Scramjet engine

A scramjet engine comprising:

• a first passage forming member having a first surface;
• and
• a second passage forming member having a second surface opposing to the first surface,
• wherein a passage is formed between the first surface and the second surface to connect a front opening and a rear opening provided downstream of the front opening,
• wherein the passage comprises:
• an upstream zone configured to generate a flow of compressed air obtained by compressing an air taken in through the front opening;
• a combustion zone connected downstream of the upstream zone and configured to combust a mixture in which fuel is injected into the flow of compressed air, to generate a combustion gas;
• and
• a downstream zone connected downstream of the combustion zone and configured to exhaust the combustion gas toward the rear opening,
• wherein a cavity is provided on the first surface in the combustion zone,
• wherein the first passage forming member comprises:
• at least one convex section located in the upstream zone and provided on the first surface to protrude toward the second surface from the first surface;
• a first fuel injection section configured to inject the fuel to the flow of compressed air through a first fuel nozzle provided for the convex section;
• and
• a second fuel injection section configured to inject the fuel to the cavity, and
• wherein the second passage forming member comprises a third fuel injection section configured to inject the fuel to a direction toward the first surface from the second surface in the passage through a second fuel nozzle provided on the second surface in the downstream zone.