Restriction in flow area in moist air network
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The Local Restriction (MA) block models the pressure drop due to a localized reduction in flow area, such as a valve or an orifice, in a moist air network. Choking occurs when the restriction reaches the sonic condition.
Ports A and B represent the restriction inlet and outlet. The input physical signal at port AR specifies the restriction area. Alternatively, you can specify a fixed restriction area as a block parameter.
The block icon changes depending on the value of the Restriction type parameter.
Restriction Type  Block Icon 





The restriction is adiabatic. It does not exchange heat with the environment.
The restriction consists of a contraction followed by a sudden expansion in flow area. The moist air accelerates during the contraction, causing the pressure to drop. The moist air separates from the wall during the sudden expansion, causing the pressure to recover only partially due to the loss of momentum.
Local Restriction Schematic
Caution
Moist air flow through this block can choke. If a Mass Flow Rate Source (MA) block or a Controlled Mass Flow Rate Source (MA) block connected to the Local Restriction (MA) block specifies a greater mass flow rate than the possible choked mass flow rate, the simulation generates an error. For more information, see Choked Flow.
The block equations use these symbols.
$$\dot{m}$$  Mass flow rate 
Φ  Energy flow rate 
p  Pressure 
ρ  Density 
R  Specific gas constant 
S  Crosssectional area 
C_{d}  Discharge coefficient 
h  Specific enthalpy 
c_{p}  Specific heat at constant pressure 
T  Temperature 
Subscripts a
, w
, and g
indicate the properties of dry air, water vapor, and trace gas, respectively. Subscripts
lam
and tur
indicate the laminar and turbulent
regime, respectively. Subscripts A
and B
indicate
the appropriate port. Subscript R
indicates the restriction.
Mass balance:
$$\begin{array}{l}{\dot{m}}_{A}+{\dot{m}}_{B}=0\\ {\dot{m}}_{wA}+{\dot{m}}_{wB}=0\\ {\dot{m}}_{gA}+{\dot{m}}_{gB}=0\end{array}$$
Energy balance:
$${\Phi}_{A}+{\Phi}_{B}=0$$
When the flow is not choked, the mixture mass flow rate (positive from port A to port B) in the turbulent regime is
$$\begin{array}{l}{\dot{m}}_{tur}={C}_{d}{S}_{R}\left({p}_{A}{p}_{B}\right)\sqrt{\frac{2{\rho}_{R}}{\left{p}_{A}{p}_{B}\right{K}_{tur}}}\\ {K}_{tur}=\left(1+\frac{{S}_{R}}{S}\right)\left(1\frac{{\rho}_{R}}{{\rho}_{in}}\frac{{S}_{R}}{S}\right)2\frac{{S}_{R}}{S}\left(1\frac{{\rho}_{R}}{{\rho}_{out}}\frac{{S}_{R}}{S}\right)\end{array}$$
Subscripts in
and out
indicate the inlet and
outlet, respectively. If p_{A} ≥
p_{B}, the inlet is port
A and the outlet is port B; otherwise,
they are reversed. The crosssectional area S is assumed to be equal
at ports A and B.
S_{R} is the area at the restriction.
The mixture mass flow rate equation is derived by combining the equations from two control volume analyses:
Momentum balance for flow area contraction from the inlet to the restriction
Momentum balance for sudden flow area expansion from the restriction to the outlet
In the analysis for the flow area contraction, pressure p_{in} acts on the area at the inlet, S, and pressure p_{R} acts on the area at the restriction, S_{R}. The pressure acting on the area outside the restriction, S − S_{R}, is assumed to be (p_{in}S + p_{R}S_{R})/(S + S_{R}).
In the analysis for the flow area expansion, the pressure acting on both the area at the restriction, S_{R}, and the area outside the restriction, S − S_{R}, is assumed to be p_{R}, because of flow separation from the restriction. The pressure acting on the area at the outlet , S, is equal to p_{out}.
The mixture mass flow rate (positive from port A to port B) in the laminar regime is linearized with respect to the pressure difference:
$${\dot{m}}_{lam}={C}_{d}{S}_{R}\left({p}_{A}{p}_{B}\right)\sqrt{\frac{2{\rho}_{R}}{\Delta {p}_{threshold}{\left(1\frac{{S}_{R}}{S}\right)}^{2}}}$$
where the threshold for transition between the laminar and turbulent regime is defined based on the laminar flow pressure ratio, B_{lam}, as
$$\Delta {p}_{threshold}=\left(\frac{{p}_{A}+{p}_{B}}{2}\right)\left(1{B}_{lam}\right)$$
When $$\left{p}_{A}{p}_{B}\right\ge \Delta {p}_{threshold}$$, the flow is assumed to be turbulent and therefore $${\dot{m}}_{unchoked}={\dot{m}}_{tur}$$.
When $$\left{p}_{A}{p}_{B}\right<\Delta {p}_{threshold}$$, $${\dot{m}}_{unchoked}$$ smoothly transitions to $${\dot{m}}_{lam}$$.
When the flow is choked, the velocity at the restriction is equal to the speed of sound and cannot increase any further. Assuming the flow is choked, the mixture mass flow rate is
$${\dot{m}}_{choked}={C}_{d}{S}_{R}{p}_{R}\sqrt{\frac{{\gamma}_{R}}{R{T}_{R}}}$$
where $${\gamma}_{R}={c}_{pR}/\left({c}_{pR}R\right)$$. Therefore, the actual mixture mass flow rate is equal to $${\dot{m}}_{unchoked}$$, but is limited in magnitude by $${\dot{m}}_{choked}$$:
$${\dot{m}}_{A}=\{\begin{array}{ll}{\dot{m}}_{choked},\hfill & \text{if}{\dot{m}}_{unchoked}\le {\dot{m}}_{choked}\hfill \\ {\dot{m}}_{unchoked},\hfill & \text{if}{\dot{m}}_{choked}{\dot{m}}_{unchoked}{\dot{m}}_{choked}\hfill \\ {\dot{m}}_{choked},\hfill & \text{if}{\dot{m}}_{unchoked}\ge {\dot{m}}_{choked}\text{}\hfill \end{array}$$
The expression for the pressure at the restriction is obtained by considering the momentum balance for flow area contraction from the inlet to the restriction only.
$${p}_{R}={p}_{in}\frac{1}{2{\rho}_{R}}{\left(\frac{{\dot{m}}_{A}}{{C}_{d}{S}_{R}}\right)}^{2}\left(1+\frac{{S}_{R}}{S}\right)\left(1\frac{{\rho}_{R}}{{\rho}_{in}}\frac{{S}_{R}}{S}\right)$$
The local restriction is assumed adiabatic, so the mixture specific total enthalpies are equal. Therefore, the changes in mixture specific enthalpies are:
$$\begin{array}{l}{h}_{A}{h}_{R}=\left(\frac{1}{{\rho}_{R}^{2}{S}_{R}^{2}}\frac{1}{{\rho}_{A}^{2}{S}^{2}}\right)\frac{{\dot{m}}_{A}^{2}}{2{C}_{D}^{2}}\\ {h}_{B}{h}_{R}=\left(\frac{1}{{\rho}_{R}^{2}{S}_{R}^{2}}\frac{1}{{\rho}_{B}^{2}{S}^{2}}\right)\frac{{\dot{m}}_{B}^{2}}{2{C}_{D}^{2}}\end{array}$$
The restriction is adiabatic. It does not exchange heat with the environment.
This block does not model supersonic flow.