Update Dynamic_FSI_Python.md

_docs_v7/Build-SU2-Linux-MacOS.md

@@ -132,6 +132,7 @@ Options can be passed to the script to enable or disable different features of S
 | `-Denable-mkl`      |  `false`      |    enable Intel MKL support     |
 | `-Denable-openblas` |  `false`      |    enable OpenBLAS support      |
 | `-Denable-pastix`   |  `false`      |    enable PaStiX support        |
+| `-Denable-mpp`   |  `false`      |    enable Mutation++ support        |
 | `-Denable-mixedprec` | `false`      |    enable the use of single precision on linear solvers and preconditioners |
 
 For example to enable AD support pass the option to the `meson.py` script along with a value:

_docs_v7/SU2-Linux-MacOS.md

@@ -15,7 +15,7 @@ permalink: /docs_v7/SU2-Linux-MacOS/
 ## Installation 
 
 ### Download and unpack the archive
-[Download](/download/) the .zip for your operating system and unzip it where you want it to be installed. 
+[Download](/download.html) the .zip for your operating system and unzip it where you want it to be installed. 
 
 ### Setting Environment variables
 

_docs_v7/Theory.md

@@ -68,7 +68,7 @@ Within the `NAVIER_STOKES` and `RANS` solvers, we discretize the equations in sp
 | --- | --- |
 | `EULER`, `FEM_EULER` | 7.0.0 |
 
-SU2 solves the compressible Euler equations, which can be obtained as a simplification of the compressible Navier-Stokes equations in the absence of viscosty and thermal conductivity. They can be expressed in differential form as
+SU2 solves the compressible Euler equations, which can be obtained as a simplification of the compressible Navier-Stokes equations in the absence of viscosity and thermal conductivity. They can be expressed in differential form as
 
  $$ \mathcal{R}(U) = \frac{\partial U}{\partial t} + \nabla \cdot \bar{F}^{c}(U) - S = 0 $$
 

_tutorials/multiphysics/Unsteady_FSI_Python/Dynamic_FSI_Python.md

@@ -61,7 +61,7 @@ $$
 \end{cases}
 $$
 
-Where $$m$$ is the mass of the airfoil, $$I$$ the inertia around the center of mass, $$S$$ the static moment of inertia at the rotation axis, $$C$$ and $$K$$ the dampings and stiffnesses respectively. $$L$$ and $$M$$ are the lift and pitching up moment.
+Where $$m$$ is the mass of the airfoil, $$I$$ the inertia around the rotation axis, $$S$$ the static moment of inertia at the rotation axis, $$C$$ and $$K$$ the dampings and stiffnesses respectively. $$L$$ and $$M$$ are the lift and pitching up moment.
 
 These equations are usually adimensionalised to obtain results independent from the free-stream density of the flow.
 Indeed, we can define the following parameters: