Work on hypersonic propulsion research using a ram accelerator is presented. Several different ram accelerator propulsive cycles have been experimentally demonstrated over the Mach number range of 3 to 8.5. The subsonic, thermally choked combustion mode has accelerated projectiles to near the Chapman-Jouguet (C-J) detonation velocity within many different propellant mixtures. In the transdetonative velocity regime (85 to 115 percent of C-J speed), projectiles have established a propulsive cycle which allows them to transition smoothly from subdetonative to superdetonative velocities. Luminosity data indicate that the combustion process moves forward onto the projectile body as it approaches the C-J speed. In the superdetonative velocity range, the projectiles accelerate while always traveling faster than the C-J velocity. Ram accelerator projectiles operating continuously through these velocity regimes generate distinctive hypersonic phenomena which can be studied very effectively in the laboratory. These results would be very useful for validating sophisticated CFD computer codes and in collecting engineering data for potential airbreathing hypersonic propulsive systems.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Experiments on hypersonic ramjet propulsion cycles using a ram accelerator


    Contributors:
    Chew, G. (author) / Knowlen, C. (author) / Burnham, E. A. (author) / Hertzberg, A. (author) / Bruckner, A. P. (author)

    Publication date :

    1991-06-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English