System for providing a favorable environment for propulsion system of a blended wing body aircraft and a method of manufacturing

1 . A system for providing a favorable environment for a propulsion system of a blended wing body aircraft, wherein the system comprising:

a blended wing body, wherein the blended wing body comprises:

a main body, wherein the main body comprises:

a main body shaping comprising an upper aft surface configured to provide the favorable environment for the propulsion system of the blended wing body aircraft, wherein the upper aft surface comprises an upper aft surface shaping configured to create a concavity with an airflow axis; and

the propulsion system mounted to the upper aft surface of the main body at an orientation to create a predetermined angle of attack between a center line of the propulsion system and a vector representing relative motion between the propulsion system and surrounding atmosphere, wherein an inlet of the propulsion system is further mounted behind a vertex of an arc within the concavity of the upper aft surface shaping, wherein the propulsion system comprises:

one or more prime movers; and

a nacelle covering the one or more prime movers, wherein the nacelle comprises:

 a thrust reverser;

 a nacelle shaping, wherein the nacelle shaping is configured to direct airflow towards the one or more prime movers; and

 the inlet configured to receive the airflow and located at a forward end of the nacelle shaping,

 wherein the inlet and the angle of attack are configured such that during flight of the blended wing body aircraft at least a portion of the inlet is above a boundary layer formed over the upper aft surface of the main body shaping to enhance uniformity of the airflow at the inlet.

2 . The system of claim 1 , wherein the favorable environment for the propulsion system comprises a conditioned region close to an entry of the propulsion system of the blended wing body aircraft.

3 . The system of claim 1 , wherein the main body shaping further comprises:

an upper fore surface, wherein the upper fore surface comprises an upper fore surface shaping.

4 . The system of claim 3 , wherein the upper fore surface shaping is configured to:

create a convexity with an air flow axis; and

increase an air flow speed in the upper fore surface of the blended wing body aircraft.

5 . The system of claim 1 , wherein the upper aft surface comprises the upper aft surface shaping configured to:

decrease an airflow speed in the upper aft surface of the blended wing body aircraft.

6 . The system of claim 1 , wherein the one or more prime movers comprises a turbofan engine.

7 . The system of claim 1 , wherein the propulsion system comprises a separation distance between a first prime mover and a second prime mover.

8 . The system of claim 1 , wherein the inlet is configured to avoid ingestion of a boundary layer.

9 . The system of claim 1 , wherein the nacelle comprises one or more pylons, wherein the one or more pylons connect the nacelle with the main body of the blended wing body aircraft.

10 . A method of manufacture of a system for providing favorable environment for a propulsion system of a blended wing body aircraft, wherein the method comprises:

receiving a main body shaping for a main body of the blended wing body aircraft, wherein the main body shaping comprises an upper aft surface configured to provide the favorable environment for the propulsion system of the blended wing body aircraft wherein the upper aft surface comprises an upper aft surface shaping configured to create a concavity with an airflow axis;

assembling the propulsion system at an orientation to create a predetermined angle of attack between a center line of the propulsion system and a vector representing relative motion between the propulsion system and surrounding atmosphere, wherein an inlet of the propulsion system is further mounted behind a vertex of an arc within the concavity of the upper aft surface shaping, wherein assembling the propulsion system comprises:

covering one or more prime movers using a nacelle, wherein the nacelle comprises:

a thrust reverser;

a nacelle shaping, wherein the nacelle shaping is configured to direct airflow towards the one or more prime movers; and

the inlet configured to receive the airflow and located at a forward end of the nacelle shaping,

wherein the inlet and the angle of attack are configured such that during flight of the blended wing body aircraft at least a portion of the inlet is above a boundary layer formed over the upper aft surface of the main body shaping to enhance uniformity of the airflow at the inlet; and

mounting the propulsion system to the upper aft surface of the main body.

11 . The method of claim 10 , wherein the favorable environment for the propulsion system comprises a conditioned region close to an entry of the propulsion system of the blended wing body aircraft.

12 . The method of claim 10 , wherein the main body further comprises:

an upper fore surface, wherein the upper fore surface comprises an upper fore surface shaping.

13 . The method of claim 12 , wherein the upper fore surface shaping is configured to:

create a convexity with an air flow axis; and

increase an air flow speed in the upper fore surface of the blended wing body aircraft.

14 . The method of claim 10 , wherein the upper aft surface shaping is configured to;

decrease an airflow speed in the upper aft surface of the blended wing body aircraft.

15 . The method of claim 10 , wherein the one or more prime movers comprises a turbofan engine.

16 . The method of claim 10 , wherein the propulsion system comprises a separation distance between a first prime mover and a second prime mover.

17 . The system of claim 1 , wherein the inlet is configured to avoid ingestion of the boundary layer.

18 . The method of claim 10 , wherein the nacelle comprises one or more pylons, wherein the one or more pylons connect the nacelle with the main body of the blended wing body aircraft.