Part of why wing tips were movable...down to create the compression. Am i correct Sir Ski? Going on gut here.
Yeah, quite a design huh?
Called "Compression Lift"
First of:
-The Criteria set by the Customer (USAF) were:
Cruise Speed of Mach 3 (2,000mph)
Cruise Altitude of 70,000 feet
A "shirtsleeve" environment for the crew.
50,000 pound payload
A range of 7,500 miles
Sized such that existing runways, hangars, etc. that had already been built for the B-52 could be used without further modification.
Have flying characteristics suitable for use with average USAF line crewmen
With this in mind, research went into full swing between Boeing and North American (Rockwell).
**It was North American that "found" old research papers from NACA which described the theory of COMPRESSION LIFT.
In flight, the XB-70 could lower the outer wing sections either 25 degrees for flying from 300 knots to Mach 1.4, or a severe 65 degrees for speeds from Mach 1.4 to Mach 3+. Measuring just a bit over 20 feet at the trailing edge, these wingtips represent the largest movable aerodynamic device ever used.
Lowering the wingtips had three distinct effects on the XB-70.
Total vertical area was increased, allowing shorter vertical stabilizers than would otherwise be needed.
The reduction in rearward wing area countered the delta wing's inherent rearward shift of the center of lift as speed increased, keeping drag-inducing trim corrections to a minimum.
Compression lift was
30 percent more effective because the pressure under the wing was better managed