**Problem
C2.3.**** Analytical 3D
Body of Revolution**

**Overview **

This problem is aimed at testing high-order methods for the computation of external flow with a high-order curved boundary representation in 3D. Inviscid, viscous (laminar) and turbulent flow conditions will be simulated.

**Governing
Equations**

The governing equations for inviscid and laminar flows are the 3D Euler and Navier-Stokes equations with a constant ratio of specific heats of 1.4 and Prandtl number of 0.72. For the laminar flow problem, the viscosity is assumed a constant.

**Flow
Conditions**

Inviscid: _{ }Laminar: _{ }Turbulent: _{}

**Geometry**

The geometry is a streamlined body based on a 10 percent thick airfoil with boundaries constructed by a surface of revolution. The airfoil is constructed by an elliptical leading edge and straight lines.

Half model:

_{}

Figure 3D Body of Revolution

**Reference values**

Reference area: 0.1 (full model)

Reference moment length: 1.0

Moment line: Quarter chord

**Boundary
Conditions**

Far field boundary: Subsonic inflow and outflow

Wing surface: no slip adiabatic wall

**Requirements**

1. Start
the simulation from a uniform free stream everywhere, and monitor the L_{2} norm of the density residual. Track the work units needed to achieve steady
state. Compute the drag and lift coefficients *c _{d}* and

2. Perform
grid and order refinement studies to find ˇ°convergedˇ± *c _{d}* and

3. Plot
the *c _{d}* and

4. Study
the numerical order of accuracy according to *c _{d}* and

5. Submit two sets of data to the workshop contact for this case

a) *c _{d}* and

b) *c _{d}* and