For Gemini, Apollo, and Soyuz capsules, lift is achieved by offsetting the center of gravity of the reentry module from the center line of the craft. This is represented in your diagram by the "location of heavy equipment" callout, and results in the tilt of the capsule relative to the flight trajectory shown. The tilt causes the body of the spacecraft itself to act as an airfoil, giving the lift vector shown. By rolling the spacecraft from side to side with the RCS, the direction of the lift vector can be adjusted. With the lift axis more vertical, the spacecraft will fly longer and further. Rolling side to side causes the lift force to be applied sideways, trading off downrange distance for crossrange. With positive vertical lift, the spacecraft stays in less dense air for longer, reducing the peak g-force sustained by the crew. The Mercury capsule, having a zero-lift profile, took about 11g on reentry, while the Apollos did 6-7g.
It would be possible to add body-flap control surfaces to such a capsule for finer control, but since the initial conditions of reentry are quite well controlled, and the landing point doesn't need to be ultra-precise, it hasn't been done for this type of capsule.
The US Space Shuttle, of course, had much more complex aerodynamic control surfaces.