NACA L-485 -Tests Results

AIRPOWER - Proof of concept

 

 

 

        

        Results analysis 

• Case 1 is an ideal minimum drag fuselage.

• Case 8- has one engine tunnel exit.

• Case 9 has a drag coefficient CDF which is

       less than that of case 1. Why?

 

             Answer

The real drag of case 9 is about 30% higher

than case 1 drag due to added airflow in the 

engine tunnel. However, since the jet effect

due to accelerated airspeed at the engine 

tunnel exit ( see fig. 7 analysis) acted in the opposite

direction to the drag force, the resultant force

measured by the wind tunnel instrument showed 

less drag than case 1.

 

Case 9 is proof of the concept of this invention,

i.e., converting air thermal energy into useful power, in

this case, thrust, which, decreased the fuselage drag

comparing to case 1.

 

Case 8 also benefitted from the jet effect but not as much as case 9.

 

The current air-generator prototype is similar to case 8.

we need an improved turbine to achieve better results.