<p>This paper presents a fixed-wing vertical take-off and landing (VTOL) aircraft with propellers fixed at an inclined angle. The aircraft operates akin to a tail-sitter, but is distinguished by its use of a distributed propulsion system fixed at an inclined angle. Compared to other conventional fixed-wing VTOL aircraft, this configuration can significantly reduce weight and complexity. Stable transitions are achieved by simply adjusting the vehicle’s pitch angle with minimal altitude change. An analysis reveals that this design exhibits a flight efficiency comparable to conventional fixed-wing aircraft during forward flight. Furthermore, the distributed propulsion provides pitch and roll control even in forward flight without conventional control surfaces. This paper details the associated modeling, stability analysis, and control law development for this new type of VTOL aircraft. Finally, flight test results validate the effectiveness of the developed control laws, and demonstrate that this type of aircraft achieves both high flight efficiency and stable transition performance.</p>