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Co-authored-by: Kristina Mazur <kristina.mazur@tum.de>

docs/documentation/analysis/constraint_analysis/index.md

@@ -17,13 +17,13 @@ A summary of possible selections can be found below:
 
 - `Mach_TO`: The mach number at takeoff
 
-- `takeoff_climb_anlge`: The takeoff climb angle for which the constraint shall be evaluated
+- `takeoff_climb_angle`: The takeoff climb angle for which the constraint shall be evaluated
 
 - `gust_speed`: The gust speed at takeoff for which the constraint shall be evaluated
 
 - `gust_load_factor`: The additional gust load factor for which the constraint shall be evaluated
 
-- `Oswald_factor`: The Oswald factor for calculating the polar, effective only if the aero_method is selected to be Calculate_Polar
+- `oswald_factor`: The Oswald factor for calculating the polar, effective only if the aero_method is selected to be Calculate_Polar
 
 - `climb_gradient_OEI`: The minimum climb rate required for which the constraint shall be evaluated, CS25 defines this parameter to be 2.4% for the second climb segment
 

docs/documentation/analysis/constraint_analysis/principles.md

@@ -12,7 +12,7 @@ The end-of-the-loop aircraft’s aerodynamic performance is different to that of
 
 ## Logic
 
-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.
+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.
 
 ## Derivation