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Unit i basic concept of isentropic flow

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This document discusses compressible flow through variable area ducts. Part A covers fundamentals of compressible flow including concepts like Mach number. Part B focuses on isentropic flow through nozzles and diffusers. The conservation equations for mass, momentum and energy are applied to one-dimensional, steady, inviscid flow. For frictional flow in a constant area duct, the shear stress term is included. The resulting differential equations are solved for a perfect gas.

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ME 6604 - GAS DYNAMICS AND JET PROPULSION UNIT – I BASIC CONCEPTS AND FUNDAMENTALS OF COMPRESSIBLE FLOW B.PRABHU ASSISTANT PROFESSOR DEPT OF MECHANICAL ENGG KAMARAJ COLLEGE OF ENGINEERING
PART - A • FUNDAMENTALS OF COMPRESSIBLE FLOW • Energy and momentum equations for compressible fluid flows, various regions of flows, reference velocities, stagnation state, velocity of sound, critical states, Mach number, critical Mach number, types of waves, Mach cone, Mach angle, effect of Mach number on compressibility.
• PART – B • Flow through variable area duct • Isentropic flow through variable area ducts, T-s and h-s diagrams for nozzle and diffuser flows, area ratio as a function of Mach number, mass flow rate through nozzles and diffusers, effect of friction in flow through nozzles
FLOW THROUGH VARIABLE AREA DUCTS
FLOW THROUGH VARIABLE AREA DUCTS • As a gas is forced through a tube, the gas molecules are deflected by the walls of the tube. If the speed of the gas is much less than the speed of sound of the gas, the density of the gas remains constant and the velocity of the flow increases. However, as the speed of the flow approaches the speed of sound we must consider compressibility effects on the gas. The density of the gas varies from one location to the next. Considering flow through a tube, as shown in the figure, if the flow is very gradually compressed (area decreases) and then gradually expanded (area increases), the flow conditions return to their original values. We say that such a process is reversible. From a consideration of the second law of thermodynamics, a reversible flow maintains a constant value of entropy. Engineers call this type of flow an isentropicflow; a combination of the Greek word "iso" (same) and entropy.
FLOW THROUGH VARIABLE AREA DUCTS
FLOW THROUGH VARIABLE AREA DUCTS • The conservation of mass is a fundamental concept of physics. Within some problem domain, the amount of mass remains constant; mass is neither created or destroyed. The mass of any object is simply the volume that the object occupies times the density of the object. For a fluid (a liquid or a gas) the density, volume, and shape of the object can all change within the domain with time and mass can move through the domain. • The conservation of mass (continuity) tells us that the mass flow rate mdot through a tube is a constant and equal to the product of the density r, velocity V, and flow area A:
Conservation of mass
Conservation of mass • Solid Mechanics • The conservation of mass is a fundamental concept of physics along with the conservation of energy and theconservation of momentum. Within some problem domain, the amount of mass remains constant--mass is neither created nor destroyed. This seems quite obvious, as long as we are not talking about black holes or very exotic physics problems. The mass of any object can be determined by multiplying the volume of the object by the density of the object. When we move a solid object, as shown at the top of the slide, the object retains its shape, density, and volume. The mass of the object, therefore, remains a constant between state "a" and state "b." • Fluid Statics • In the center of the figure, we consider an amount of a static fluid , liquid or gas. If we change the fluid from some state "a" to another state "b" and allow it to come to rest, we find that, unlike a solid, a fluid may change its shape. The amount of fluid, however, remains the same. We can calculate the amount of fluid by multiplying the density times the volume. Since the mass remains constant, the product of the density and volume also remains constant. (If the density remains constant, the volume also remains constant.) The shape can change, but the mass remains the same. • Fluid Dynamics • Finally, at the bottom of the slide, we consider the changes for a fluid that is moving through our domain. There is no accumulation or depletion of mass, so mass is conserved within the domain. Since the fluid is moving, defining the amount of mass gets a little tricky. Let's consider an amount of fluid that passes through point "a" of our domain in some amount of time t. If the fluid passes through an area A at velocity V, we can define the volume Vol to be: • Vol = A * V * t
Conservation Laws for a Real Fluid   0.    V t        wqVe t e        .     gVV t V ij ˆ..        iiij pij  '      gpVV t V ij ˆ.. '       
Conservation of Mass Applied to 1 D Steady Flow   0.    V t    Conservation of Mass: Conservation of Mass for Stead Flow:   0.  V   Integrate from inlet to exit :   onstant. CVdV V   
One Dimensional Stead Flow A, V  A+dA, V+dV d dl   onstant.. CdxdAV V      onstant. Cdx dx VAd     0VAd  0 A dA V dVd  
Conservation of Momentum For A Real Fluid Flow   pVV ij  ' ..     VdpVdVdVV VVV ij   ' ..   No body forces One Dimensional Steady flow A, V  A+dA, V+dV d dl
  dAdxpdxdAdAdxVV V w VV ij   ' .        dx dx pAd dx dx Ad dx dx AVd ww    2      pAdAdAVd ww   2
Conservation of Energy Applied to 1 D Steady Flow     wqVe t e        . Steady flow with negligible Body Forces and no heat transfer is adiabatic real flow   wVe    . For a real fluid the rate of work transfer is due to viscous stress and pressure. Neglecting the the effect of viscous dissipation.   VdAnpVe  .ˆ.  
For a total change from inlet to exit :     AV VdAnpVdVe  .ˆ.  Using gauss divergence theorem: One dimensional flow     VV VdVpVdVe  ..      VV dAdxVpdAdxVe  .. 
      dx dx pAVd dx dx eVAd     pAVdeVAd  2 2 V ue                               AV p d V uVAd   2 2 0 2 2                        Vp uVAd   0 2 2                V hVAd 
Summary of Real Fluid Analysis 0 A dA V dVd        pAdAdAVd ww   2 0 2 2                V hVAd 
Further Analysis of Momentum equation      pAdAdVAdVVAVd ww      pAdAdVAdV ww      pAdPxddVm w      pAdAddVm ww   pdAAdpPdxxdPPxddVm www  
Frictional Flow in A Constant Area Duct 0 V dVd   AdpPdxPxddVm ww   0 2 2                V hVd 
Frictional Flow in A Constant Area Duct AdpPdxdVm w   w The shear stress is defined as and average viscous stress which is always opposite to the direction of flow for the entire length dx. AdpPdxPxddVm ww   AdpPdxAVdV w  
AdpPdxAVdV w   Divide by AV2 22 V dp dx A P VV dV w    0 V dVd   00 2 2        VdVdTC V hd p
One dimensional Frictional Flow of A Perfect Gas 0 V dVd   0VdVdTCp 2 V dp dx A P f V dV   T dT V dV p dp T dTd p dp   
Sonic Equation 2 22 2 2 2 2 2 RT dTV RT VdV MdM RT V c V M   Differential form of above equation: T dT V dV M dM 2  T dT V dV p dp  T dT M dM p dp 2 
    M dM M M T dT               2 2 2 1 1 1   Energy equation can be modified as: T dT M dM p dp 2      M dM M M M dM p dp               2 2 2 1 1 1 2 1  
1D steady real flow through constant area duct : momentum equation 022  V dp dx A P VV dV w   022  p dp V p dx A P VV dV w   022  p dp V p dx A P VV dV w  
022  p dp V p dx A P VV dV w     022  p dp V p dx A P VV dV w     0 1 22  p dp M dx A P VV dV w  
0 1 22  p dp M dx A P VV dV w       M dM M M T dT               2 2 2 1 1 1       M dM M M M dM p dp               2 2 2 1 1 1 2 1   T dT V dV M dM 2  Differential Equations for Frictional Flow Through Constant Area Duct T dT M dM p dp 2 
0 1 22  p dp M dx A P VT dT M dM w           0 2 1 1 1 2 11 2 1 1 1 2 2 22 2 2                                          M dM M M M dM M dx A P VM dM M M M dM w                     dx A P VM MM M dM w 22 22 1 2 1 1    
            dx A P VM M T dT w 22 4 1 1               dx A P VM MM p dp w 22 22 1 11                 dx A P VM MM M dM w 22 22 1 2 1 1    
Second Law Analysis vdpdTCTds p  dp T v T dT Cds p  p dp R T dT Cds p 
p dp R T dT Cds p  p dp T dT C ds p   1           2 1 1 V TC T dT T dT C ds p p              TT T T dT T dT C ds p 02 1 1  
TT dT T dT C ds p    02 11        T T T T s s p iii TT dT T dT C ds 02 11                                  2 1 0 0 /1 ln iip i TT TT T T C ss             dx A P VM M T dT w 22 4 1 1  
Fanno Line Adiabatic flow in a constant area with friction is termed as Fanno flow.
Isentropic Nozzle and Adiabatic Duct
C Nozzle Discharge Curve
CD Nozzle + Discharge Curve
Nature of Real Flow Entropy of an irreversible adiabatic system should always increase!          dx A P V MCds w p 2 2 1                  dx A P VM MM M dM w 22 22 1 2 1 1                 dx A P VM M T dT w 22 4 1 1               dx A P VM MM p dp w 22 22 1 11  
M dM dp dT dV <1 +ve -ve -ve +ve >1 -ve +ve +ve -ve
Compressible Real Flow ),(Re, M d k functionf  Effect of Mach number is negligible…. )(Re, d k functionf   1 Re  n T T        2 1 2 1  
Pressure drop in Compressible Flow Laminar Flow Turbulent Flows               22 2 2 1 1 1 MM M M dM dx A P f   Re 16 f 2 9.0 Re 74.5 7.3 log 0625.0               hD k f
Moody Chart
Compressible Flow Through Finite Length Duct Integrate over a length l               22 2 2 1 1 14 MM M M dM D fdx h   M dM MM M D fdx e i M M l h          22 2 0 2 1 1 14  
              22 2 2 1 1 14 MM M M dM D fdx h                                       22 22 22 2 1 1 2 1 1 ln 2 11114 ie ei eih MM MM MM l D f      is a Mean friction factor over a length l . f
Maximum Allowable Length • The length of the duct required to give a Mach number of 1 with an initial Mach number Mi Similarly                                     2 2 2max 2 1 1 1 2 1 1 ln 2 1 1 114 i i ih M M M l D f                          1 2 2 * 2 1 1 2 1 1 * iM p p M dM M M p dp p p  
                  1 2 2 2 1 1 1 * ii M T T M dM M M T dT   2/1 2 * 2 1 1 2 1 1               i i MMp p                 2 * 2 1 1 2 1 iMT T   2 5.1 5 . 111 1.384 293 103.3 m sN T T         
 1/ 2 2 1 1            i o M p p * 0 * 0 * 0 0 p p p p p p    1 2 ** 0 0 2 1 2 1 1                    iM p p p p    12 2 * 0 0 2 1 2 1 1 1                    i i M Mp p
Compressible Frictional Flow through Constant Area Duct HD fL *4 0 * 0 p p p p* T T* V V * M
Frictional Flow in A Variable Area Duct 0 A dA V dVd   A, V  A+dA, V+dV d
0 4 2 2 2  V dV Mdx D fM p dp h   T dTd p dp    0 A dA V dVd   A dA V dV T dT p dp 
0 4 2 2 2  V dV Mdx D fM A dA V dV T dT h   T dT M dM V dV T dT V dV M dM 22  0 2 4 22 2 2                T dT M dM Mdx D fM A dA T dT M dM T dT h       M dM M M T dT               2 2 2 1 1 1  
0 4 2 2 1 1 1 2 2 2      dx D fM M dM M M A dA h   dx D fM M M A dA M M M dM h 4 21 2 1 1 1 2 1 1 2 2 2 2 2                               Constant Mach number frictional flow hD fM dx dA 2 2 
  dx D fM M A dA M M dM M h 4 22 1 1 2 1 11 2 222                  Sonic Point : M=1 0 4 22 1 1 2 1 1                  dx D f A dA h  0 4 22 1 2 1                  dx D f A dA h  dx D f A dA h 4 2  
54 Stagnation Properties Consider a fluid flowing into a diffuser at a velocity , temperature T, pressure P, and enthalpy h, etc. Here the ordinary properties T, P, h, etc. are called the static properties; that is, they are measured relative to the flow at the flow velocity. The diffuser is sufficiently long and the exit area is sufficiently large that the fluid is brought to rest (zero velocity) at the diffuser exit while no work or heat transfer is done. The resulting state is called the stagnation state.  V We apply the first law per unit mass for one entrance, one exit, and neglect the potential energies. Let the inlet state be unsubscripted and the exit or stagnation state have the subscript o. q h V w h V net net o o       2 2 2 2
55 Since the exit velocity, work, and heat transfer are zero, h h V o   2 2 The term ho is called the stagnation enthalpy (some authors call this the total enthalpy). It is the enthalpy the fluid attains when brought to rest adiabatically while no work is done. If, in addition, the process is also reversible, the process is isentropic, and the inlet and exit entropies are equal. s so  The stagnation enthalpy and entropy define the stagnation state and the isentropic stagnation pressure, Po. The actual stagnation pressure for irreversible flows will be somewhat less than the isentropic stagnation pressure as shown below.
56

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Unit i basic concept of isentropic flow

  • 1. ME 6604 - GAS DYNAMICS AND JET PROPULSION UNIT – I BASIC CONCEPTS AND FUNDAMENTALS OF COMPRESSIBLE FLOW B.PRABHU ASSISTANT PROFESSOR DEPT OF MECHANICAL ENGG KAMARAJ COLLEGE OF ENGINEERING
  • 2. PART - A • FUNDAMENTALS OF COMPRESSIBLE FLOW • Energy and momentum equations for compressible fluid flows, various regions of flows, reference velocities, stagnation state, velocity of sound, critical states, Mach number, critical Mach number, types of waves, Mach cone, Mach angle, effect of Mach number on compressibility.
  • 3. • PART – B • Flow through variable area duct • Isentropic flow through variable area ducts, T-s and h-s diagrams for nozzle and diffuser flows, area ratio as a function of Mach number, mass flow rate through nozzles and diffusers, effect of friction in flow through nozzles
  • 5. FLOW THROUGH VARIABLE AREA DUCTS • As a gas is forced through a tube, the gas molecules are deflected by the walls of the tube. If the speed of the gas is much less than the speed of sound of the gas, the density of the gas remains constant and the velocity of the flow increases. However, as the speed of the flow approaches the speed of sound we must consider compressibility effects on the gas. The density of the gas varies from one location to the next. Considering flow through a tube, as shown in the figure, if the flow is very gradually compressed (area decreases) and then gradually expanded (area increases), the flow conditions return to their original values. We say that such a process is reversible. From a consideration of the second law of thermodynamics, a reversible flow maintains a constant value of entropy. Engineers call this type of flow an isentropicflow; a combination of the Greek word "iso" (same) and entropy.
  • 7. FLOW THROUGH VARIABLE AREA DUCTS • The conservation of mass is a fundamental concept of physics. Within some problem domain, the amount of mass remains constant; mass is neither created or destroyed. The mass of any object is simply the volume that the object occupies times the density of the object. For a fluid (a liquid or a gas) the density, volume, and shape of the object can all change within the domain with time and mass can move through the domain. • The conservation of mass (continuity) tells us that the mass flow rate mdot through a tube is a constant and equal to the product of the density r, velocity V, and flow area A:
  • 9. Conservation of mass • Solid Mechanics • The conservation of mass is a fundamental concept of physics along with the conservation of energy and theconservation of momentum. Within some problem domain, the amount of mass remains constant--mass is neither created nor destroyed. This seems quite obvious, as long as we are not talking about black holes or very exotic physics problems. The mass of any object can be determined by multiplying the volume of the object by the density of the object. When we move a solid object, as shown at the top of the slide, the object retains its shape, density, and volume. The mass of the object, therefore, remains a constant between state "a" and state "b." • Fluid Statics • In the center of the figure, we consider an amount of a static fluid , liquid or gas. If we change the fluid from some state "a" to another state "b" and allow it to come to rest, we find that, unlike a solid, a fluid may change its shape. The amount of fluid, however, remains the same. We can calculate the amount of fluid by multiplying the density times the volume. Since the mass remains constant, the product of the density and volume also remains constant. (If the density remains constant, the volume also remains constant.) The shape can change, but the mass remains the same. • Fluid Dynamics • Finally, at the bottom of the slide, we consider the changes for a fluid that is moving through our domain. There is no accumulation or depletion of mass, so mass is conserved within the domain. Since the fluid is moving, defining the amount of mass gets a little tricky. Let's consider an amount of fluid that passes through point "a" of our domain in some amount of time t. If the fluid passes through an area A at velocity V, we can define the volume Vol to be: • Vol = A * V * t
  • 10. Conservation Laws for a Real Fluid   0.    V t        wqVe t e        .     gVV t V ij ˆ..        iiij pij  '      gpVV t V ij ˆ.. '       
  • 11. Conservation of Mass Applied to 1 D Steady Flow   0.    V t    Conservation of Mass: Conservation of Mass for Stead Flow:   0.  V   Integrate from inlet to exit :   onstant. CVdV V   
  • 12. One Dimensional Stead Flow A, V  A+dA, V+dV d dl   onstant.. CdxdAV V      onstant. Cdx dx VAd     0VAd  0 A dA V dVd  
  • 13. Conservation of Momentum For A Real Fluid Flow   pVV ij  ' ..     VdpVdVdVV VVV ij   ' ..   No body forces One Dimensional Steady flow A, V  A+dA, V+dV d dl
  • 14.   dAdxpdxdAdAdxVV V w VV ij   ' .        dx dx pAd dx dx Ad dx dx AVd ww    2      pAdAdAVd ww   2
  • 15. Conservation of Energy Applied to 1 D Steady Flow     wqVe t e        . Steady flow with negligible Body Forces and no heat transfer is adiabatic real flow   wVe    . For a real fluid the rate of work transfer is due to viscous stress and pressure. Neglecting the the effect of viscous dissipation.   VdAnpVe  .ˆ.  
  • 16. For a total change from inlet to exit :     AV VdAnpVdVe  .ˆ.  Using gauss divergence theorem: One dimensional flow     VV VdVpVdVe  ..      VV dAdxVpdAdxVe  .. 
  • 17.       dx dx pAVd dx dx eVAd     pAVdeVAd  2 2 V ue                               AV p d V uVAd   2 2 0 2 2                        Vp uVAd   0 2 2                V hVAd 
  • 18. Summary of Real Fluid Analysis 0 A dA V dVd        pAdAdAVd ww   2 0 2 2                V hVAd 
  • 19. Further Analysis of Momentum equation      pAdAdVAdVVAVd ww      pAdAdVAdV ww      pAdPxddVm w      pAdAddVm ww   pdAAdpPdxxdPPxddVm www  
  • 20. Frictional Flow in A Constant Area Duct 0 V dVd   AdpPdxPxddVm ww   0 2 2                V hVd 
  • 21. Frictional Flow in A Constant Area Duct AdpPdxdVm w   w The shear stress is defined as and average viscous stress which is always opposite to the direction of flow for the entire length dx. AdpPdxPxddVm ww   AdpPdxAVdV w  
  • 22. AdpPdxAVdV w   Divide by AV2 22 V dp dx A P VV dV w    0 V dVd   00 2 2        VdVdTC V hd p
  • 23. One dimensional Frictional Flow of A Perfect Gas 0 V dVd   0VdVdTCp 2 V dp dx A P f V dV   T dT V dV p dp T dTd p dp   
  • 24. Sonic Equation 2 22 2 2 2 2 2 RT dTV RT VdV MdM RT V c V M   Differential form of above equation: T dT V dV M dM 2  T dT V dV p dp  T dT M dM p dp 2 
  • 25.     M dM M M T dT               2 2 2 1 1 1   Energy equation can be modified as: T dT M dM p dp 2      M dM M M M dM p dp               2 2 2 1 1 1 2 1  
  • 26. 1D steady real flow through constant area duct : momentum equation 022  V dp dx A P VV dV w   022  p dp V p dx A P VV dV w   022  p dp V p dx A P VV dV w  
  • 28. 0 1 22  p dp M dx A P VV dV w       M dM M M T dT               2 2 2 1 1 1       M dM M M M dM p dp               2 2 2 1 1 1 2 1   T dT V dV M dM 2  Differential Equations for Frictional Flow Through Constant Area Duct T dT M dM p dp 2 
  • 29. 0 1 22  p dp M dx A P VT dT M dM w           0 2 1 1 1 2 11 2 1 1 1 2 2 22 2 2                                          M dM M M M dM M dx A P VM dM M M M dM w                     dx A P VM MM M dM w 22 22 1 2 1 1    
  • 30.             dx A P VM M T dT w 22 4 1 1               dx A P VM MM p dp w 22 22 1 11                 dx A P VM MM M dM w 22 22 1 2 1 1    
  • 31. Second Law Analysis vdpdTCTds p  dp T v T dT Cds p  p dp R T dT Cds p 
  • 32. p dp R T dT Cds p  p dp T dT C ds p   1           2 1 1 V TC T dT T dT C ds p p              TT T T dT T dT C ds p 02 1 1  
  • 33. TT dT T dT C ds p    02 11        T T T T s s p iii TT dT T dT C ds 02 11                                  2 1 0 0 /1 ln iip i TT TT T T C ss             dx A P VM M T dT w 22 4 1 1  
  • 34. Fanno Line Adiabatic flow in a constant area with friction is termed as Fanno flow.
  • 35. Isentropic Nozzle and Adiabatic Duct
  • 37. CD Nozzle + Discharge Curve
  • 38. Nature of Real Flow Entropy of an irreversible adiabatic system should always increase!          dx A P V MCds w p 2 2 1                  dx A P VM MM M dM w 22 22 1 2 1 1                 dx A P VM M T dT w 22 4 1 1               dx A P VM MM p dp w 22 22 1 11  
  • 39. M dM dp dT dV <1 +ve -ve -ve +ve >1 -ve +ve +ve -ve
  • 40. Compressible Real Flow ),(Re, M d k functionf  Effect of Mach number is negligible…. )(Re, d k functionf   1 Re  n T T        2 1 2 1  
  • 41. Pressure drop in Compressible Flow Laminar Flow Turbulent Flows               22 2 2 1 1 1 MM M M dM dx A P f   Re 16 f 2 9.0 Re 74.5 7.3 log 0625.0               hD k f
  • 43. Compressible Flow Through Finite Length Duct Integrate over a length l               22 2 2 1 1 14 MM M M dM D fdx h   M dM MM M D fdx e i M M l h          22 2 0 2 1 1 14  
  • 44.               22 2 2 1 1 14 MM M M dM D fdx h                                       22 22 22 2 1 1 2 1 1 ln 2 11114 ie ei eih MM MM MM l D f      is a Mean friction factor over a length l . f
  • 45. Maximum Allowable Length • The length of the duct required to give a Mach number of 1 with an initial Mach number Mi Similarly                                     2 2 2max 2 1 1 1 2 1 1 ln 2 1 1 114 i i ih M M M l D f                          1 2 2 * 2 1 1 2 1 1 * iM p p M dM M M p dp p p  
  • 46.                   1 2 2 2 1 1 1 * ii M T T M dM M M T dT   2/1 2 * 2 1 1 2 1 1               i i MMp p                 2 * 2 1 1 2 1 iMT T   2 5.1 5 . 111 1.384 293 103.3 m sN T T         
  • 47.  1/ 2 2 1 1            i o M p p * 0 * 0 * 0 0 p p p p p p    1 2 ** 0 0 2 1 2 1 1                    iM p p p p    12 2 * 0 0 2 1 2 1 1 1                    i i M Mp p
  • 48. Compressible Frictional Flow through Constant Area Duct HD fL *4 0 * 0 p p p p* T T* V V * M
  • 49. Frictional Flow in A Variable Area Duct 0 A dA V dVd   A, V  A+dA, V+dV d
  • 52. 0 4 2 2 1 1 1 2 2 2      dx D fM M dM M M A dA h   dx D fM M M A dA M M M dM h 4 21 2 1 1 1 2 1 1 2 2 2 2 2                               Constant Mach number frictional flow hD fM dx dA 2 2 
  • 53.   dx D fM M A dA M M dM M h 4 22 1 1 2 1 11 2 222                  Sonic Point : M=1 0 4 22 1 1 2 1 1                  dx D f A dA h  0 4 22 1 2 1                  dx D f A dA h  dx D f A dA h 4 2  
  • 54. 54 Stagnation Properties Consider a fluid flowing into a diffuser at a velocity , temperature T, pressure P, and enthalpy h, etc. Here the ordinary properties T, P, h, etc. are called the static properties; that is, they are measured relative to the flow at the flow velocity. The diffuser is sufficiently long and the exit area is sufficiently large that the fluid is brought to rest (zero velocity) at the diffuser exit while no work or heat transfer is done. The resulting state is called the stagnation state.  V We apply the first law per unit mass for one entrance, one exit, and neglect the potential energies. Let the inlet state be unsubscripted and the exit or stagnation state have the subscript o. q h V w h V net net o o       2 2 2 2
  • 55. 55 Since the exit velocity, work, and heat transfer are zero, h h V o   2 2 The term ho is called the stagnation enthalpy (some authors call this the total enthalpy). It is the enthalpy the fluid attains when brought to rest adiabatically while no work is done. If, in addition, the process is also reversible, the process is isentropic, and the inlet and exit entropies are equal. s so  The stagnation enthalpy and entropy define the stagnation state and the isentropic stagnation pressure, Po. The actual stagnation pressure for irreversible flows will be somewhat less than the isentropic stagnation pressure as shown below.
  • 56. 56