Cavity door effects on aerodynamic loadings of compressed-carriage store configurations separating from cavities at supersonic speeds

An experimental wind-tunnel investigation has been conducted at supersonic Mach numbers to determine the effects of cavity doors on the aerodynamic characteristics of compressed-carriage store configurations during separation from a shallow box cavity (closed cavity flow) located in a simulated generic parent aircraft. The tests were conducted in the Langley Unitary Plan Wind Tunnel at free-stream Mach numbers of 1.70, 2.00, and 2.65 for a constant Reynolds number per foot of two million. Results are summarized to show the effects of cavity door opening angles, vertical door height, folded and unfolded tail fins, and Mach number on the near-field aerodynamic separation characteristics of a single missile-type store with in-line cruciform wings and tail fins.