changes made based on remarks

docs/documentation/analysis/constraint_analysis/index.md

 # Constraint Analysis {#mainpage}
 One of the essential aspects of aircraft design is to size the aircraft to meet the point performance requirement. This process involves the evaluation of the constraints within the Thrust to Weight and Wing Loading design space. As the tool is "sizing" the aircraft, it requires information about the aerodynamic performance of the aircraft and the change of weight throughout the mission. Therefore this tool gets executed at the end of each loop to correctly size the aircraft.
 
-# Baseline Implementation
-The constraint analysis tool is established with an energy based approach which is coming from Jack D. Mattingly's Aircraft Engine Design book.
-
 # Module Configuration
 The module can be configured to meet specific user needs by selecting desired parameters within the program_settings section of the module config file.
 A summary of possible selections can be found below:
@@ -29,6 +26,8 @@ A summary of possible selections can be found below:
 
 - `minimum_climb_rate`: The minimum climb rate required at the service ceiling, CS25 defines this parameter to be 100 ft/min which is equal to 0.508 m/s
 
+- `safety_factor`: The additional percentage increment that is added to the Thrust to Weight ratio
+
 # Module Output
 
 - `Updated Design Point`: An updated Thrust to Weight and Wing Loading pair

docs/documentation/analysis/constraint_analysis/principles.md

@@ -14,6 +14,9 @@ The end-of-the-loop aircraft’s aerodynamic performance is different to that of
 
 Point performance requirements are evaluated as constraints within the $T_{SL}/W_{TO}$ – $W_{TO}/S_{Ref}$ design space. The point is selected to have the minimum $T_{SL}/W_{TO}$ possible value that lies in the feasible space.
 
+# Baseline Implementation
+The constraint analysis tool is established with an energy based approach which is coming from Jack D. Mattingly's Aircraft Engine Design book.
+
 ## Derivation
 
 1\. Lift Equation (getCL):
@@ -233,19 +236,11 @@ weight_fraction_TO (taken from the mission analysis results),
 
 ## Updating the Design Point
 
-min_finder.find_dominant_curve();
-
-double sf = this->configuration_xml->at("module_configuration_file/program_settings/safety_factor/value");
-
-min_finder.find_design_point(sf);
-
-min_finder.update_design_point();
-
 Steps:
 
-1. Find the dominant curve: Takes the max T/W required at each W/S, hence gets the constraining curve
-2. Read the “safety factor” which adds the desired increment to the minimum T/W for additional safety. (CAN BE VARIED EACH ITERATION FOR FASTER CONVERGENCE)
-3. Find the minimum T/W from the dominant curve, get the W/S value corresponding to this T/W
+1. Find the dominant curve: Takes the max $T_{SL}/W_{TO}$ required at each $W_{TO}/S_{Ref}$, hence gets the constraining curve
+2. Read the “safety factor” which adds the desired increment to the minimum $T_{SL}/W_{TO}$ for additional safety.
+3. Find the minimum $T_{SL}/W_{TO}$ from the dominant curve, get the $W_{TO}/S_{Ref}$ value corresponding to this $T_{SL}/W_{TO}$
     1. Not an “optimization”, just a sorting algorithm
     2. Does not interpolate between points
 4. Update the design point
@@ -264,7 +259,10 @@ Steps:
 4. Assemble the constraints
 5. Find the dominant curve
 6. Evaluate the feasible area
-7. Find the minimum T/W from the dominant curve and get the W/S that corresponds to this T/W
+7. Find the minimum $T_{SL}/W_{TO}$ from the dominant curve and get the W/S that corresponds to this $T_{SL}/W_{TO}$
 8. Update the design point
 9. Plot the results
-10. Save the plots
\ No newline at end of file
+10. Save the plots
+
+## Example Output
+![](figures/constraint_plot.png)
\ No newline at end of file