Small typos.

Author: economon

_tutorials/compressible_flow/UQ_NACA0012.md

@@ -27,7 +27,7 @@ The following tutorial will walk you through the steps required when using the E
 
 ### Background
 
-This test case is for the NACA 0012 airfoil in viscous flow. This is a simple 2D geometry that stalls, and exhibits seperated flow, at high angles of attack. It is a ubiquitous geometry that has significant amounts of experimental data available that allows for the comparison of lower fidelity RANS CFD simulations, to the higher fidelity wind tunnel tests that have been conducted. 
+This test case is for the NACA 0012 airfoil in viscous flow. This is a simple 2D geometry that stalls, and exhibits separated flow, at high angles of attack. It is a ubiquitous geometry that has significant amounts of experimental data available that allows for the comparison of lower fidelity RANS CFD simulations, to the higher fidelity wind tunnel tests that have been conducted. 
 
 The EQUiPS module uses the Eigenspace Perturbation methodology to estimate the uncertainties arising from RANS turbulence closures. This involves perturbing the eigenvalues and eigenvectors of the Reynolds stress tensor to explore the extremal states of componentality, and turbulence production of the flow. Utilizing 5 differently perturbed flow simulations, in addition to a baseline unperturbed flow simulation, the module provides interval estimates on the quantities of interest. Each perturbed simulation results in a different realization of the flow field, and by extension, a different realization of the QoIs. The interval bounds are formed by the maximum and minimum values the QoIs resulting from these 6 simulations.
 

_tutorials/incompressible_flow/Inc_Inviscid_Hydrofoil.md

@@ -82,7 +82,7 @@ The inlet condition is prescribed as a uniform velocity inlet, where the velocit
 
 The format for the uniform velocity inlet boundary condition is (marker name, temperature, velocity magnitude, x-component of flow direction, y-component of flow direction, z-component of flow direction), where the final three components make up a unit flow direction vector (magnitude = 1.0). In this problem, the flow is exactly aligned with the x-direction of the coordinate system, and thus the flow direction vector is `(1.0, 0.0, 0.0)`. We are not solving the energy equation for this inviscid problem, so the temperature input value is ignored.
 
-The pressure outlet condition is prescibed as a uniform static (gauge) pressure. Note that, in the incompressible solver, the pressure variable is interpreted as a dynamic pressure instead of the thermodynamic pressure, as in the compressible solver. Therefore, the specified outlet pressure is a gauge value relative to the operating pressure, which is typically taken as the local atmospheric value at the outlet, and thus, the gauge pressure at the outlet is often set to 0.0 Pa. 
+The pressure outlet condition is prescribed as a uniform static (gauge) pressure. Note that, in the incompressible solver, the pressure variable is interpreted as a dynamic pressure instead of the thermodynamic pressure, as in the compressible solver. Therefore, the specified outlet pressure is a gauge value relative to the operating pressure, which is typically taken as the local atmospheric value at the outlet, and thus, the gauge pressure at the outlet is often set to 0.0 Pa. 
 
 ### Running SU2