Black Brant Project - Bend Strength

The first step in the process was to determine the maximum dynamic pressure on the rocket. This was done by dividing the force on the nose cone (DRAG) by it's equivalent flat plat area.
		Maximum Drag on the rocket
		Nose cone drag equals 40% of the total drag and has a CD 0f 0.6
		The frontal area of the nose cone
		Maximum Dynamic Pressure
The next step was to determine the total area presented to the air stream when the rocket is at a 90 angle of attack. This will be used to determine the maximum possible loading on the airframe.
		Distance from nose to Center of Pressure Distance from the tip of the nose to the Center of Pressure
		Length of the nose cone (nose cone tip + the transitional section)
		Equivalent length of the nose cone
		Length of the body tube component
		Overall equivalent body length
		Total area of the rocket at 90 degrees
		Drag
Maximum possible loading on the rocket airframe.
		This assumes a 90 degree angle of attack, and a velocity of Mach 1.25