I was reading Ray Whitford's Design for Air combat and came upon a passage that said that on the SR-71 conical camber "gives a useful reduction in the otherwise very high rolling moment due to sideslip inherent in the highly swept delta wing."
I could not understand how this would happen and dug a little deeper to find a paper NACA RM A56DO2 where as per my understanding the opposite is said.
If what the book says is true, then an aircraft with a conical camber wing flying with the relative wind from the left (sideslip) should roll to the right with less torque/ rate of roll compared to a normal delta wing.
y-axis= Angle of attack Here the wing is facing relative wind 6° off to the left. We can see that the conical cambered wing with relative wind from the left produces a stronger roll to the right compared to a normal wing. The book says the opposite.
The paper further adds that the conical camber increases maximum effective dihedral. Which will again promotes stability. So am I having a brain fart or is this a contradiction?