From 9b22cc818ad9eaabac2f3b080ec43b5965436a0e Mon Sep 17 00:00:00 2001
From: Alfin Johny <alfin.johny@tum.de>
Date: Tue, 4 Feb 2025 15:23:36 +0100
Subject: [PATCH 1/4] Fix incorrectly displyed math equations with .
---
.../sizing/propulsion_design/engineering_principles.md | 8 ++++----
1 file changed, 4 insertions(+), 4 deletions(-)
diff --git a/docs/documentation/sizing/propulsion_design/engineering_principles.md b/docs/documentation/sizing/propulsion_design/engineering_principles.md
index 0a8220b..51bfec5 100644
--- a/docs/documentation/sizing/propulsion_design/engineering_principles.md
+++ b/docs/documentation/sizing/propulsion_design/engineering_principles.md
@@ -47,15 +47,15 @@ The _scale factor_ is necessary because (as conceptual aircraft designer), we us
So, the scaling is based on continuity principle assuming that the operating condition is constant (commonly known station numbering; assuming no pressure drop).
-$ 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 related to the cross-sectional area $A$ of the engine.
+Therefore, thrust $T$ is proportional to the mass flow $\textcolor{white}{\dot{m}}$, 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 $
+$ \textcolor{white}{\dot{m}} = \rho \cdot V \cdot A = \rho \cdot V \cdot \pi \left(\frac{d}{2}\right)^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.
-$ d_{new} = d_{ref} \cdot ( \frac{T_{new}}{T_{ref}} )^{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 $127.27~kN$ as sea level static thrust, but for the design only $100~kN$ are needed. The scaling factor would be $0.7857$. Assuming an initial diameter $2~m$, the new diameter would be $1.773~m$ with the scaling factor of $(0.7857)^{0.5} = 0.8864$.
--
GitLab
From 5469891e90e5934f7f6c523bd8560df2c9104e32 Mon Sep 17 00:00:00 2001
From: Alfin Johny <alfin.johny@tum.de>
Date: Wed, 5 Feb 2025 09:56:24 +0100
Subject: [PATCH 2/4] Fix math equation rendering issues
---
docs/assets/css/unicado.css | 15 +++++++++++++++
1 file changed, 15 insertions(+)
diff --git a/docs/assets/css/unicado.css b/docs/assets/css/unicado.css
index 8837256..8c612d4 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;
--
GitLab
From 9199e95568faaf8166e384f1b466f9bf4d9b25b0 Mon Sep 17 00:00:00 2001
From: Alfin Johny <alfin.johny@tum.de>
Date: Mon, 10 Feb 2025 10:33:18 +0100
Subject: [PATCH 3/4] Align math equations to the middle
---
.../sizing/propulsion_design/engineering_principles.md | 6 +++---
1 file changed, 3 insertions(+), 3 deletions(-)
diff --git a/docs/documentation/sizing/propulsion_design/engineering_principles.md b/docs/documentation/sizing/propulsion_design/engineering_principles.md
index 51bfec5..1c15b66 100644
--- a/docs/documentation/sizing/propulsion_design/engineering_principles.md
+++ b/docs/documentation/sizing/propulsion_design/engineering_principles.md
@@ -47,15 +47,15 @@ The _scale factor_ is necessary because (as conceptual aircraft designer), we us
So, the scaling is based on continuity principle assuming that the operating condition is constant (commonly known station numbering; assuming no pressure drop).
-$ \textcolor{white}{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 $\textcolor{white}{\dot{m}}$, which is related to the cross-sectional area $A$ of the engine.
-$ \textcolor{white}{\dot{m}} = \rho \cdot V \cdot A = \rho \cdot V \cdot \pi \left(\frac{d}{2}\right)^2 $
+$$ \textcolor{white}{\dot{m}} = \rho \cdot V \cdot A = \rho \cdot V \cdot \pi \left(\frac{d}{2}\right)^2 $$
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.
-$ \textcolor{white} d_{new} = d_{ref} \cdot ( \frac{T_{new}}{T_{ref}} )^{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 $127.27~kN$ as sea level static thrust, but for the design only $100~kN$ are needed. The scaling factor would be $0.7857$. Assuming an initial diameter $2~m$, the new diameter would be $1.773~m$ with the scaling factor of $(0.7857)^{0.5} = 0.8864$.
--
GitLab
From 4fb7819d07be3e76beda9e3d13d0d1fbbe45b9e1 Mon Sep 17 00:00:00 2001
From: Alfin Johny <alfin.johny@tum.de>
Date: Mon, 10 Feb 2025 11:00:59 +0100
Subject: [PATCH 4/4] Fix documentation issues
---
.../sizing/propulsion_design/engineering_principles.md | 2 ++
1 file changed, 2 insertions(+)
diff --git a/docs/documentation/sizing/propulsion_design/engineering_principles.md b/docs/documentation/sizing/propulsion_design/engineering_principles.md
index 1c15b66..e9cec0d 100644
--- a/docs/documentation/sizing/propulsion_design/engineering_principles.md
+++ b/docs/documentation/sizing/propulsion_design/engineering_principles.md
@@ -10,6 +10,7 @@ Designing the propulsion with this tool includes different engineering disciplin
- [Mass analyzer](#massanalyzer): calculates the mass properties (center of gravity, mass, and inertia) of engine, nacelle, and pylon.
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) |
@@ -89,6 +90,7 @@ Here, currently only one method is implemented:
- *default* is based on a thesis of RWTH Aachen \cite{Ata10}
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 |
--
GitLab