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ceasiompy/ThermoData/README.md

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+# Thermo_Data

ceasiompy/ThermoData/__specs__.py

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+from pathlib import Path
+from ceasiompy.utils.moduleinterfaces import CPACSInOut
+from ceasiompy.utils.commonxpath import (
+    REF_XPATH,
+    CLCALC_XPATH,
+    SU2_FIXED_CL_XPATH,
+    SU2_TARGET_CL_XPATH,
+    ENGINE_TYPE_XPATH,
+    RANGE_XPATH,
+)
+
+# ===== Module Status =====
+# True if the module is active
+# False if the module is disabled (not working or not ready)
+module_status = True
+
+# ===== Results directory path =====
+
+RESULTS_DIR = Path("Results", "Thermodata")
+
+# ===== CPACS inputs and outputs =====
+
+cpacs_inout = CPACSInOut()
+
+# ===== Input =====
+
+
+cpacs_inout.add_input(
+    var_name="net_force",
+    var_type=float,
+    default_value=2000,
+    unit="1",  # AGGIUNGERE UNITA DI MISURA
+    descr="Engine net force",
+    xpath=RANGE_XPATH + "/NetForce",
+    gui=True,
+    gui_name="NetForce",
+    gui_group="Cruise",
+)
+
+cpacs_inout.add_input(
+    var_name="engine type",
+    var_type=list,
+    default_value=[0, 1],
+    unit=None,
+    descr="0: TBJ, 1: TBF ",
+    xpath=ENGINE_TYPE_XPATH,
+    gui=True,
+    gui_name="0 for Turbojet 1 for Turbofan",
+    gui_group="User inputs",
+)
+
+
+# ===== Output =====
+
+cpacs_inout.add_output(
+    var_name="target_cl",
+    default_value=None,
+    unit="1",
+    descr="Value of CL to achieve to have a level flight with the given conditions",
+    xpath=SU2_TARGET_CL_XPATH,
+)
+
+cpacs_inout.add_output(
+    var_name="fixed_cl",
+    default_value=None,
+    unit="-",
+    descr="FIXED_CL_MODE parameter for SU2",
+    xpath=SU2_FIXED_CL_XPATH,
+)

ceasiompy/ThermoData/func/run_func.py

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+"""
+CEASIOMpy: Conceptual Aircraft Design Software
+
+Developed by CFS ENGINEERING, 1015 Lausanne, Switzerland
+
+Function to run the PyCycle code in order to obtain turbojet and turbofan boundary conditions
+at given altitude, mach number and net force = thrust of the engine 
+
+Python version: >=3.8
+
+| Author: Giacomo Benedetti and Francesco Marcucci
+| Creation: 2023-12-12
+
+"""
+
+from pathlib import Path
+
+from ceasiompy.ThermoData.func.turbofan_func import (
+    turbofan_analysis,
+    write_hbtf_file,
+)
+
+from ceasiompy.ThermoData.func.turbojet_func import (
+    turbojet_analysis,
+    write_turbojet_file,
+)
+
+from ceasiompy.utils.ceasiomlogger import get_logger
+
+from ceasiompy.utils.commonxpath import (
+    ENGINE_TYPE_XPATH,
+    ENGINE_BC,
+    RANGE_XPATH,
+    SU2_AEROMAP_UID_XPATH,
+)
+from ceasiompy.utils.commonnames import (
+    ENGINE_BOUNDARY_CONDITIONS,
+)
+from cpacspy.cpacsfunctions import (
+    get_value_or_default,
+    add_float_vector,
+)
+from cpacspy.cpacsfunctions import create_branch, get_value_or_default
+from cpacspy.cpacspy import CPACS
+
+log = get_logger()
+
+MODULE_DIR = Path(__file__).parent
+MODULE_NAME = MODULE_DIR.name
+
+
+def thermo_data_run(cpacs_path, cpacs_out_path, wkdir):
+    """Running the PyCycle code by choosing between turbojet or turbofan engine
+
+    Args
+        cpacs_path (Path): Path to CPACS file
+        cpacs_out_path (Path):Path to CPACS output file
+        wkdir (str): Path to the working directory
+    """
+
+    if not wkdir.exists():
+        raise OSError(f"The working directory : {wkdir} does not exit!")
+
+    cpacs = CPACS(cpacs_path)
+    tixi = cpacs.tixi
+
+    Fn = get_value_or_default(tixi, RANGE_XPATH + "/NetForce", 2000)
+
+    aeromap_list = cpacs.get_aeromap_uid_list()
+
+    if aeromap_list:
+        aeromap_default = aeromap_list[0]
+        log.info(f"The aeromap is {aeromap_default}")
+        aeromap_uid = get_value_or_default(
+            cpacs.tixi, SU2_AEROMAP_UID_XPATH, aeromap_default
+        )
+        activate_aeromap = cpacs.get_aeromap_by_uid(aeromap_uid)
+        alt_list = activate_aeromap.get("altitude").tolist()
+        mach_list = activate_aeromap.get("machNumber").tolist()
+        T_tot_out_array = []
+        P_tot_out_array = []
+
+        for case_nb in range(len(alt_list)):
+            alt = alt_list[case_nb]
+            MN = mach_list[case_nb]
+            case_dir_name = f"Case{str(case_nb).zfill(2)}_alt{alt}_mach{round(MN, 2)}"
+            case_dir_path = Path(wkdir, case_dir_name)
+
+            if not case_dir_path.exists():
+                case_dir_path.mkdir()
+
+                EngineBC = Path(case_dir_path, ENGINE_BOUNDARY_CONDITIONS)
+
+                f = open(EngineBC, "w")
+
+                engine_type = get_value_or_default(tixi, ENGINE_TYPE_XPATH, 0)
+                create_branch(cpacs.tixi, ENGINE_BC)
+
+                if engine_type == 0:
+                    (
+                        T_tot_out,
+                        V_stat_out,
+                        MN_out,
+                        P_tot_out,
+                        massflow_stat_out,
+                        T_stat_out,
+                        P_stat_out,
+                    ) = turbojet_analysis(alt, MN, Fn)
+
+                    T_tot_out_array.append(T_tot_out)
+                    P_tot_out_array.append(P_tot_out)
+
+                    f = write_turbojet_file(
+                        file=f,
+                        T_tot_out=T_tot_out,
+                        V_stat_out=V_stat_out,
+                        MN_out=MN_out,
+                        P_tot_out=P_tot_out,
+                        massflow_stat_out=massflow_stat_out,
+                        T_stat_out=T_stat_out,
+                        P_stat_out=P_stat_out,
+                    )
+
+                else:
+
+                    (
+                        T_tot_out_byp,
+                        V_stat_out_byp,
+                        MN_out_byp,
+                        P_tot_out_byp,
+                        massflow_stat_out_byp,
+                        T_stat_out_byp,
+                        T_tot_out_core,
+                        V_stat_out_core,
+                        MN_out_core,
+                        P_tot_out_core,
+                        massflow_stat_out_core,
+                        T_stat_out_core,
+                    ) = turbofan_analysis(alt, MN, Fn)
+
+                    T_tot_out_array.append(T_tot_out_core)
+                    P_tot_out_array.append(P_tot_out_core)
+
+                    f = write_hbtf_file(
+                        file=f,
+                        T_tot_out_byp=T_tot_out_byp,
+                        V_stat_out_byp=V_stat_out_byp,
+                        MN_out_byp=MN_out_byp,
+                        P_tot_out_byp=P_tot_out_byp,
+                        massflow_stat_out_byp=massflow_stat_out_byp,
+                        T_stat_out_byp=T_stat_out_byp,
+                        T_tot_out_core=T_tot_out_core,
+                        V_stat_out_core=V_stat_out_core,
+                        MN_out_core=MN_out_core,
+                        P_tot_out_core=P_tot_out_core,
+                        massflow_stat_out_core=massflow_stat_out_core,
+                        T_stat_out_core=T_stat_out_core,
+                    )
+        add_float_vector(tixi, ENGINE_BC + "/temperatureOutlet", T_tot_out_array)
+        add_float_vector(tixi, ENGINE_BC + "/pressureOutlet", P_tot_out_array)
+
+    cpacs.save_cpacs(cpacs_out_path, overwrite=True)