updated tutorials for clarity and removed unusable ones (may be brought back later)

Author: timdmacdo

_posts/2015-06-14-Boeing_737-800.md

@@ -18,11 +18,11 @@ This tutorial shows how the user can setup a conventional configuration aircraft
 
 ### Steps to simulate the aircraft's performance over a mission :
 
-1) Locate the tutorial script folder, /Tutorials, from your project folder as described in the Download guide. If using the command line, cd to this directory.
+1) Locate the folder where you have the tutorial repository. If using the command line, cd to this directory.
 
 2) Open the tut_mission_B737.py script in your favorite editor or IDE. The script is setup to run the B737 on its design mission. Run it in your IDE. If using the command line use the command
 
-<pre><code class="python"> $python tut_mission_B737_800.py  </code></pre>
+<pre><code class="python"> python tut_mission_B737_800.py  </code></pre>
 
 3) A few plots depicting the variation of the different aircraft performance parameters over the course of the mission are shown.
 

_posts/2015-06-15-Lithium_Air_Regional_Jet_Sizing.md

@@ -14,12 +14,12 @@ permalink: /guides/turbofan_network.html
 
 ## Turbofan Modeling Tutorial
 
-The tutorial describes how the energy network in SUAVE can be used to build a model of a turbofan engine. Once this is clear to the user, then the understanding the setup of the other gasturbine models, the ducted fan and the turbojet should not be very difficult. The turbofan model is built using the different turbofan components as its building blocks and then linking the inputs and outputs of the different components. The script to follow is the tut_mission_B737.py script that was used in the [Boeing 737-800 Analysis Tutorial](/guides/boeing_737-800.html)
+This tutorial describes how the energy network framework in SUAVE can be used to build a model of a turbofan engine. Once this is clear to the user, understanding the setup of the other gasturbine models, the ducted fan and the turbojet will be much easier. The turbofan model is built with several turbofan components as its building blocks. These are then linked together through their inputs and outputs. The script to follow is the tut_mission_B737.py script that was used in the [Boeing 737-800 Analysis Tutorial](/guides/boeing_737-800.html)
 
 
 ### Setting up the Turbofan model
 
-First the turbofan energy energy network is instantiated. The parameters associated with the network as a whole are assigned.
+First the turbofan energy network is instantiated. The parameters associated with the network as a whole are assigned.
 
 <pre><code class="python"># ------------------------------------------------------------------
 #   Turbofan Network
@@ -42,14 +42,14 @@ turbofan.working_fluid = SUAVE.Attributes.Gases.Air()
 Then the different components are added
 
 
-### Components :
+### Components
 
 The basic components used to model the turbofan are described below.
 
 
 #### Ram
 
-The 'Ram' component is used to convert the freestream quantities that are passed into the Turbofan network into stagnation quantities. As the turbofan network is based on a 1D gasdynamic analysis, most of the energy transfer across the different components are modelled as changes in the stagnation quantities. Thus the Ram component acts as a preprocessor converting the input 'Conditions' into quantities required by the network.
+The 'Ram' component is used to convert the freestream quantities that are passed into the turbofan network into stagnation quantities. As the turbofan network is based on a 1D gasdynamic analysis, most of the energy transfer across the different components are modelled as changes in the stagnation quantities. Thus the Ram component acts as a preprocessor converting the input conditions into quantities required by the network.
 
 <pre><code class="python"># ------------------------------------------------------------------
 #   Component 1 - Ram
@@ -66,7 +66,7 @@ turbofan.append(ram)
 
 #### Nozzle
 
-The 'Nozzle' component is used to model the inlet diffuser and the outlet fan and compressor nozzles as shown below.
+The 'Nozzle' component is used to model the inlet diffuser, the outlet fan, and the compressor nozzles as shown below.
 
 
 <pre><code class="python"># ------------------------------------------------------------------
@@ -147,7 +147,7 @@ turbofan.append(compressor)
 
 #### Fan
 
-A fan component is also added to the network. To model turbojets, the fan component and the fan nozzle are not added but all the other components remain the same.
+A fan component is also added to the network. If you were to model a turbojet, the fan component and the fan nozzle would not be added but all the other components would remain the same.
 
 <pre><code class="python"># ------------------------------------------------------------------
 #  Component 10 - Fan
@@ -167,7 +167,7 @@ turbofan.append(fan)
 
 #### Combustor
 
-The combustor component is where the the fuel to air ratio is computed and this is used to compute the sfc and the thrust later in the network.
+The combustor component is where the the fuel to air ratio is computed. It is also used to compute the sfc and the thrust later in the network.
 
 <pre><code class="python"># ------------------------------------------------------------------
 #  Component 7 - Combustor
@@ -178,7 +178,6 @@ combustor.tag = 'combustor'
 
 # setup
 combustor.efficiency                = 0.99 
-combustor.alphac                    = 1.0     
 combustor.turbine_inlet_temperature = 1450
 combustor.pressure_ratio            = 0.95
 combustor.fuel_data                 = SUAVE.Attributes.Propellants.Jet_A()    
@@ -246,7 +245,7 @@ turbofan.thrust = thrust
 
 ### Sizing the Turbofan
 
-Once the network is built, it is essential to size the engine with a set of sizing conditions. The sizing function 'turbofan_sizing' takes in the model of the turbofan and the mach number and the altitude for which the turbofan is sized. The sizing thrust is an engine/network property (defined in the 'Setting up the Turbofan model' section above. The function takes these quantities and computes the design mass flow rate through the components. Once sized, the network/engine can be added to the vehicle as shown in the  B737 tutorial.
+Once the network is built, it is essential to size the engine with a set of sizing conditions. The sizing function 'turbofan_sizing' takes in the model of the turbofan and the mach number and the altitude for which the turbofan is sized. The sizing thrust is an engine/network property (defined in the 'Setting up the Turbofan model' section above). The function takes these quantities and computes the design mass flow rate through the components. Once sized, the network/engine can be added to the vehicle as shown in the  B737 tutorial.
 
 <pre><code class="python">#bypass ratio  closer to fan
 

_posts/2015-06-15-Turbofan_Network.md

@@ -9,18 +9,18 @@ permalink: /guides/payload_range_diagram.html
 ---
 
 ### Embraer E-190 Payload Range Diagram Tutorial
-1) Locate the tutorial script folder. If necessary cd to this directory.
+1) Locate the tutorial script folder.
 
 2) Open the test_payload_range.py script in your favorite editor or IDE.
 
-3) Similar to the B737-800 Tutorial, the setup is divided into steps, but in this case the setup is imported from other script (test_mission_Embraer_E190_constThr).
+3) Similar to the B737-800 Tutorial, the setup is divided into steps.
 
 4) For the Payload Range Diagram, besides the vehicle and mission, the user must provide the following inputs:
 
-* **cruise_segment_tag**: You must inform the tag of the segment that will have the length modified in order to comply with required fuel burn for each one of the payload range diagram points.
+* **cruise_segment_tag**: You must enter the tag of the segment which will have its length modified in order to comply with required fuel burn for each one of the payload range diagram points.
 * **reserves**: This will be considered as a fixed fuel reserve for all the diagram points.
 
-5) The tutorial presents the following definition (line 36):
+5) The tutorial presents the following definition:
 
 ~~~
 # run payload diagram	
@@ -29,21 +29,16 @@ reserves = 1750.
 payload_range_results = payload_range(vehicle,mission,cruise_segment_tag,reserves)
 ~~~
 
-6) First, let's just run it as it is for now. Run the script in either the IDE or in a terminal: 
+6) First, let's just run it as it is for now. Run the script in either the IDE or in a terminal as `python tut_payload_range.py`
 
-~~~
-$python tut_payload_range.py 
-~~~
-
-7) After all the calculation the payload diagram will be ploted, and the data will be stored in a file named 'PayloadRangeDiagram.dat', in the folder where you run the script.
+7) After the calculations are completed, the payload diagram will be plotted and the data will be stored in a file named 'PayloadRangeDiagram.dat'. This is in the folder where you run the script.
 
-8) You can try to modify vehicle and/or mission parameters, e see how the payload range diagram is affected. For now, let's add some drag counts to the airplane:
+8) You can try to modify vehicle and/or mission parameters and see how the payload range diagram is affected. For now, let's add some drag counts to the airplane:
 
 * Locate and open the script test_mission_Embraer_E190_constThr.py, in the tutorial folder (this is the script that contains the vehicle and mission setups)
-* Locate ``` base_analysis() ``` and then the Aerodynamics Analysis text block (line 144) 
-* Add 50 drag counts to the vehicle (line 132): <br>
-`aerodynamics.settings.drag_coefficient_increment = 0.0050 `
+* Locate ``` base_analysis() ``` and then the Aerodynamics Analysis text block (line 113) 
+* Add 50 drag counts to the vehicle (line 115): `aerodynamics.settings.drag_coefficient_increment = 0.0050 `
 * Rerun the script as before and notice the changes in the results.
 
-9) Similarly the mission parameters can be changed. Again, let's the user decide what changes they want to explore.
+9) Similarly the mission parameters can be changed. Again, this lets the user decide what changes they want to explore.