They are expecting just over 2g accel and 3g decel in a 'perfect' run...
http://www.bloodhoundssc.com/project/adventure/breaking-record
This is where we need to go back to the basic physics. a=F/m and d=-F/m
To accelerate and decelerate to a given speed on a shorter course or a higher speed on the same course, we need less weight. Not more thrust, more engines, and more weight. Less weight, period. The weight required to do the ALSR is much less than assumed by many observers. Rockets beat jets hands down because rockets lose more fuel weight than jets during the run and have less mass at top speed and less mass to decelerate. Deep throttleable rocket engines in the thrust class required are available off the shelf at a TRL of 8+. i.e. one level off the reliability of a production car. The assumption that jets must be used with rockets is analogous to the use of both solid and liquid rockets on the space shuttle. The disadvantages of each type limit the system.
Look at Blue Flame's original specs. The engine design thrust was double what was actually used for the record runs. Even with this handicap, Blue Flame hit the measured mile in a distance that allowed the driver to see the mile entrance from the launch line. Heavy designs cannot do this no matter how much engineering is thrown at them. The post run analysis showed that Blue Flame as designed would have topped out at 870-920 mph depending on the shock drag off the top of the exposed rear wheels (Mach 2.2 relative). Blue Flame was light and simple. It was built using 1960's state of the art steel space frame and aluminum skin. Given today's rocket and carbon construction technology, the same car could be made with 50% greater thrust and Isp with 30% less launch mass. We do the math from this point. Heavy, blunt, and complex vehicles are not in the baseline. When a program starts with a needlessly heavy, complex, and expensive concept it is at a severe disadvantage to a light, simple, and inexpensive design.
5.9 miles 0-1100-0 was our design point, with margin. The analysis has shown the design to be lighter and faster than we have designed for. 4.2G launch, peak at 4.7G at 520 mph as mass is burned off, taper to 3.2G at 1100 mph due to wave drag. Decel profile is symetrical over distance, this requires a multi-stage, fully redundant chute system with each stage capable of surviving the dynamic pressure of the chute two stages above it. Peak G under decel should be under 5.5G.
We're going to hear a lot of howls about these G forces. We interviewed three X-15 pilots and twelve race, aerobatic, and test pilots including Neil Armstrong. Several were candidate drivers for the Fossett LSR. Our G profile is a fraction of that experienced by most experimental test pilots, fighter pilots, and is laughable to unlimited aerobatic pilots.
The assumptions that have limited the understanding of the ALSR for 40 years need to be re-examined. We can do it better, cheaper, faster, and simpler. We just have to want to.