WP80

Full specification

The WP80 is a short-life turbojet aimed at high-speed unmanned aircraft. It holds at least 78 kgf in the rated condition and 59 kgf at the mid point, with 1.38 kg/kgf/h at maximum state and 1.55 kg/s airflow. The start ceiling is 5,000 m, a ground start takes 50 s or less, and acceleration and deceleration are 10 s each. The integrated ECU reports over RS-422 at 115,200 bps, and the maximum continuous run at full power is 10 min. Fuel is RP-3 with 5% lubricant at ambient pressure plus 30–50 kPa.

Thrust class

Mid class

Fuel consumption

SFC 1.38 kg/kgf/h at maximum state

Fuel

RP-3 + 5% lubricant

Start

ECU automatic start sequence

ECU

Integrated ECU, RS-422 at 115,200 bps

Service interval

25 h TBO

Max altitude

12,000 m

Temperature

-40 to 60 °C

Start altitude

5,000 m

Mach

0.9

Ground start time

50 s

Acceleration

10 s

Deceleration

10 s

Inlet duct inner diameter

121.4 mm

Air flow

1.55 kg/s

Idle thrust

12 kgf maximum at 30,000 rpm

Fuel supply pressure

Ambient + 30–50 kPa

Typical use

High-speed UAV

Rated values from the model datasheet; factory test performance can vary by 2–3%. Altitude, Mach and temperature limits are operating limits, not guarantees of airframe performance.

Fitment notes

1. 01Fuel is aviation kerosene with the lubricant ratio stated above. Fit a 20–50 µm filter before the pump and keep supply pressure inside the datasheet range.
2. 02Ground starts follow the ECU's automatic ignition sequence. Stay within the stated start altitude and temperature limits; a start that times out is aborted by the controller.
3. 03Keep the intake and exhaust clear during runs. The manuals specify 3 m in front and 5 m to each side as a safety distance for ground operation.