**3.2.4 Apollo capsule**

356 Computational Simulations and Applications

The freestream conditions for each trajectory point are enumerated in Table 3, which are

M U, m/s P, Pa T, K 1.2 351 4519 210 1.4 409 3952 213 2.0 596 2891 219 3.0 903 2073 224 5.0 1532 1238 232 6.0 1890 1064 234

Four types of boundary conditions are required for the computation of flow field, i.e. wall, inflow, outflow and symmetric conditions. They are prescribed as follows. At the solid wall, no-slip condition is enforced together with an isothermal wall condition. At the centre line of the symmetric reentry capsule are prescribed For the supersonic outflow case, all flow

The dimensional detail of the ARD capsule is having an axisymmetric design with a spherical blunt nose diameter, D = 2.8 m, spherical cap radius, RN = 3.36 m and a shoulder radius, RC = 0.014 m. The back shell has inclination angle N = 33 deg relative to the capsule's axis of symmetry. A frustum of cone of radius 0.0507 m with a 12 deg half angle cone is attached to the base region. The overall length of the capsule L = 2.04 m. The ARD

The OREX geometry is depicted in Fig. 2 with the detailed dimension. The fore-body shape consists of RN = 1.35 m, a half-angle cone of N = 50 deg, D = 3.4 m, L = 1.508 m, and RC = 0.01 m. The OREX geometry incorporates a rear cover with a small backward facing step at the junction between back cover and heat shield. The aft body is having B = 15 deg, half-

The dimensional detail of the Beagle-2 in Table 1(a) is of axisymmetric designs. The forebody of the Beagle has a 60 deg half cone with a maximum diameter, D = 0.9 m. The Beagle-2 capsule has a spherical blunt nose radius of R = 0.417 m, and a shoulder radius of RC = 0.029m. The back shell has an inclination angle, B = 43.75 deg relative to the vehicle's axis of symmetry. The overall length of the module is L = 0.4995 m and the length to the

variables are extrapolated at the outer and wake region of the computational region.

resembles a 70% scaled version of the Apollo capsule (Liever et al. 2003).

used as initial conditions. The subscript represents freestream value in Table 3.

**3.1.5 Initial and boundary conditions** 

Table 3. Trajectory points and initial conditions.

angle cone relative to the plane of symmetry.

**3.2 Reentry capsule geometry** 

**3.2.1 ARD capsule** 

**3.2.2 OREX capsule** 

**3.2.3 Beagle-2 capsule** 

diameter ratio is 0.555.

The dimensional detail of the Apollo is shown in Fig. 2 are of axisymmetric designs. The Apollo capsule has a spherical blunt nose diameter of D = 3.95 m, spherical nose radius of N = 4.595 m and a shoulder radius of RC = 0.186 m. The back shell has an inclination angle, B = 32.5 deg relative to the vehicle's axis of symmetry. The overall length of the module is L = 3.522 m.
