What type of airfoil do low-supersonic aircraft use?
Normally, supersonic fighter wings for which airfoil information is published use a very thin NACA 6-series section with very little camber, such as
Aircraft                root airfoil      tip airfoil
McDonnell Douglas F-15  NACA 64A006.6     NACA 64A203
General Dynamics F-16   NACA 64A204       NACA 64A204
Lockheed-Martin F-22    NACA 64A?05.92    NACA 64A?04.29

This information is from The Incomplete Guide to Airfoil Usage by Dave Lednicer. As you can see, the F-16 uses camber throughout, indicated by the 0.2 design lift coefficient of the airfoil, while the F-15 uses an uncambered root airfoil.
Those airfoils are chosen because flow around them at supersonic flight speed is still heavily influenced by subsonic flow characteristics* as long as wing sweep allows for a subsonic leading edge. This produces nose suction which is very helpful to keep drag down. Delta wing aircraft enhance this nose suction by cambering the outboard leading edge (conical camber).
Common to all supersonic wings is their minimization of wing thickness, because wave drag will grow with the square of thickness. Typical sections use a relative thickness between 4% and 6%. In case of the F15, thickness varies between 6.6% at the root and 3% at the tip.
Supercritical airfoils work best in a narrow Mach and angle of attack range and are used for transsonic designs (flight Mach number between 0.7 and 1.0). Fighter aircraft with their wide variety of speeds and angles of attack will rarely profit from using them. The strongly negative pitching moment of supercritical airfoils (resulting from rear loading) makes them unsuitable for most fighter designs.
Supersonic airfoils are reserved for designs with a supersonic leading edge, like the F-104 or X-15 wings and tail or the XB-70 canard. They are only used if top speed exceeds Mach 2.2 and the sweep necessary for a subsonic leading edge would be too high for decent subsonic performance.

* For those with a severe problem of reading comprehension: Of course the flow over a swept wing is supersonic when the airplane moves at supersonic speed. Only the behavior of the flow is like that at subsonic speed as long as LE sweep is higher than the Mach cone angle.