Update src/engines/ramjet.py

src/engines/ramjet.py

@@ -14,6 +14,7 @@ T_ISA_SL = 288.15
 LAPSE = 0.0065
 LHV_JP10 = 43.50e6
 
+
 class RamjetEngine(BaseEngine):
     def __init__(self):
         super().__init__(
@@ -161,10 +162,10 @@ class RamjetEngine(BaseEngine):
 
     def compute_fault_signatures(self, baseline: Dict, flight_conditions: Dict) -> List[List[Dict]]:
         results = []
-        for f in self.fault_library:
+        for fault in self.fault_library:  # renamed from 'f' to avoid shadowing
             lvl_vals = []
             for lv in range(3):
-                m = f["levels"][lv]
+                m = fault["levels"][lv]
                 alt_m = flight_conditions.get("altitude_m", 15000)
                 M = flight_conditions.get("mach", 2.5)
 
@@ -180,12 +181,12 @@ class RamjetEngine(BaseEngine):
                 P_t2 = P0 * eta_rec
                 T_t4 = 2200.0 * (1 - (m[3] if len(m) > 3 else 0))
                 mdot = self.A_inlet * P0 * M * (GAMMA / (T0 * 287))**0.5
-                f = mdot * CP * (T_t4 - T_t2) / (eta_b * LHV_JP10)
+                fuel_ratio = mdot * CP * (T_t4 - T_t2) / (eta_b * LHV_JP10)  # renamed from 'f'
                 T_t5 = T_t4
                 P_t5 = P_t2 * eta_n
                 V_exit = (2 * CP * (T_t5 - T))**0.5
                 thrust = mdot * (V_exit - M * (GAMMA * 287 * T)**0.5) + (P_t5 - P) * self.A_exit
-                Isp = thrust / (f * 9.81) if f > 0 else 0
+                Isp = thrust / (fuel_ratio * 9.81) if fuel_ratio > 0 else 0
                 EGT = T_t5 - 273.15
 
                 lvl_vals.append({"EGT": EGT, "thrust": thrust/1000, "Isp": Isp, "mdot": mdot})
@@ -247,3 +248,4 @@ class RamjetEngine(BaseEngine):
             {"name": "Isp", "label": "Specific Impulse", "default": 1200.0, "unit": "s", "type": "number"},
             {"name": "mdot", "label": "Air Mass Flow", "default": 2.5, "unit": "kg/s", "type": "number"}
         ]
+