Quote:
Originally Posted by 41Sqn_Banks
But this is nothing special about the Spitfire. Each aircraft has it's structural limits, exceeding these limits damages/destroys the aircraft. As you say the critical situations might be different for each aircraft.
The problem is not the Spitfire, the problem is that structural limits are not simulated.
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Question.
One aircraft has a stick force gradient of 4 lbs/g, the other has a stick force gradient of 20lbs/g.
Question 1.
In which aircraft is it easier for the pilot to reach the actual break point of ca. 10-12 g?
Question 2.
Is it possible for the aircraft which has a stick force gradient of 4 lbs/g to actually reach that 10-12 g load at which the airframe is likely to break?