A review of rigid body response on sting supported models at high angles of incidence

Unsteady aerodynamics: retrospect and prospect

“…This topic is discussed fully in Ref. 22. Current combat aircraft in flight at moderate/high angles of incidence (say a = 20-30°) encounter a wide range of unsteady handling problems, such as wing rock, wing drop or nose slice ( Fig.…”

“…This fact has serious implications for the stability of a sting-supported model and the levels of structural damping required, as discussed in Ref. 22.…”

“…One change recommended is to increase the structural damping in the mode. In the tests of Ref 22. the damper provided only increases the structural damping from 0-4% critical to 1% critical and this increase is achieved only over a small range of heave amplitude.…”

“…Effect of damper on sting bending at f = 6-7Hz for M= 0-5, q = 7-5kN/M° to break the balance or to cause structural failures at the high kinetic pressures required to generate high Reynolds numbers. The risk of failures may be reduced by a number of changes in model design and test procedures recommended in Ref 22…”