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Unpowered flight II

Unpowered flight Unpowered flight occurs when: A single-engine aircraft has engine failure or runs out of fuel; A multiengine aircraft runs out of fuel; An aircraft has no propulsion system (a glider or a sailplane). The forces acting on an airplane in a power-off glide are lift, drag, and weight: the thrust is zero because the power is off. The glide flight path makes an angle gamma (γ) below the horizontal. For an equilibrium unaccelerated glide the sum of the forces must be zero. The weight can be divided into two components: W ⋅ sin(γ) acting in a forward direction; W ⋅ cos (γ) acting downward at right angles to the descent path. The weight component along the flight path must balance drag and the weight component perpendicular to the flight path must balance lift. Forces in the glide The equations of motion for unpowered flight are: An expression for the glide angle can be recovered from equations of motion by division: The glide angle is a ...

Esercizio V 01

Glide ratio In the figure below you see the hypothetical lift-drag polar of an aircraft For this aircraft, determine the maximum glide ratio. Answer From the lecture on drag you should know that the maximum glide ratio (or the maximum lift over drag ratio) can be determined from such as diagram by drawing the steepest tangent to the curve (from the origin). See the figure below. The point where this tangent touches the lift-drag polar corresponds to the flight condition with the maximum glide ratio. We see that at the specified point the lift coefficient is roughly 0.4, while the drag coefficient is approximately 0.03. Dividing the two, we get E =13.3. Aircraft drag Suppose that the lift-drag polar of the previous problem belongs to a 32,000 kilogram aircraft with an average wing chord of 3.5 metres and a wingspan of 30 metres. At a certain moment this aircraft flies in cruise at a speed of 300 ft/s, with an air density of 1.0 kilogram per cubic metre. For this fli...

Volo librato (I)

Esercitazione Tracciare la polare aerodinamica, la curva odografa relativamente ad un aliante del quale sono note le seguenti caratteristiche: Massa: 530 kg; Superficie alare: 12 m^2; CD0: 0.00715; k: 0.0112. Nello stesso diagramma indicare il punto di lavoro sulle due curve e la traiettoria di planata nel caso in cui: Caso A: CL= 0.3 Caso B: CL= 0.4 Caso C: CL= 0.5 Caso D: CL= 0.6 Caso E: CL= 0.9 Caso F: CL= 1.0 Caso G: CL= 1.2 Caso F: CL= 1.3 Esempio di curva odografa. N.B. Il grafico riporta solamente la scala dei coefficienti aerodinamici mentre la scala dell'odografa è stata normalizzata in modo da risultare tangente alla prima nel punto di efficienza massima. Script Scilab (C)

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