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Isentropic Flow.

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Presentation on theme: "Isentropic Flow."— Presentation transcript:

1 Isentropic Flow

2 Examples of Isentropic Flow
Air foil flow Diffusers Actually there is no isentropic flow but it is assumption for ideal case of flow Most flows are real flow

3 Definition of Isentropic Flow
There are Five thermo dynamics process 1- Constant pressure process 𝑃 𝑉 0 =𝑐𝑜𝑛𝑠. 2- Constant Volume Process 𝑃 𝑉 ∞ =𝑐𝑜𝑛𝑠. 3- Constant Temperature Process 𝑃 𝑉 1 =𝑐𝑜𝑛𝑠 4- Constant entropy 𝑃 𝑉 𝛾 =𝑐𝑜𝑛𝑠 5- The general process 𝑃 𝑉 𝑛 =𝑐𝑜𝑛𝑠 Isentropic flow : the flow which the properties of it at any location or any time could be estimated According to the isentropic process equation

4 ISENTROPIC Process Governing Equation
Goal: Relate Thermodynamics to Compressible Flow Adiabatic Process: No heat is added or removed from system dq = 0 Note: Temperature can still change because of changing density Reversible Process: No friction (or other dissipative effects) Isentropic Process: (1) Adiabatic + (2) Reversible (1) No heat exchange + (2) no frictional losses Relevant for compressible flows only Provides important relationships among thermodynamic variables at two different points along a streamline g = ratio of specific heats g = cp/cv gair=1.4

5 ENERGY EQUATION SUMMARY
Energy can neither be created nor destroyed; can only change physical form Same idea as 1st law of thermodynamics Energy equation for frictionless, adiabatic flow (isentropic) h = enthalpy = e+p/r = e+RT h = cpT for an ideal gas Also energy equation for frictionless, adiabatic flow Relates T and V at two different points along a streamline

6 SPEED OF SOUND Sound waves travel through air at a finite speed
Sound speed (information speed) has an important role in aerodynamics Combine conservation of mass, Euler’s equation and isentropic relations: Speed of sound, a, in a perfect gas depends only on temperature of gas Mach number = flow velocity normalizes by speed of sound If M < 1 flow is subsonic If M = 1 flow is sonic If M > flow is supersonic If M < 0.3 flow may be considered incompressible

7 GOVERNING EQUATIONS STEADY AND INVISCID FLOW
Incompressible flow of fluid along a streamline or in a stream tube of varying area Most important variables: p and V T and r are constants throughout flow continuity Bernoulli continuity Compressible, isentropic (adiabatic and frictionless) flow along a streamline or in a stream tube of varying area T, p, r, and V are all variables isentropic energy equation of state at any point

8 Derivation of Isentropic Flow Equations
Isentropic governing equation 𝑇 2 𝑇 1 = 𝑃 2 𝑃 𝛾−1 𝛾 = 𝜌 2 𝜌 1 𝛾−1 1 Speed of sound 𝑎 2 𝑎 = 𝛾𝑅𝑇 2 𝛾𝑅𝑇 1 𝑎= 𝛾𝑅𝑇 𝑎 2 =𝛾𝑅𝑇 2 By combining Eq 1 and Eq 2 𝑎 2 𝑎 = 𝑇 2 𝑇 1 = 𝑃 2 𝑃 𝛾−1 𝛾 = 𝜌 2 𝜌 1 𝛾−1 3

9 Applying energy equation
𝐶 𝑝 𝑇 𝑉 = 𝐶 𝑝 𝑇 𝑉 𝐶 𝑝 𝑇 𝑉 𝐶 𝑝 𝑇 1 = 𝐶 𝑝 𝑇 𝑉 𝐶 𝑝 𝑇 2 𝑇 2 𝑇 1 = 1+ 𝑉 𝐶 𝑝 𝑇 𝑉 𝐶 𝑝 𝑇 2 𝑉 2 𝛾𝑅𝑇 = 𝑉 𝛾𝑅𝑇 2 = 𝑀 2 𝑉 2 2 𝐶 𝑝 𝑇 = 𝑉 2 𝛾𝑅𝑇 𝛾𝑅 2𝐶 𝑝 𝑉 2 2 𝐶 𝑝 𝑇 = 𝑉 2 𝛾𝑅𝑇 𝛾𝑅 2𝐶 𝑝 = 𝛾−1 2 𝑀 2 𝛾𝑅 2𝐶 𝑝 = 𝛾−1 2

10 𝑇 2 𝑇 1 = 1+ 𝑉 𝐶 𝑝 𝑇 𝑉 𝐶 𝑝 𝑇 2 𝑉 2 2 𝐶 𝑝 𝑇 = 𝑉 2 2𝛾𝑅𝑇 𝛾𝑅 𝐶 𝑝 = 𝛾−1 2 𝑀 2 𝑇 2 𝑇 1 = 1+ 𝛾−1 2 𝑀 𝛾−1 2 𝑀 2 2

11 Isentropic process Equations
𝑇 2 𝑇 1 = 1+ 𝛾−1 2 𝑀 𝛾−1 2 𝑀 2 2 𝑃 1 𝑃 2 = 𝜌 1 𝜌 𝛾 = 𝑇 1 𝑇 𝛾 𝛾−1 𝑃 1 𝑃 2 = 1+ 𝛾−1 2 𝑀 𝛾−1 2 𝑀 𝛾 𝛾−1 𝑃 1 𝑃 2 = 𝜌 1 𝜌 𝛾 = 𝑇 1 𝑇 𝛾 𝛾−1 𝜌 1 𝜌 2 = 1+ 𝛾−1 2 𝑀 𝛾−1 2 𝑀 𝛾−1

12 Compressible flow Equation Referred to Stagnation Conditions
At stagnation condition the velocity is zero 𝑉 =0 𝑀 =0 ℎ 𝑜 =constant For Any two point on flow stream 𝜌 1 𝜌 2 = 1+ 𝛾−1 2 𝑀 𝛾−1 2 𝑀 𝛾−1 𝑇 2 𝑇 1 = 1+ 𝛾−1 2 𝑀 𝛾−1 2 𝑀 2 2 𝑃 1 𝑃 2 = 1+ 𝛾−1 2 𝑀 𝛾−1 2 𝑀 𝛾 𝛾−1 𝑃 𝑜 𝑃 1 = 1+ 𝛾−1 2 𝑀 𝛾 𝛾−1 𝜌 𝑜 𝜌 1 = 1+ 𝛾−1 2 𝑀 𝛾−1 𝑇 𝑜 𝑇 1 =1+ 𝛾−1 2 𝑀 1 2 For any point on flow stream and stagnation point

13 Compressible flow Equation Referred to Critical Conditions
At critical conditions the velocity is equal to speed of sound 𝑉 =a 𝑀 ∗ =1 For Any two point on flow stream 𝜌 1 𝜌 2 = 1+ 𝛾−1 2 𝑀 𝛾−1 2 𝑀 𝛾−1 𝑇 2 𝑇 1 = 1+ 𝛾−1 2 𝑀 𝛾−1 2 𝑀 2 2 𝑃 1 𝑃 2 = 1+ 𝛾−1 2 𝑀 𝛾−1 2 𝑀 𝛾 𝛾−1 𝑃 𝑜 𝑃 1 = 1+ 𝛾−1 2 𝑀 𝛾 𝛾−1 𝜌 𝑜 𝜌 1 = 1+ 𝛾−1 2 𝑀 𝛾−1 𝑇 𝑜 𝑇 1 =1+ 𝛾−1 2 𝑀 1 2 𝑃 𝑜 𝑃 ∗ = 1+ 𝛾− 𝛾 𝛾−1 𝜌 𝑜 𝜌 ∗ = 1+ 𝛾− 𝛾−1 𝑇 𝑜 𝑇 ∗ =1+ 𝛾− 𝑃 𝑜 𝑃 ∗ = 𝛾 𝛾 𝛾−1 𝑇 𝑜 𝑇 ∗ = 𝛾+1 2 𝜌 𝑜 𝜌 ∗ = 𝛾 𝛾−1 For critical point of flow stream and stagnation point


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