public final class Isentropic
extends java.lang.Object
Written by: Joseph A. Huwaldt
Modifier and Type | Field and Description |
---|---|
static boolean |
SUBSONIC
Constant indicating that a subsonic solution should be returned in Me().
|
static boolean |
SUPERSONIC
Constant indicating that a supersonic solution should be returned in Me().
|
Modifier and Type | Method and Description |
---|---|
static double |
A_Astar(double M,
double gam)
Calculates the duct area ratio (A/A*) necessary to create sonic flow (M=1) at the
throat of the duct.
|
static void |
main(java.lang.String[] args)
A simple method to test the isentropic methods in this class.
|
static double |
Me(double A_Astar,
double gam,
double tol,
boolean type)
Calculates the Mach number at the entrance or exit of a duct (nozzle) given the
ratio of the local duct area at the entrance or exit to the area where the sonic
(M=1) condition exists.
|
static double |
Me(double A_Astar,
double gam,
double tol,
boolean type,
IsentropicMeEvaluator machfn)
Calculates the Mach number at the entrance or exit of a duct (nozzle) given the
ratio of the local duct area at the entrance or exit to the area where the sonic
(M=1) condition exists.
|
static double |
P2_P1(double T2_T1,
double gam)
Calculate the isentropic pressure ratio between two points in the flow given the
temperature ratio.
|
static double |
PT_P(double M,
double gam)
Calculates the ratio of total to static pressure at a point in a flow as a function
of Mach number at that point.
|
static double |
rho2_rho1(double T2_T1,
double gam)
Calculate the isentropic density ratio between two points in the flow given the
temperature ratio.
|
static double |
rhoT_rho(double M,
double gam)
Calculates the ratio of total to static density at a point in a flow as a function
of Mach number at that point.
|
static double |
T2_T1(double P2_P1,
double gam)
Calculate the isentropic temperature ratio between two points in the flow given the
pressure ratio.
|
static double |
TT_T(double M,
double gam)
Calculates the ratio of total to static temperature at a point in a flow as a
function of Mach number at that point.
|
public static final boolean SUBSONIC
public static final boolean SUPERSONIC
public static double T2_T1(double P2_P1, double gam)
P2_P1
- The pressure ratio between two points in isentropic flow.gam
- The specific heat ratio of the gas. The value used for air is 1.4.public static double P2_P1(double T2_T1, double gam)
T2_T1
- The temperature ratio between two points in isentropic flow.gam
- The specific heat ratio of the gas. The value used for air is 1.4.public static double rho2_rho1(double T2_T1, double gam)
T2_T1
- The temperature ratio between two points in isentropic flow.gam
- The specific heat ratio of the gas. The value used for air is 1.4.public static double TT_T(double M, double gam)
M
- The Mach number at a point in the flow.gam
- The specific heat ratio of the gas. The value used for air is 1.4.public static double PT_P(double M, double gam)
M
- The Mach number at a point in the flow.gam
- The specific heat ratio of the gas. The value used for air is 1.4.public static double rhoT_rho(double M, double gam)
M
- The Mach number at a point in the flow.gam
- The specific heat ratio of the gas. The value used for air is 1.4.public static double A_Astar(double M, double gam)
M
- The Mach number at a point in the flow corresponding to the area "A".gam
- The specific heat ratio of the gas. The value used for air is 1.4.public static double Me(double A_Astar, double gam, double tol, boolean type) throws jahuwaldt.tools.math.RootException
A_Astar
- The ratio of the local duct area at the entrance or exit to the area
where the sonic condition exists (A/A*).gam
- The specific heat ratio of the gas. The value used for air is 1.4.tol
- Tolerance to use when calculating Mach number.type
- A flag that indicates if you want the subsonic (false) or supersonic
(true) solution returned.jahuwaldt.tools.math.RootException
public static double Me(double A_Astar, double gam, double tol, boolean type, IsentropicMeEvaluator machfn) throws jahuwaldt.tools.math.RootException
A_Astar
- The ratio of the local duct area at the entrance or exit to the area
where the sonic condition exists (A/A*).gam
- The specific heat ratio of the gas. The value used for air is 1.4.tol
- Tolerance to use when calculating Mach number.type
- A flag that indicates if you want the subsonic (false) or supersonic
(true) solution returned.machfn
- An instance of IsentropicMeEvaluator.jahuwaldt.tools.math.RootException
public static void main(java.lang.String[] args)