diff --git a/rocketpy/Flight.py b/rocketpy/Flight.py
index cb908dcab..2175967df 100644
--- a/rocketpy/Flight.py
+++ b/rocketpy/Flight.py
@@ -16,6 +16,7 @@
 from scipy import integrate
 
 from .Function import Function
+from .prints.flight_prints import _FlightPrints
 
 try:
     from functools import cached_property
@@ -636,6 +637,10 @@ def __init__(
         self._bearing = Function(0)
         self._latitude = Function(0)
         self._longitude = Function(0)
+
+        # Initialize prints and plots objects
+        self.prints = _FlightPrints(self)
+
         # Initialize solver monitors
         self.functionEvaluations = []
         self.functionEvaluationsPerTimeStep = []
@@ -3288,256 +3293,7 @@ def info(self):
         ------
         None
         """
-
-        # Get index of out of rail time
-        outOfRailTimeIndexes = np.nonzero(self.x[:, 0] == self.outOfRailTime)
-        outOfRailTimeIndex = (
-            -1 if len(outOfRailTimeIndexes) == 0 else outOfRailTimeIndexes[0][0]
-        )
-
-        # Get index of time before parachute event
-        if len(self.parachuteEvents) > 0:
-            eventTime = self.parachuteEvents[0][0] + self.parachuteEvents[0][1].lag
-            eventTimeIndex = np.nonzero(self.x[:, 0] == eventTime)[0][0]
-        else:
-            eventTime = self.tFinal
-            eventTimeIndex = -1
-
-        # Print surface wind conditions
-        print("Surface Wind Conditions\n")
-        print("Frontal Surface Wind Speed: {:.2f} m/s".format(self.frontalSurfaceWind))
-        print("Lateral Surface Wind Speed: {:.2f} m/s".format(self.lateralSurfaceWind))
-
-        # Print out of rail conditions
-        print("\n\n Rail Departure State\n")
-        print("Rail Departure Time: {:.3f} s".format(self.outOfRailTime))
-        print("Rail Departure Velocity: {:.3f} m/s".format(self.outOfRailVelocity))
-        print(
-            "Rail Departure Static Margin: {:.3f} c".format(
-                self.staticMargin(self.outOfRailTime)
-            )
-        )
-        print(
-            "Rail Departure Angle of Attack: {:.3f}°".format(
-                self.angleOfAttack(self.outOfRailTime)
-            )
-        )
-        print(
-            "Rail Departure Thrust-Weight Ratio: {:.3f}".format(
-                self.rocket.thrustToWeight(self.outOfRailTime)
-            )
-        )
-        print(
-            "Rail Departure Reynolds Number: {:.3e}".format(
-                self.ReynoldsNumber(self.outOfRailTime)
-            )
-        )
-
-        # Print burnOut conditions
-        print("\n\nBurnOut State\n")
-        print("BurnOut time: {:.3f} s".format(self.rocket.motor.burnOutTime))
-        print(
-            "Altitude at burnOut: {:.3f} m (AGL)".format(
-                self.z(self.rocket.motor.burnOutTime) - self.env.elevation
-            )
-        )
-        print(
-            "Rocket velocity at burnOut: {:.3f} m/s".format(
-                self.speed(self.rocket.motor.burnOutTime)
-            )
-        )
-        print(
-            "Freestream velocity at burnOut: {:.3f} m/s".format(
-                (
-                    self.streamVelocityX(self.rocket.motor.burnOutTime) ** 2
-                    + self.streamVelocityY(self.rocket.motor.burnOutTime) ** 2
-                    + self.streamVelocityZ(self.rocket.motor.burnOutTime) ** 2
-                )
-                ** 0.5
-            )
-        )
-        print(
-            "Mach Number at burnOut: {:.3f}".format(
-                self.MachNumber(self.rocket.motor.burnOutTime)
-            )
-        )
-        print(
-            "Kinetic energy at burnOut: {:.3e} J".format(
-                self.kineticEnergy(self.rocket.motor.burnOutTime)
-            )
-        )
-
-        # Print apogee conditions
-        print("\n\nApogee\n")
-        print(
-            "Apogee Altitude: {:.3f} m (ASL) | {:.3f} m (AGL)".format(
-                self.apogee, self.apogee - self.env.elevation
-            )
-        )
-        print("Apogee Time: {:.3f} s".format(self.apogeeTime))
-        print("Apogee Freestream Speed: {:.3f} m/s".format(self.apogeeFreestreamSpeed))
-
-        # Print events registered
-        print("\n\nEvents\n")
-        if len(self.parachuteEvents) == 0:
-            print("No Parachute Events Were Triggered.")
-        for event in self.parachuteEvents:
-            triggerTime = event[0]
-            parachute = event[1]
-            openTime = triggerTime + parachute.lag
-            velocity = self.freestreamSpeed(openTime)
-            altitude = self.z(openTime)
-            name = parachute.name.title()
-            print(name + " Ejection Triggered at: {:.3f} s".format(triggerTime))
-            print(name + " Parachute Inflated at: {:.3f} s".format(openTime))
-            print(
-                name
-                + " Parachute Inflated with Freestream Speed of: {:.3f} m/s".format(
-                    velocity
-                )
-            )
-            print(
-                name
-                + " Parachute Inflated at Height of: {:.3f} m (AGL)".format(
-                    altitude - self.env.elevation
-                )
-            )
-
-        # Print impact conditions
-        if len(self.impactState) != 0:
-            print("\n\nImpact\n")
-            print("X Impact: {:.3f} m".format(self.xImpact))
-            print("Y Impact: {:.3f} m".format(self.yImpact))
-            print("Time of Impact: {:.3f} s".format(self.tFinal))
-            print("Velocity at Impact: {:.3f} m/s".format(self.impactVelocity))
-        elif self.terminateOnApogee is False:
-            print("\n\nEnd of Simulation\n")
-            print("Time: {:.3f} s".format(self.solution[-1][0]))
-            print("Altitude: {:.3f} m".format(self.solution[-1][3]))
-
-        # Print maximum values
-        print("\n\nMaximum Values\n")
-        print(
-            "Maximum Speed: {:.3f} m/s at {:.2f} s".format(
-                self.maxSpeed, self.maxSpeedTime
-            )
-        )
-        print(
-            "Maximum Mach Number: {:.3f} Mach at {:.2f} s".format(
-                self.maxMachNumber, self.maxMachNumberTime
-            )
-        )
-        print(
-            "Maximum Reynolds Number: {:.3e} at {:.2f} s".format(
-                self.maxReynoldsNumber, self.maxReynoldsNumberTime
-            )
-        )
-        print(
-            "Maximum Dynamic Pressure: {:.3e} Pa at {:.2f} s".format(
-                self.maxDynamicPressure, self.maxDynamicPressureTime
-            )
-        )
-        print(
-            "Maximum Acceleration: {:.3f} m/s² at {:.2f} s".format(
-                self.maxAcceleration, self.maxAccelerationTime
-            )
-        )
-        print(
-            "Maximum Gs: {:.3f} g at {:.2f} s".format(
-                self.maxAcceleration / self.env.g, self.maxAccelerationTime
-            )
-        )
-        print(
-            "Maximum Upper Rail Button Normal Force: {:.3f} N".format(
-                self.maxRailButton1NormalForce
-            )
-        )
-        print(
-            "Maximum Upper Rail Button Shear Force: {:.3f} N".format(
-                self.maxRailButton1ShearForce
-            )
-        )
-        print(
-            "Maximum Lower Rail Button Normal Force: {:.3f} N".format(
-                self.maxRailButton2NormalForce
-            )
-        )
-        print(
-            "Maximum Lower Rail Button Shear Force: {:.3f} N".format(
-                self.maxRailButton2ShearForce
-            )
-        )
-
-        return None
-
-    def printInitialConditionsData(self):
-        """Prints all initial conditions data available about the flight
-
-        Parameters
-        ----------
-        None
-
-        Return
-        ------
-        None
-        """
-
-        print(
-            "Position - x: {:.2f} m | y: {:.2f} m | z: {:.2f} m".format(
-                self.x(0), self.y(0), self.z(0)
-            )
-        )
-        print(
-            "Velocity - Vx: {:.2f} m/s | Vy: {:.2f} m/s | Vz: {:.2f} m/s".format(
-                self.vx(0), self.vy(0), self.vz(0)
-            )
-        )
-        print(
-            "Attitude - e0: {:.3f} | e1: {:.3f} | e2: {:.3f} | e3: {:.3f}".format(
-                self.e0(0), self.e1(0), self.e2(0), self.e3(0)
-            )
-        )
-        print(
-            "Euler Angles - Spin φ : {:.2f}° | Nutation θ: {:.2f}° | Precession ψ: {:.2f}°".format(
-                self.phi(0), self.theta(0), self.psi(0)
-            )
-        )
-        print(
-            "Angular Velocity - ω1: {:.2f} rad/s | ω2: {:.2f} rad/s| ω3: {:.2f} rad/s".format(
-                self.w1(0), self.w2(0), self.w3(0)
-            )
-        )
-        return None
-
-    def printNumericalIntegrationSettings(self):
-        """Prints out the Numerical Integration settings
-
-        Parameters
-        ----------
-        None
-
-        Return
-        ------
-        None
-        """
-        print("Maximum Allowed Flight Time: {:f} s".format(self.maxTime))
-        print("Maximum Allowed Time Step: {:f} s".format(self.maxTimeStep))
-        print("Minimum Allowed Time Step: {:e} s".format(self.minTimeStep))
-        print("Relative Error Tolerance: ", self.rtol)
-        print("Absolute Error Tolerance: ", self.atol)
-        print("Allow Event Overshoot: ", self.timeOvershoot)
-        print("Terminate Simulation on Apogee: ", self.terminateOnApogee)
-        print("Number of Time Steps Used: ", len(self.timeSteps))
-        print(
-            "Number of Derivative Functions Evaluation: ",
-            sum(self.functionEvaluationsPerTimeStep),
-        )
-        print(
-            "Average Function Evaluations per Time Step: {:3f}".format(
-                sum(self.functionEvaluationsPerTimeStep) / len(self.timeSteps)
-            )
-        )
-
+        self.prints.all()
         return None
 
     def calculateStallWindVelocity(self, stallAngle):
@@ -4706,21 +4462,9 @@ def allInfo(self):
         None
         """
 
-        # Print initial conditions
-        print("Initial Conditions\n")
-        self.printInitialConditionsData()
-
-        # Print launch rail orientation
-        print("\n\nLaunch Rail Orientation\n")
-        print("Launch Rail Inclination: {:.2f}°".format(self.inclination))
-        print("Launch Rail Heading: {:.2f}°\n\n".format(self.heading))
-
         # Print a summary of data about the flight
         self.info()
 
-        print("\n\nNumerical Integration Information\n")
-        self.printNumericalIntegrationSettings()
-
         print("\n\nTrajectory 3d Plot\n")
         self.plot3dTrajectory()
 
diff --git a/rocketpy/prints/flight_prints.py b/rocketpy/prints/flight_prints.py
index 07cc08158..330ef1c29 100644
--- a/rocketpy/prints/flight_prints.py
+++ b/rocketpy/prints/flight_prints.py
@@ -4,5 +4,433 @@
 
 
 class _FlightPrints:
-    def __init__(self) -> None:
-        pass
+    """Class that holds prints methods for Flight class.
+
+    Attributes
+    ----------
+    _FlightPrints.flight : Flight
+        Flight object that will be used for the prints.
+
+    """
+
+    def __init__(
+        self,
+        flight,
+    ):
+        """Initializes _FlightPrints class
+
+        Parameters
+        ----------
+        flight: Flight
+            Instance of the Flight class.
+
+        Returns
+        -------
+        None
+        """
+        self.flight = flight
+        return None
+
+    def initial_conditions(self):
+        """Prints all initial conditions data available about the Flight.
+
+        Parameters
+        ----------
+        None
+
+        Return
+        ------
+        None
+        """
+
+        print("\nInitial Conditions\n")
+
+        # Post-process results
+        if self.flight.postProcessed is False:
+            self.flight.postProcess()
+        print(
+            "Position - x: {:.2f} m | y: {:.2f} m | z: {:.2f} m".format(
+                self.flight.x(0), self.flight.y(0), self.flight.z(0)
+            )
+        )
+        print(
+            "Velocity - Vx: {:.2f} m/s | Vy: {:.2f} m/s | Vz: {:.2f} m/s".format(
+                self.flight.vx(0), self.flight.vy(0), self.flight.vz(0)
+            )
+        )
+        print(
+            "Attitude - e0: {:.3f} | e1: {:.3f} | e2: {:.3f} | e3: {:.3f}".format(
+                self.flight.e0(0),
+                self.flight.e1(0),
+                self.flight.e2(0),
+                self.flight.e3(0),
+            )
+        )
+        print(
+            "Euler Angles - Spin φ : {:.2f}° | Nutation θ: {:.2f}° | Precession ψ: {:.2f}°".format(
+                self.flight.phi(0), self.flight.theta(0), self.flight.psi(0)
+            )
+        )
+        print(
+            "Angular Velocity - ω1: {:.2f} rad/s | ω2: {:.2f} rad/s| ω3: {:.2f} rad/s".format(
+                self.flight.w1(0), self.flight.w2(0), self.flight.w3(0)
+            )
+        )
+
+        return None
+
+    def numerical_integration_settings(self):
+        """Prints out the Numerical Integration settings available about the
+        flight.
+
+        Parameters
+        ----------
+        None
+
+        Return
+        ------
+        None
+        """
+
+        print("\nNumerical Integration Settings\n")
+        print("Maximum Allowed Flight Time: {:f} s".format(self.flight.maxTime))
+        print("Maximum Allowed Time Step: {:f} s".format(self.flight.maxTimeStep))
+        print("Minimum Allowed Time Step: {:e} s".format(self.flight.minTimeStep))
+        print("Relative Error Tolerance: ", self.flight.rtol)
+        print("Absolute Error Tolerance: ", self.flight.atol)
+        print("Allow Event Overshoot: ", self.flight.timeOvershoot)
+        print("Terminate Simulation on Apogee: ", self.flight.terminateOnApogee)
+        print("Number of Time Steps Used: ", len(self.flight.timeSteps))
+        print(
+            "Number of Derivative Functions Evaluation: ",
+            sum(self.flight.functionEvaluationsPerTimeStep),
+        )
+        print(
+            "Average Function Evaluations per Time Step: {:3f}".format(
+                sum(self.flight.functionEvaluationsPerTimeStep)
+                / len(self.flight.timeSteps)
+            )
+        )
+
+        return None
+
+    def surface_wind_conditions(self):
+        """Prints out the Surface Wind Conditions available about the flight.
+
+        Returns
+        -------
+        None
+        """
+        if self.flight.postProcessed is False:
+            self.flight.postProcess()
+        print("\nSurface Wind Conditions\n")
+        print(
+            "Frontal Surface Wind Speed: {:.2f} m/s".format(
+                self.flight.frontalSurfaceWind
+            )
+        )
+        print(
+            "Lateral Surface Wind Speed: {:.2f} m/s".format(
+                self.flight.lateralSurfaceWind
+            )
+        )
+
+        return None
+
+    def launch_rail_conditions(self):
+        """Prints out the Launch Rail Conditions available about the flight.
+
+        Parameters
+        ----------
+        None
+
+        Returns
+        -------
+        None
+        """
+
+        print("\nLaunch Rail Orientation\n")
+        print("Launch Rail Inclination: {:.2f}°".format(self.flight.inclination))
+        print("Launch Rail Heading: {:.2f}°".format(self.flight.heading))
+        return None
+
+    def out_of_rail_conditions(self):
+        """Prints out the Out of Rail Conditions available about the flight.
+
+        Returns
+        -------
+        None
+        """
+        if self.flight.postProcessed is False:
+            self.flight.postProcess()
+        print("\nRail Departure State\n")
+        print("Rail Departure Time: {:.3f} s".format(self.flight.outOfRailTime))
+        print(
+            "Rail Departure Velocity: {:.3f} m/s".format(self.flight.outOfRailVelocity)
+        )
+        print(
+            "Rail Departure Static Margin: {:.3f} c".format(
+                self.flight.staticMargin(self.flight.outOfRailTime)
+            )
+        )
+        print(
+            "Rail Departure Angle of Attack: {:.3f}°".format(
+                self.flight.angleOfAttack(self.flight.outOfRailTime)
+            )
+        )
+        print(
+            "Rail Departure Thrust-Weight Ratio: {:.3f}".format(
+                self.flight.rocket.thrustToWeight(self.flight.outOfRailTime)
+            )
+        )
+        print(
+            "Rail Departure Reynolds Number: {:.3e}".format(
+                self.flight.ReynoldsNumber(self.flight.outOfRailTime)
+            )
+        )
+
+        return None
+
+    def burn_out_conditions(self):
+        """Prints out the Burn Out Conditions available about the flight.
+
+        Returns
+        -------
+        None
+        """
+        if self.flight.postProcessed is False:
+            self.flight.postProcess()
+        print("\nBurnOut State\n")
+        print("BurnOut time: {:.3f} s".format(self.flight.rocket.motor.burnOutTime))
+        print(
+            "Altitude at burnOut: {:.3f} m (AGL)".format(
+                self.flight.z(self.flight.rocket.motor.burnOutTime)
+                - self.flight.env.elevation
+            )
+        )
+        print(
+            "Rocket velocity at burnOut: {:.3f} m/s".format(
+                self.flight.speed(self.flight.rocket.motor.burnOutTime)
+            )
+        )
+        print(
+            "Freestream velocity at burnOut: {:.3f} m/s".format(
+                (
+                    self.flight.streamVelocityX(self.flight.rocket.motor.burnOutTime)
+                    ** 2
+                    + self.flight.streamVelocityY(self.flight.rocket.motor.burnOutTime)
+                    ** 2
+                    + self.flight.streamVelocityZ(self.flight.rocket.motor.burnOutTime)
+                    ** 2
+                )
+                ** 0.5
+            )
+        )
+        print(
+            "Mach Number at burnOut: {:.3f}".format(
+                self.flight.MachNumber(self.flight.rocket.motor.burnOutTime)
+            )
+        )
+        print(
+            "Kinetic energy at burnOut: {:.3e} J".format(
+                self.flight.kineticEnergy(self.flight.rocket.motor.burnOutTime)
+            )
+        )
+
+        return None
+
+    def apogee_conditions(self):
+        """Prints out the Apogee Conditions available about the flight.
+
+        Returns
+        -------
+        None
+        """
+        if self.flight.postProcessed is False:
+            self.flight.postProcess()
+        print("\nApogee State\n")
+        print(
+            "Apogee Altitude: {:.3f} m (ASL) | {:.3f} m (AGL)".format(
+                self.flight.apogee, self.flight.apogee - self.flight.env.elevation
+            )
+        )
+        print("Apogee Time: {:.3f} s".format(self.flight.apogeeTime))
+        print(
+            "Apogee Freestream Speed: {:.3f} m/s".format(
+                self.flight.apogeeFreestreamSpeed
+            )
+        )
+
+        return None
+
+    def events_registered(self):
+        """Prints out the Events Registered available about the flight.
+
+        Returns
+        -------
+        None
+        """
+        if self.flight.postProcessed is False:
+            self.flight.postProcess()
+        print("\nParachute Events\n")
+        if len(self.flight.parachuteEvents) == 0:
+            print("No Parachute Events Were Triggered.")
+        for event in self.flight.parachuteEvents:
+            triggerTime = event[0]
+            parachute = event[1]
+            openTime = triggerTime + parachute.lag
+            velocity = self.flight.freestreamSpeed(openTime)
+            altitude = self.flight.z(openTime)
+            name = parachute.name.title()
+            print(name + " Ejection Triggered at: {:.3f} s".format(triggerTime))
+            print(name + " Parachute Inflated at: {:.3f} s".format(openTime))
+            print(
+                name
+                + " Parachute Inflated with Freestream Speed of: {:.3f} m/s".format(
+                    velocity
+                )
+            )
+            print(
+                name
+                + " Parachute Inflated at Height of: {:.3f} m (AGL)".format(
+                    altitude - self.flight.env.elevation
+                )
+            )
+        return None
+
+    def impact_conditions(self):
+        """Prints out the Impact Conditions available about the flight.
+
+        Returns
+        -------
+        None
+        """
+        if self.flight.postProcessed is False:
+            self.flight.postProcess()
+        if len(self.flight.impactState) != 0:
+            print("\nImpact Conditions\n")
+            print("X Impact: {:.3f} m".format(self.flight.xImpact))
+            print("Y Impact: {:.3f} m".format(self.flight.yImpact))
+            print("Time of Impact: {:.3f} s".format(self.flight.tFinal))
+            print("Velocity at Impact: {:.3f} m/s".format(self.flight.impactVelocity))
+        elif self.flight.terminateOnApogee is False:
+            print("End of Simulation")
+            print("Time: {:.3f} s".format(self.flight.solution[-1][0]))
+            print("Altitude: {:.3f} m".format(self.flight.solution[-1][3]))
+
+        return None
+
+    def maximum_values(self):
+        """Prints out the Maximum Values available about the flight.
+
+        Returns
+        -------
+        None
+        """
+        print("\nMaximum Values\n")
+        print(
+            "Maximum Speed: {:.3f} m/s at {:.2f} s".format(
+                self.flight.maxSpeed, self.flight.maxSpeedTime
+            )
+        )
+        print(
+            "Maximum Mach Number: {:.3f} Mach at {:.2f} s".format(
+                self.flight.maxMachNumber, self.flight.maxMachNumberTime
+            )
+        )
+        print(
+            "Maximum Reynolds Number: {:.3e} at {:.2f} s".format(
+                self.flight.maxReynoldsNumber, self.flight.maxReynoldsNumberTime
+            )
+        )
+        print(
+            "Maximum Dynamic Pressure: {:.3e} Pa at {:.2f} s".format(
+                self.flight.maxDynamicPressure, self.flight.maxDynamicPressureTime
+            )
+        )
+        print(
+            "Maximum Acceleration: {:.3f} m/s² at {:.2f} s".format(
+                self.flight.maxAcceleration, self.flight.maxAccelerationTime
+            )
+        )
+        print(
+            "Maximum Gs: {:.3f} g at {:.2f} s".format(
+                self.flight.maxAcceleration / self.flight.env.g,
+                self.flight.maxAccelerationTime,
+            )
+        )
+        print(
+            "Maximum Upper Rail Button Normal Force: {:.3f} N".format(
+                self.flight.maxRailButton1NormalForce
+            )
+        )
+        print(
+            "Maximum Upper Rail Button Shear Force: {:.3f} N".format(
+                self.flight.maxRailButton1ShearForce
+            )
+        )
+        print(
+            "Maximum Lower Rail Button Normal Force: {:.3f} N".format(
+                self.flight.maxRailButton2NormalForce
+            )
+        )
+        print(
+            "Maximum Lower Rail Button Shear Force: {:.3f} N".format(
+                self.flight.maxRailButton2ShearForce
+            )
+        )
+        return None
+
+    def all(self):
+        """Prints out all data available about the Flight.
+
+        Parameters
+        ----------
+        None
+
+        Return
+        ------
+        None
+        """
+
+        # Print initial conditions
+        self.initial_conditions()
+        print()
+
+        # Print surface wind conditions
+        self.surface_wind_conditions()
+        print()
+
+        # Print launch rail orientation
+        self.launch_rail_conditions()
+        print()
+
+        # Print out of rail conditions
+        self.out_of_rail_conditions()
+        print()
+
+        # Print burnOut conditions
+        self.burn_out_conditions()
+        print()
+
+        # Print apogee conditions
+        self.apogee_conditions()
+        print()
+
+        # Print events registered
+        self.events_registered()
+        print()
+
+        # Print impact conditions
+        self.impact_conditions()
+        print()
+
+        # Print maximum values
+        self.maximum_values()
+        print()
+
+        # Print Numerical Integration Information
+        self.numerical_integration_settings()
+        print()
+
+        return None