1.)  ¹Heating Rate Equation

Q_max  <  70 Btu / Ft.²-Sec.

k  = 4.4695199x10^-9

r = Gas Density (Slugs / Ft.³)
V = Velocity (Ft. / Sec.)

2.)  Normal Acceleration Equation

a_n = L cos a + D sin a

a_{n max}  <  2.5 G

L  = Aerodynamic Lift.  See Eqn. A3-1
D  = Aerodynamic Drag.  See Eqn. A3-2

a = Angle of Attack (Degrees)

3.)  Dynamic Pressure Equation

q = ¹/₂ rV ²

q_max   <  300 psf

r = Gas Density (Slugs / Ft.³)
V = Velocity (Ft. / Sec.)

1. Determined empirically during Space Shuttle flights and is based on a one dimensional adiabatic steady state heating model.  It is the heating rate for stagnation regions of the shuttles surface during high Mach number reentry atmospheric flight.