# How does the surface area of a heat shield impact the ideal angle of attack for reentry?

The Apollo command module had a diameter of about 12.8 ft (which I assume is pretty close to the diameter of its heat shield). However, the heat shield for the new Orion spacecraft is a little bigger, at 16.5 ft (again, the diameter of the vehicle itself).

Orion's heat shield. Img credit space.com.

We know that for Apollo 13, the ideal angle of attack was no shallower than 5.3 degrees, and no steeper than 7.7 degrees. I assume that the changed dimensions of the Orion spacecraft make some differences to this - so my question: What difference does the surface area of the heat shield make to the reentry angle?

It's not the surface area by itself. There are two main factors. The first is the ballistic coefficient, $\beta$, which is the mass divided by the product of the surface area and the coefficient of drag: $\beta={m\over C_D A}$. The second is the lift over drag (L/D) of the vehicle, which for these blunt vehicles is usually obtained with an offset center of gravity.
As $\beta$ goes up, the shallowest allowable entry angle goes steeper. Also as $\beta$ goes up, the heating rate goes up, making the steepest angle shallower. At some point you would improve the thermal protection system to allow higher heating at steeper angles to keep that corridor open.
As an approximation, as a vehicle gets larger, the mass goes up as the cube of the size, whereas the area goes up as the square. So you would expect that $\beta$ goes up as the vehicle goes up in size, even though the surface area is increasing. So Orion should have a higher $\beta$ than Apollo.