text: is usually conlined 
  to the high angle of attack range and may be 
  a consequence of a configuration that otherwise 
  has very desirable flying qualities. 
  In such a 
  case it would be necessary to provide some 
  to prevent entry 
  automatic control function 
  into the pitch-up range or to provide synthetic 
  stability for the condition. Since the pitch-up 
  is usually a strong instability with a high1 
  rate of divergence, most pilots would not be 
  capable of contending with the condition. At 
  high 4, pitch-up would be of great danger in 
  that structural failure could easily result. At 
  low q, failing flight loads may not result but 
  the strong instability may preclude a successful 
  recovery from the ensuing motion of the, air- 
  plane. 
  
  EFFFCTS OF HIGH MACH NUMBFB 
  
  Certain stability problems are particular to 
  supersonic flight. While most of the problem 
  areas have been treated in particular in previous 
  to review the 
  discussion, it 
  effects of supersonic flight on the various items 
  of stability. 
  
  is worthwhile 
  
  The static longitudinal stability of an air- 
  plane increases during the transition from sub- 
  sonic to supersonic flight. Usually the prin- 
  cipal source of the change in stability is due to 
  the shift of the wing aerodynamic center with 