diff --git a/docs/documentation/sizing/tank_design/getting_started.md b/docs/documentation/sizing/tank_design/getting_started.md
index e7cf0a150825e2bf1a77c16bd4fbdd7fde0199b1..15df93fb585dab650f153dc5b6a1067ed7cb6cae 100644
--- a/docs/documentation/sizing/tank_design/getting_started.md
+++ b/docs/documentation/sizing/tank_design/getting_started.md
@@ -48,12 +48,12 @@ To single execute the _tank\_design_ module, we need an _acXML_ file that alread
 <sup>*</sup> The _tank\_design_ execution is also possible without mission analysis data. Alternatively, the following assumption is used to calculate the mission fuel amount:
 
 $$
-    m_{fuel} = n_{PAX} \cdot R \cdot \frac{E}{100 \text{ km}}
+    m_{\text{fuel}} = n_{\text{PAX}} \cdot R \cdot \frac{E}{100 \text{ km}}
 $$
 
 In which
 
-- $n_{PAX}$ - number of passengers
+- $n_{\text{PAX}}$ - number of passengers
 - $R$ - range in km
 - $E$  - energy demand (3.35 liter per PAX per 100 km)
 
diff --git a/docs/documentation/sizing/tank_design/tank_design_method.md b/docs/documentation/sizing/tank_design/tank_design_method.md
index dd7c72b4e9c8b65f7740fba5b8aad1e40fa6343c..b500e8964cffd2544b563c777be0223942d2393f 100644
--- a/docs/documentation/sizing/tank_design/tank_design_method.md
+++ b/docs/documentation/sizing/tank_design/tank_design_method.md
@@ -1,5 +1,6 @@
 # Calculation method
 The task of the _tank_design_ module differs slightly depending on the energy carrier:
+
 - [Kerosene](#kerosene-tanks) - Determine the maximum fuel capacity of the aircraft using its geometry.
 - [Liquid hydrogen](#liquid-hydrogen-tanks) - Size tanks to ensure that the required amount of fuel is available.
 
@@ -53,10 +54,13 @@ The user can select the desired method via the following node in the `program_se
 ![](figures/02_obelisk.png)
 
 The volume can be calculated using the following equation:
-$
+
+$$
     V_{\text{obelisk}} = \frac{l}{3} \cdot \left( S_1 + S_2 + \frac{h_1 \cdot w_2 + h_2 \cdot w_1}{2}\right)
-$
+$$
+
 In which
+
 - $l$ - length
 - $S_1$, $S_2$ - end face areas
 - $h_1$, $w_1$  - height and width of end face $S_1$
@@ -91,9 +95,10 @@ The Simpson's rule is a method of numerical integration that is often used to ca
 cross-sections are known at different positions. In the case of an obelisk - i.e. a body with square or rectangular 
 cross-sections that vary along the height - the volume is integrated as the sum of the cross-sectional areas $S(x)$
 along the length $l$:
-$
+
+$$
     V_{\text{obelisk}} = \int_0^l S(x) \, dx
-$
+$$
 
 If the cross-sectional areas $S(x)$ at $i+1$ uniformly distributed points are known (which is the case for the 
 tank design), Simpson's rule can be applied.
@@ -104,35 +109,39 @@ interpolation (see following figure). Each tank is thus divided into two section
 ![](figures/02_obelisk_simpson.png)
 
 The tank volume can therefore be determined using a simplified Simpson's rule:
-$
+
+$$
     V_{\text{obelisk}} = \frac{l}{6.0} \cdot (S_{1} + 4.0 \cdot S_{12} + S_{2})
-$
+$$
 
 #### Calculate net tank volume {#net-tank-volume}
 The volume must then be converted from cubic meter to liter. A portion of the volume of the obelisk is lost to the internal structure of the integral tanks (e.g., ribs), with a reduction factor $ f_{\text{volume,usable}} = 0.95$.
 Additionally, the expansion of the fuel due to heating must be considered, with a temperature expansion allowance of $ a_{\text{temperature,expansion}} = 0.95$. Thus, the wing tank volume is calculated as:
-$
+
+$$
     V_{\text{tank}} = f_{\text{volume,usable}} \cdot a_{\text{temperature,expansion}} \cdot V_{\text{obelisk}}
-$
+$$
 
 !!! note 
     As the wing has a vent tank at each wing tip to allow for the thermodynamic expansion of the fuel, this factor is `1.0` for the wing tanks.
 
 #### Calculate energy {#calculate-energy}
 Using the volumetric energy density of kerosene $\eta_{\text{v,kerosene}}$, the energy contained in each tank can be determined:
-$
+
+$$
     V_{\text{tank}} = \eta_{\text{v,kerosene}} \cdot V_{\text{obelisk}}
-$
+$$
 
 ### Additional center tank
 The module allows the installation of an additional center tank in the form of an LD3-45 container. The process includes the following steps:
+
 1. **Height check**: The program first verifies whether the cargo compartment has sufficient height to accommodate the container.
-  - If insufficient height is detected: All output values related to the center tank are set to zero.
-  - If sufficient height is detected: The installation proceeds.
+    - If insufficient height is detected: All output values related to the center tank are set to zero.
+    - If sufficient height is detected: The installation proceeds.
 2. **Installation placement**: The LD3-45 container is positioned 10 cm behind the end of the landing gear bay, aligning approximately with the trailing edge of the wing.
 3. **Container data**: The volume and dimensions of the LD3-45 container are predefined and referenced from the Lufthansa Cargo website<sup>[2]</sup>.
 
-The energy contained in an additional center tank is calculated by first determining the usable volume and then taking into account the volumetric energy density of kerosene. With the known factors $ f_{\text{volume,usable}}$ and $a_{\text{temperature,expansion}}$, the usable volume of an additional center tank results in $V_{\text{ACT,usable}} = 3068.5\text{ L}$ which is equal to an energy amount of $ E_{\text{ACT}} = 99189262.5\text{ MJ}$.
+The energy contained in an additional center tank is calculated by first determining the usable volume and then taking into account the volumetric energy density of kerosene. With the known factors $ f_{\text{volume,usable}}$ and $a_{\text{temperature,expansion}}$, the usable volume of an additional center tank results in $V_{\text{ACT,usable}} = 3,068.5\text{ L}$ which is equal to an energy amount of $ E_{\text{ACT}} = 99,189,262.5\text{ MJ}$.
 
 #### Limitations
 **Single Center Tank Limit:** The program currently supports the calculation of only one additional center tank. Attempts to add more tanks will not be processed.