diff --git a/docs/assets/css/unicado.css b/docs/assets/css/unicado.css
index 88372568650c79e24c080e4488fc1663cc942c40..8c612d43564dd53cc8e6fc1cba976cbd31b775df 100644
--- a/docs/assets/css/unicado.css
+++ b/docs/assets/css/unicado.css
@@ -37,6 +37,21 @@
   font-size: 1.1em;
 }
 
+/* Make all LaTeX-style math equations white */
+:root {
+  --math-color: #ffffff; /* Set the default color for equations */
+}
+
+/* MathJax equations */
+.MathJax, mjx-container, math {
+  color: var(--math-color) !important;
+}
+
+/* KaTeX equations */
+.katex, .katex-display {
+  color: var(--math-color) !important;
+}
+
 /* Download button styling */
 .download-button-container {
   text-align: center;
diff --git a/docs/documentation/sizing/propulsion_design/engineering_principles.md b/docs/documentation/sizing/propulsion_design/engineering_principles.md
index 3ee23c713be64de6c58142ff1c3b54d11fb0e979..8af8f50a8cf03ea42ca0ddd57c5fc31028aae6d7 100644
--- a/docs/documentation/sizing/propulsion_design/engineering_principles.md
+++ b/docs/documentation/sizing/propulsion_design/engineering_principles.md
@@ -20,6 +20,15 @@ For these five disciplines, you can choose different methods of calculating thei
 | **Mass analyzer**        | *Default*                                                         |
 
 
+For these five disciplines, you can choose different **methods** (or fidelities) of calculating their output. Here is an overview of the current implemented methods (details see sections):
+
+| Discipline          | Methods                                                           |
+|---------------------|-------------------------------------------------------------------|
+|Engine designer      | *Rubber* (*Empirical* and *PropulsionSystem* are in preparation)  |
+|Propulsor integrator | *Default*                                                         |
+|Nacelle designer     | *Default*                                                         |
+|Pylon designer       | *Default*                                                         |
+|Mass analyzer        | *Default*                                                         |
 
 If you want to learn more about how to configure methods or generally the settings and outputs, go to the [getting started](getting-started.md).
 
@@ -55,19 +64,15 @@ The _scale factor_ is necessary for the rubber method as it uses the concept of
 
 The scaling is based on continuity principle assuming that the engine characteristics are constant.
 
-$T = \dot{m} \cdot (V_9 - V_0)$
+$$ \textcolor{white}{T = \dot{m} \cdot (V_9 - V_0)} $$
 
-Therefore, thrust $T$ is proportional to the mass flow $\dot{m}$, which is linearly related to the cross-sectional area $A$ of the engine.
+Therefore, thrust $T$ is proportional to the mass flow $\dot m$, which is related to the cross-sectional area $A$ of the engine. 
 
-\[
-\dot{m} = \rho \cdot V \cdot A = \rho \cdot V \cdot \pi \frac{d}{2}^2
-\]
+$$ \dot m = \rho \cdot V \cdot A = \rho \cdot V \cdot \pi \frac{d}{2}^2 $$
 
-Because area $A$ is proportional to the square of the diameter $d$, it follows that the diameter should be proportional to the square root of the scale factor.  
+Because area $A$ is proportional to the square of the diameter $d$ , it follows that the diameter should be proportional to the square root of the scale factor. 
 
-\[
-d_{\text{new}} = d_{\text{ref}} \cdot \left( \frac{T_{\text{new}}}{T_{\text{ref}}} \right)^{0.5}
-\]
+$$ \textcolor{white} d_{new} = d_{ref} \cdot ( \frac{T_{new}}{T_{ref}} )^{0.5} $$
 
 An exemplary simplified calculation (data from the V2527-A5): the current engine provides $127.27~\text{kN}$ as sea level static thrust, but for the design only $100~\text{kN}$ are needed. The scaling factor would be $0.7857$. Assuming an initial diameter $2~\text{m}$, the new diameter would be $1.773~\text{m}$ with the scaling factor of $(0.7857)^{0.5} = 0.8864$.
 
@@ -108,16 +113,15 @@ Here, currently only one method is implemented:
 
 This method includes multiple empirical functions for different propulsion integration. These are the options that are currently implemented:
 
-| Parent     | Lateral | Longitudinal | Vertical |
-|------------|---------|--------------|----------|
-| Wing       | Right   | Front        | Under    |
-| Wing       | Left    | Front        | Under    |
-| Wing       | Right   | Front        | Over     |
-| Wing       | Left    | Front        | Over     |
-| Fuselage   | Right   | Rear         | Mid      |
-| Fuselage   | Left    | Rear         | Mid      |
-| Empennage  | Mid     | Front        | In       |
-
+| Parent    | Lateral | Longitudinal | Vertical |
+|-----------|---------|--------------|----------|
+| Wing      | Right   | Front        | Under    |
+| Wing      | Left    | Front        | Under    |
+| Wing      | Right   | Front        | Over     |
+| Wing      | Left    | Front        | Over     |
+| Fuselage  | Right   | Rear         | Mid      |
+| Fuselage  | Left    | Rear         | Mid      |
+| Empennage | Mid     | Front        | In       |
 
 For detailed information, it is referred to the thesis.