Module CompAero.isentropic_relations
This module contains the class that represents the Isentropic Flow State
Expand source code
"""This module contains the class that represents the Isentropic Flow State"""
from dataclasses import dataclass
from math import nan, sqrt
from colorama.ansi import Fore
from scipy.optimize import brenth # type: ignore
from CompAero.greek_letters import LowerCaseGreek as lcg
from CompAero.internal import (
GammaNotDefinedError,
InvalidOptionCombinationError,
check_value,
footer,
named_header,
seperator,
to_string,
)
from CompAero.types import FlowState
ISENTROPIC_VALID_OPTIONS = [
"gamma, mach",
" gamma, P0/P",
" gamma, T0/T",
" gamma, Rho0/Rho",
" gamma, A/A*",
]
@dataclass
class ISENTROPIC_CHOICE:
MACH = "gamma, mach"
P0_P = " gamma, P0/P"
T0_T = " gamma, T0/T"
RHO0_RHO = " gamma, Rho0/Rho"
a_a_star = " gamma, A/A*"
class IsentropicRelations:
# pylint: disable=too-many-instance-attributes
"""This class is a collective name space for basic calculations regarding isentropic flows.
The constructor of this class can also determine the entire state of the flow given a partial
state of the flow
Args:
gamma (float): ratio of specific heats
mach (float, optional): Mach number of the flow. Defaults to nan.
p0_p (float, optional): Ratio of total pressure to static pressure. Defaults to nan.
t0_t (float, optional): Ratio of total temperature to static temperature. Defaults to nan.
rho0_rho (float, optional): Ratio of total density to static density. Defaults to nan.
a_a_star (float, optional): Ratio of Nozzle Area to sonic throat area. Defaults to nan.
flow_type (FlowState, optional): States wether the flow is subsonic or supersonic.
Used for Area Ratio Calculations. Defaults to
FlowState.SUPER_SONIC.
Raises:
InvalidOptionCombinationError: Raised if invalid combination of values are given to the
constructor
Useage:
To use this class pass gamma and one of the known parameters of the flow and the rest are
calculated#.
Valid_Combinations_of_Parameters:
1: gamma, mach\n
2: gamma, p0/p\n
3: gamma, t0/t\n
4: gamma, rho0/rho\n
5: gamma, a/a*, flowtype (flow type defaults to super sonic)\n
"""
def __init__(
self,
gamma: float,
mach: float = nan,
p0_p: float = nan,
t0_t: float = nan,
rho0_rho: float = nan,
a_a_star: float = nan,
flow_type: FlowState = FlowState.SUPER_SONIC,
) -> None:
# pylint: disable=too-many-arguments
# pylint: disable=too-many-statements
self.gamma = gamma
""" Ratio of specific heats """
self.mach = mach
""" mach number of the flow """
self.p0_p = p0_p
""" Ratio of Total pressure to static pressure """
self.t0_t = t0_t
""" Ratio of total temperature to static temperature """
self.rho0_rho = rho0_rho
""" Ratio of total density to static density """
self.a_a_star = a_a_star
""" Ratio of Nozzle area to sonic nozzle area """
self.flow_type = flow_type
""" Type of flow which is either subsonic or supersonic (Type: flowstate) """
self.precision = 4
""" Precision to use when printing output to the console defaults to four """
# Calculate parameters based on what was passed in
if not check_value(self.gamma):
raise GammaNotDefinedError()
if check_value(self.mach):
pass
elif check_value(self.p0_p):
self.mach = IsentropicRelations.calc_mach_from_p0_p(self.p0_p, self.gamma)
elif check_value(self.t0_t):
self.mach = IsentropicRelations.calc_mach_from_t0_t(self.t0_t, self.gamma)
elif check_value(self.rho0_rho):
self.mach = IsentropicRelations.calc_mach_from_rho0_rho(self.rho0_rho, self.gamma)
elif check_value(self.a_a_star):
self.mach = IsentropicRelations.calc_mach_from_a_a_star(
self.a_a_star, self.gamma, self.flow_type
)
else:
raise InvalidOptionCombinationError()
if check_value(self.mach):
self.__calc_state_from_mach()
def __calc_state_from_mach(self) -> None:
self.t0_t = IsentropicRelations.calc_t0_t(self.mach, self.gamma)
self.p0_p = IsentropicRelations.calc_p0_p(self.mach, self.gamma)
self.rho0_rho = IsentropicRelations.calc_rho0_rho(self.mach, self.gamma)
self.a_a_star = IsentropicRelations.calc_a_a_star(self.mach, self.gamma)
self.flow_type = FlowState.SUPER_SONIC if self.mach > 1.0 else FlowState.SUB_SONIC
x = True
def __str__(self) -> str:
return "".join(
[
named_header("Isentropic Flow State at Mach", self.mach, self.precision),
seperator(),
to_string(lcg.gamma, self.gamma, self.precision, dot_line=True),
to_string("p0/p", self.p0_p, self.precision),
to_string("T0/T", self.t0_t, self.precision, dot_line=True),
to_string(f"{lcg.rho}0/{lcg.rho}", self.rho0_rho, self.precision),
to_string("A/A*", self.a_a_star, self.precision, dot_line=True),
to_string("Flow Type", self.flow_type.name, self.precision),
footer(),
]
)
@staticmethod
def calc_t0_t(mach: float, gamma: float, offset: float = 0.0) -> float:
"""Calculates the ratio of Total Temperature to static temperature (T0/T)
Args:
mach (float): Mach number of the flow
gamma (float): Ratio of specific heats of the flow
offset (float, optional): offset that can be used for root finding for a specific
value. Defaults to 0.0.
Returns:
float: T0/T
"""
return 1 + (gamma - 1) / 2 * pow(mach, 2) - offset
@staticmethod
def calc_mach_from_t0_t(t0_t: float, gamma: float) -> float:
"""Calculates the Mach number for a flow given the ratio of total tempto static temp
Args:
t0_t (float): Ratio of total temperature to static temperature
gamma (float): ratio of specific heats
Returns:
float: mach number
"""
return sqrt((t0_t - 1) * 2 / (gamma - 1))
@staticmethod
def calc_p0_p(mach: float, gamma: float, offset: float = 0.0) -> float:
"""Calculates the ratio of Total pressure to static pressure (P0/P)
Args:
mach (float): mach number of the flow
gamma (float): ratio of specific heats
offset (float, optional): offset that can be used for root finding for a specific
value. Defaults to 0.0.
Returns:
float: P0/P
"""
return pow((1 + (gamma - 1) / 2 * pow(mach, 2)), gamma / (gamma - 1)) - offset
@staticmethod
def calc_mach_from_p0_p(p0_p: float, gamma: float) -> float:
"""Calculates the Mach # for a flow given the ratio of total pressure to static pressure
Args:
p0_p (float): Ratio of total pressure to static pressure
gamma (float): ratio of specific heats
Returns:
float: mach number
"""
return brenth(IsentropicRelations.calc_p0_p, 0, 30, args=(gamma, p0_p)) # type: ignore
@staticmethod
def calc_rho0_rho(mach: float, gamma: float, offset: float = 0.0) -> float:
"""Calculates the ratio of Total density to static density (rho0/rho)
Args:
mach (float): mach number of the flow
gamma (float): ratio of specific heats
offset (float, optional): offset that can be used for root finding for a specific
value. Defaults to 0.0.
Returns:
float: rho0/rho
"""
return pow((1 + (gamma - 1) / 2 * pow(mach, 2)), 1 / (gamma - 1)) - offset
@staticmethod
def calc_mach_from_rho0_rho(rho0_rho: float, gamma: float) -> float:
"""Calculates the Mach number for a flow given the ratio of total density to static density
Args:
rho0_rho (float): Ratio of total density to static density
gamma (float): ratio of specific heats
Returns:
float: mach number
"""
return brenth(
IsentropicRelations.calc_rho0_rho, 0, 30, args=(gamma, rho0_rho)
) # type: ignore
@staticmethod
def calc_a_a_star(mach: float, gamma: float, offset: float = 0.0) -> float:
"""Calculates the ratio of Nozzle Area to Sonic Throat Area (A/A*)
Args:
mach (float): mach number of the flow
gamma (float): ratio of specific heats
offset (float, optional): offset that can be used for root finding for a specific
value. Defaults to 0.0.
Returns:
float: A/A*
"""
gm1 = gamma - 1
gp1 = gamma + 1
m_sqr = pow(mach, 2)
non_raised = 2 / gp1 * (1 + gm1 / 2 * m_sqr)
return sqrt(pow(non_raised, gp1 / gm1) / m_sqr) - offset
@staticmethod
def calc_mach_from_a_a_star(
a_a_star: float, gamma: float, flow_type: FlowState = FlowState.SUPER_SONIC
) -> float:
"""Calculates the mach number for a flow given the nozzle area ratio and flow type
Args:
a_a_star (float): Ratio of nozzle area ratio to sonic area ratio
gamma (float): ratio of specific heats
flow_type (FlowState, optional): Type of flow whether it is super sonic of subsonic.
Defaults to FlowState.SUPER_SONIC.
Returns:
float: mach number
"""
assert isinstance(flow_type, FlowState)
if a_a_star == 1.0:
return a_a_star
if flow_type == FlowState.SUPER_SONIC:
return brenth(
IsentropicRelations.calc_a_a_star, 1, 30, args=(gamma, a_a_star)
) # type: ignore
if flow_type == FlowState.SUB_SONIC:
return brenth(
IsentropicRelations.calc_a_a_star, 0.001, 1, args=(gamma, a_a_star)
) # type: ignore
err = f"{Fore.RED}Unsupported flow type passed to A/A* calculations. Got {flow_type}"
raise ValueError(err)Classes
class ISENTROPIC_CHOICE-
ISENTROPIC_CHOICE()
Expand source code
@dataclass class ISENTROPIC_CHOICE: MACH = "gamma, mach" P0_P = " gamma, P0/P" T0_T = " gamma, T0/T" RHO0_RHO = " gamma, Rho0/Rho" a_a_star = " gamma, A/A*"Class variables
var MACHvar P0_Pvar RHO0_RHOvar T0_Tvar a_a_star
class IsentropicRelations (gamma: float, mach: float = nan, p0_p: float = nan, t0_t: float = nan, rho0_rho: float = nan, a_a_star: float = nan, flow_type: FlowState = FlowState.SUPER_SONIC)-
This class is a collective name space for basic calculations regarding isentropic flows. The constructor of this class can also determine the entire state of the flow given a partial state of the flow
Args
gamma:float- ratio of specific heats
mach:float, optional- Mach number of the flow. Defaults to nan.
p0_p:float, optional- Ratio of total pressure to static pressure. Defaults to nan.
t0_t:float, optional- Ratio of total temperature to static temperature. Defaults to nan.
rho0_rho:float, optional- Ratio of total density to static density. Defaults to nan.
a_a_star:float, optional- Ratio of Nozzle Area to sonic throat area. Defaults to nan.
flow_type:FlowState, optional- States wether the flow is subsonic or supersonic. Used for Area Ratio Calculations. Defaults to FlowState.SUPER_SONIC.
Raises
InvalidOptionCombinationError- Raised if invalid combination of values are given to the constructor
Useage
To use this class pass gamma and one of the known parameters of the flow and the rest are calculated#.
Valid_Combinations_Of_Parameters
1: gamma, mach
2: gamma, p0/p
3: gamma, t0/t
4: gamma, rho0/rho
5: gamma, a/a*, flowtype (flow type defaults to super sonic)
Expand source code
class IsentropicRelations: # pylint: disable=too-many-instance-attributes """This class is a collective name space for basic calculations regarding isentropic flows. The constructor of this class can also determine the entire state of the flow given a partial state of the flow Args: gamma (float): ratio of specific heats mach (float, optional): Mach number of the flow. Defaults to nan. p0_p (float, optional): Ratio of total pressure to static pressure. Defaults to nan. t0_t (float, optional): Ratio of total temperature to static temperature. Defaults to nan. rho0_rho (float, optional): Ratio of total density to static density. Defaults to nan. a_a_star (float, optional): Ratio of Nozzle Area to sonic throat area. Defaults to nan. flow_type (FlowState, optional): States wether the flow is subsonic or supersonic. Used for Area Ratio Calculations. Defaults to FlowState.SUPER_SONIC. Raises: InvalidOptionCombinationError: Raised if invalid combination of values are given to the constructor Useage: To use this class pass gamma and one of the known parameters of the flow and the rest are calculated#. Valid_Combinations_of_Parameters: 1: gamma, mach\n 2: gamma, p0/p\n 3: gamma, t0/t\n 4: gamma, rho0/rho\n 5: gamma, a/a*, flowtype (flow type defaults to super sonic)\n """ def __init__( self, gamma: float, mach: float = nan, p0_p: float = nan, t0_t: float = nan, rho0_rho: float = nan, a_a_star: float = nan, flow_type: FlowState = FlowState.SUPER_SONIC, ) -> None: # pylint: disable=too-many-arguments # pylint: disable=too-many-statements self.gamma = gamma """ Ratio of specific heats """ self.mach = mach """ mach number of the flow """ self.p0_p = p0_p """ Ratio of Total pressure to static pressure """ self.t0_t = t0_t """ Ratio of total temperature to static temperature """ self.rho0_rho = rho0_rho """ Ratio of total density to static density """ self.a_a_star = a_a_star """ Ratio of Nozzle area to sonic nozzle area """ self.flow_type = flow_type """ Type of flow which is either subsonic or supersonic (Type: flowstate) """ self.precision = 4 """ Precision to use when printing output to the console defaults to four """ # Calculate parameters based on what was passed in if not check_value(self.gamma): raise GammaNotDefinedError() if check_value(self.mach): pass elif check_value(self.p0_p): self.mach = IsentropicRelations.calc_mach_from_p0_p(self.p0_p, self.gamma) elif check_value(self.t0_t): self.mach = IsentropicRelations.calc_mach_from_t0_t(self.t0_t, self.gamma) elif check_value(self.rho0_rho): self.mach = IsentropicRelations.calc_mach_from_rho0_rho(self.rho0_rho, self.gamma) elif check_value(self.a_a_star): self.mach = IsentropicRelations.calc_mach_from_a_a_star( self.a_a_star, self.gamma, self.flow_type ) else: raise InvalidOptionCombinationError() if check_value(self.mach): self.__calc_state_from_mach() def __calc_state_from_mach(self) -> None: self.t0_t = IsentropicRelations.calc_t0_t(self.mach, self.gamma) self.p0_p = IsentropicRelations.calc_p0_p(self.mach, self.gamma) self.rho0_rho = IsentropicRelations.calc_rho0_rho(self.mach, self.gamma) self.a_a_star = IsentropicRelations.calc_a_a_star(self.mach, self.gamma) self.flow_type = FlowState.SUPER_SONIC if self.mach > 1.0 else FlowState.SUB_SONIC x = True def __str__(self) -> str: return "".join( [ named_header("Isentropic Flow State at Mach", self.mach, self.precision), seperator(), to_string(lcg.gamma, self.gamma, self.precision, dot_line=True), to_string("p0/p", self.p0_p, self.precision), to_string("T0/T", self.t0_t, self.precision, dot_line=True), to_string(f"{lcg.rho}0/{lcg.rho}", self.rho0_rho, self.precision), to_string("A/A*", self.a_a_star, self.precision, dot_line=True), to_string("Flow Type", self.flow_type.name, self.precision), footer(), ] ) @staticmethod def calc_t0_t(mach: float, gamma: float, offset: float = 0.0) -> float: """Calculates the ratio of Total Temperature to static temperature (T0/T) Args: mach (float): Mach number of the flow gamma (float): Ratio of specific heats of the flow offset (float, optional): offset that can be used for root finding for a specific value. Defaults to 0.0. Returns: float: T0/T """ return 1 + (gamma - 1) / 2 * pow(mach, 2) - offset @staticmethod def calc_mach_from_t0_t(t0_t: float, gamma: float) -> float: """Calculates the Mach number for a flow given the ratio of total tempto static temp Args: t0_t (float): Ratio of total temperature to static temperature gamma (float): ratio of specific heats Returns: float: mach number """ return sqrt((t0_t - 1) * 2 / (gamma - 1)) @staticmethod def calc_p0_p(mach: float, gamma: float, offset: float = 0.0) -> float: """Calculates the ratio of Total pressure to static pressure (P0/P) Args: mach (float): mach number of the flow gamma (float): ratio of specific heats offset (float, optional): offset that can be used for root finding for a specific value. Defaults to 0.0. Returns: float: P0/P """ return pow((1 + (gamma - 1) / 2 * pow(mach, 2)), gamma / (gamma - 1)) - offset @staticmethod def calc_mach_from_p0_p(p0_p: float, gamma: float) -> float: """Calculates the Mach # for a flow given the ratio of total pressure to static pressure Args: p0_p (float): Ratio of total pressure to static pressure gamma (float): ratio of specific heats Returns: float: mach number """ return brenth(IsentropicRelations.calc_p0_p, 0, 30, args=(gamma, p0_p)) # type: ignore @staticmethod def calc_rho0_rho(mach: float, gamma: float, offset: float = 0.0) -> float: """Calculates the ratio of Total density to static density (rho0/rho) Args: mach (float): mach number of the flow gamma (float): ratio of specific heats offset (float, optional): offset that can be used for root finding for a specific value. Defaults to 0.0. Returns: float: rho0/rho """ return pow((1 + (gamma - 1) / 2 * pow(mach, 2)), 1 / (gamma - 1)) - offset @staticmethod def calc_mach_from_rho0_rho(rho0_rho: float, gamma: float) -> float: """Calculates the Mach number for a flow given the ratio of total density to static density Args: rho0_rho (float): Ratio of total density to static density gamma (float): ratio of specific heats Returns: float: mach number """ return brenth( IsentropicRelations.calc_rho0_rho, 0, 30, args=(gamma, rho0_rho) ) # type: ignore @staticmethod def calc_a_a_star(mach: float, gamma: float, offset: float = 0.0) -> float: """Calculates the ratio of Nozzle Area to Sonic Throat Area (A/A*) Args: mach (float): mach number of the flow gamma (float): ratio of specific heats offset (float, optional): offset that can be used for root finding for a specific value. Defaults to 0.0. Returns: float: A/A* """ gm1 = gamma - 1 gp1 = gamma + 1 m_sqr = pow(mach, 2) non_raised = 2 / gp1 * (1 + gm1 / 2 * m_sqr) return sqrt(pow(non_raised, gp1 / gm1) / m_sqr) - offset @staticmethod def calc_mach_from_a_a_star( a_a_star: float, gamma: float, flow_type: FlowState = FlowState.SUPER_SONIC ) -> float: """Calculates the mach number for a flow given the nozzle area ratio and flow type Args: a_a_star (float): Ratio of nozzle area ratio to sonic area ratio gamma (float): ratio of specific heats flow_type (FlowState, optional): Type of flow whether it is super sonic of subsonic. Defaults to FlowState.SUPER_SONIC. Returns: float: mach number """ assert isinstance(flow_type, FlowState) if a_a_star == 1.0: return a_a_star if flow_type == FlowState.SUPER_SONIC: return brenth( IsentropicRelations.calc_a_a_star, 1, 30, args=(gamma, a_a_star) ) # type: ignore if flow_type == FlowState.SUB_SONIC: return brenth( IsentropicRelations.calc_a_a_star, 0.001, 1, args=(gamma, a_a_star) ) # type: ignore err = f"{Fore.RED}Unsupported flow type passed to A/A* calculations. Got {flow_type}" raise ValueError(err)Static methods
def calc_a_a_star(mach: float, gamma: float, offset: float = 0.0) ‑> float-
Calculates the ratio of Nozzle Area to Sonic Throat Area (A/A*)
Args
mach:float- mach number of the flow
gamma:float- ratio of specific heats
offset:float, optional- offset that can be used for root finding for a specific value. Defaults to 0.0.
Returns
float- A/A*
Expand source code
@staticmethod def calc_a_a_star(mach: float, gamma: float, offset: float = 0.0) -> float: """Calculates the ratio of Nozzle Area to Sonic Throat Area (A/A*) Args: mach (float): mach number of the flow gamma (float): ratio of specific heats offset (float, optional): offset that can be used for root finding for a specific value. Defaults to 0.0. Returns: float: A/A* """ gm1 = gamma - 1 gp1 = gamma + 1 m_sqr = pow(mach, 2) non_raised = 2 / gp1 * (1 + gm1 / 2 * m_sqr) return sqrt(pow(non_raised, gp1 / gm1) / m_sqr) - offset def calc_mach_from_a_a_star(a_a_star: float, gamma: float, flow_type: FlowState = FlowState.SUPER_SONIC) ‑> float-
Calculates the mach number for a flow given the nozzle area ratio and flow type
Args
a_a_star:float- Ratio of nozzle area ratio to sonic area ratio
gamma:float- ratio of specific heats
flow_type:FlowState, optional- Type of flow whether it is super sonic of subsonic. Defaults to FlowState.SUPER_SONIC.
Returns
float- mach number
Expand source code
@staticmethod def calc_mach_from_a_a_star( a_a_star: float, gamma: float, flow_type: FlowState = FlowState.SUPER_SONIC ) -> float: """Calculates the mach number for a flow given the nozzle area ratio and flow type Args: a_a_star (float): Ratio of nozzle area ratio to sonic area ratio gamma (float): ratio of specific heats flow_type (FlowState, optional): Type of flow whether it is super sonic of subsonic. Defaults to FlowState.SUPER_SONIC. Returns: float: mach number """ assert isinstance(flow_type, FlowState) if a_a_star == 1.0: return a_a_star if flow_type == FlowState.SUPER_SONIC: return brenth( IsentropicRelations.calc_a_a_star, 1, 30, args=(gamma, a_a_star) ) # type: ignore if flow_type == FlowState.SUB_SONIC: return brenth( IsentropicRelations.calc_a_a_star, 0.001, 1, args=(gamma, a_a_star) ) # type: ignore err = f"{Fore.RED}Unsupported flow type passed to A/A* calculations. Got {flow_type}" raise ValueError(err) def calc_mach_from_p0_p(p0_p: float, gamma: float) ‑> float-
Calculates the Mach # for a flow given the ratio of total pressure to static pressure
Args
p0_p:float- Ratio of total pressure to static pressure
gamma:float- ratio of specific heats
Returns
float- mach number
Expand source code
@staticmethod def calc_mach_from_p0_p(p0_p: float, gamma: float) -> float: """Calculates the Mach # for a flow given the ratio of total pressure to static pressure Args: p0_p (float): Ratio of total pressure to static pressure gamma (float): ratio of specific heats Returns: float: mach number """ return brenth(IsentropicRelations.calc_p0_p, 0, 30, args=(gamma, p0_p)) # type: ignore def calc_mach_from_rho0_rho(rho0_rho: float, gamma: float) ‑> float-
Calculates the Mach number for a flow given the ratio of total density to static density
Args
rho0_rho:float- Ratio of total density to static density
gamma:float- ratio of specific heats
Returns
float- mach number
Expand source code
@staticmethod def calc_mach_from_rho0_rho(rho0_rho: float, gamma: float) -> float: """Calculates the Mach number for a flow given the ratio of total density to static density Args: rho0_rho (float): Ratio of total density to static density gamma (float): ratio of specific heats Returns: float: mach number """ return brenth( IsentropicRelations.calc_rho0_rho, 0, 30, args=(gamma, rho0_rho) ) # type: ignore def calc_mach_from_t0_t(t0_t: float, gamma: float) ‑> float-
Calculates the Mach number for a flow given the ratio of total tempto static temp
Args
t0_t:float- Ratio of total temperature to static temperature
gamma:float- ratio of specific heats
Returns
float- mach number
Expand source code
@staticmethod def calc_mach_from_t0_t(t0_t: float, gamma: float) -> float: """Calculates the Mach number for a flow given the ratio of total tempto static temp Args: t0_t (float): Ratio of total temperature to static temperature gamma (float): ratio of specific heats Returns: float: mach number """ return sqrt((t0_t - 1) * 2 / (gamma - 1)) def calc_p0_p(mach: float, gamma: float, offset: float = 0.0) ‑> float-
Calculates the ratio of Total pressure to static pressure (P0/P)
Args
mach:float- mach number of the flow
gamma:float- ratio of specific heats
offset:float, optional- offset that can be used for root finding for a specific value. Defaults to 0.0.
Returns
float- P0/P
Expand source code
@staticmethod def calc_p0_p(mach: float, gamma: float, offset: float = 0.0) -> float: """Calculates the ratio of Total pressure to static pressure (P0/P) Args: mach (float): mach number of the flow gamma (float): ratio of specific heats offset (float, optional): offset that can be used for root finding for a specific value. Defaults to 0.0. Returns: float: P0/P """ return pow((1 + (gamma - 1) / 2 * pow(mach, 2)), gamma / (gamma - 1)) - offset def calc_rho0_rho(mach: float, gamma: float, offset: float = 0.0) ‑> float-
Calculates the ratio of Total density to static density (rho0/rho)
Args
mach:float- mach number of the flow
gamma:float- ratio of specific heats
offset:float, optional- offset that can be used for root finding for a specific value. Defaults to 0.0.
Returns
float- rho0/rho
Expand source code
@staticmethod def calc_rho0_rho(mach: float, gamma: float, offset: float = 0.0) -> float: """Calculates the ratio of Total density to static density (rho0/rho) Args: mach (float): mach number of the flow gamma (float): ratio of specific heats offset (float, optional): offset that can be used for root finding for a specific value. Defaults to 0.0. Returns: float: rho0/rho """ return pow((1 + (gamma - 1) / 2 * pow(mach, 2)), 1 / (gamma - 1)) - offset def calc_t0_t(mach: float, gamma: float, offset: float = 0.0) ‑> float-
Calculates the ratio of Total Temperature to static temperature (T0/T)
Args
mach:float- Mach number of the flow
gamma:float- Ratio of specific heats of the flow
offset:float, optional- offset that can be used for root finding for a specific value. Defaults to 0.0.
Returns
float- T0/T
Expand source code
@staticmethod def calc_t0_t(mach: float, gamma: float, offset: float = 0.0) -> float: """Calculates the ratio of Total Temperature to static temperature (T0/T) Args: mach (float): Mach number of the flow gamma (float): Ratio of specific heats of the flow offset (float, optional): offset that can be used for root finding for a specific value. Defaults to 0.0. Returns: float: T0/T """ return 1 + (gamma - 1) / 2 * pow(mach, 2) - offset
Instance variables
var a_a_star-
Ratio of Nozzle area to sonic nozzle area
var flow_type-
Type of flow which is either subsonic or supersonic (Type: flowstate)
var gamma-
Ratio of specific heats
var mach-
mach number of the flow
var p0_p-
Ratio of Total pressure to static pressure
var precision-
Precision to use when printing output to the console defaults to four
var rho0_rho-
Ratio of total density to static density
var t0_t-
Ratio of total temperature to static temperature