What is the NACA Series of the Rockwell B-1b's wing design?

Question

I can't find any information about the airfoil of the Rockwell B-1b. It's listed as a NACA 69-190-2, which doesn't follow the conventional format of the 6-Series airfoils. I'm assuming its a design unique to Rockwell but I thought it would still be listed in the airfoiltools database. I cannot find any information about it. Jane's has a write up in the 86-87 edition but only mentions the leading edge dimensions.

From Jane's:

Wings: Cantilever low-wing fail-safe blended wing body structure, with variable geometry on outer panels. ...

Each of the outer wing panels, which have 15" of leading-edge sweep when fully forward and 67" 30' when fully swept, is a conventional two-spar aluminium alloy torsion box structure, with machined spars, ribs, and one-piece integrally stiffened top and bottom skin panels.

Full span seven-segment leading-edge slats on each outer panel can be drooped 20" for take-off and landing.

Six-segment single-slotted trailing-edge flaps on each outer panel, with maximum downward deflection of 40°.

Answer 1

It is not listed as NACA ..., it is listed as NA 69-190-2. When the development contract for the B1 was awarded in 1970, North American and Rockwell had already merged. Hence, I am assuming that NA stands for North American and that it is a proprietary airfoil. Since the B1 flies at high subsonic speeds when the wings are extended, I would assume that the airfoil is a supercritical one, which also rules out a NACA 6-series airfoil.