diff --git a/rocketpy/Rocket.py b/rocketpy/Rocket.py
index e62eb3dcb..4e937e6ea 100644
--- a/rocketpy/Rocket.py
+++ b/rocketpy/Rocket.py
@@ -234,6 +234,9 @@ def __init__(
 
         # Parachute data initialization
         self.parachutes = []
+                
+        # Parachute's Calculated Cds data initialization
+        self.calculated_cds = []
 
         # Rail button data initialization
         self.railButtons = None
@@ -662,63 +665,27 @@ def cnalfa1(cn):
             # Return self
             return self.aerodynamicSurfaces[-1]
 
-    def calculateCds(
-        self,
-        finalSpeed = 9,
-        finalAirDensity = None,
-        parachuteKind = None,
-        Cd = None,
-        area = None
-    ):
-        """Calculates the parachute's Cds using its final speed and 
-        air density or its area, that can be given or calculated through
-        the Cd or kind of the parachute 
+    def calculate_cds(self, final_speed = 9, final_air_density):
+        """Returns the parachute's Cds calculated through its final speed and 
+        air density.
+        
         Parameters
         ----------
-        finalSpeed : float
-            Final speed of the system rocket/parachute.
-        finalAirDensity : float
-            Air density at the lowest height in which the parachute 
-            is being used.
-        parachuteKind : string
-            Indicates the format of the parachute.
-        Cd : float
-            Value of the parachute's dragg coefficient.
-        area : float
-            Surface area of the parachute in squared meters.
+        final_speed : float, optional
+            Rocket's speed when landing.
+        final_air_density : float
+            Air density right before the rocket lands.
 
         Returns
         -------
-        Cds : float
-            Estimated Cds of the parachute.
+        cds : float
+            Number equal to drag coefficient times reference area for parachute.
+            
         """
-
-        if finalAirDensity != None:
-            Cds = 2 * self.mass * 9.80665 / ((finalSpeed ** 2) * finalAirDensity)
-
-        elif Cd != None:
-            Cds = area * Cd
-
-        else:
-            if parachuteKind == "quarter spherical":
-                    Cd = 0.88
-
-            if parachuteKind == "semi-ellipsoidal":
-                    Cd = 0.6
-
-            if parachuteKind == "hemispherical":
-                    Cd = 0.7
-
-            if parachuteKind == "flat circular":
-                    Cd = 0.75
-
-            if parachuteKind == "conical":
-                    Cd = 0.8
         
-            if parachuteKind == "toroidal":
-                    Cd = 0.8
-            Cds = area * Cd
-        return Cds
+        cds = 2 * self.mass * 9.80665 / ((final_speed ** 2) * final_air_density)
+        self.calculated_cds.append(cds)
+        return cds
     
     def addParachute(
         self, name, CdS, trigger, samplingRate=100, lag=0, noise=(0, 0, 0)
@@ -951,7 +918,10 @@ def info(self):
         # Print parachute data
         for chute in self.parachutes:
             print("\n" + chute.name.title() + " Parachute")
-            print("CdS Coefficient: " + str(chute.CdS) + " m2")
+            if chute.CdS in self.calculated_cds:
+                print("Calculated CdS Coefficient: " + str(chute.CdS) + " m2")
+            else:
+                print("CdS Coefficient: " + str(chute.CdS) + " m2")
 
         # Show plots
         print("\nAerodynamics Plots")
@@ -1029,8 +999,11 @@ def allInfo(self):
 
         # Print parachute data
         for chute in self.parachutes:
-            print("\n" + chute.name.title() + " Parachute")
-            print("CdS Coefficient: " + str(chute.CdS) + " m2")
+            print("\n" + chute.name.title() + " Parachute")            
+            if chute.CdS in self.calculated_cds:
+                print("Calculated CdS Coefficient: " + str(chute.CdS) + " m2")
+            else:
+                print("CdS Coefficient: " + str(chute.CdS) + " m2")
             if chute.trigger.__name__ == "<lambda>":
                 line = getsourcelines(chute.trigger)[0][0]
                 print(