title: Dale Weejet 800
text: # Dale Weejet 800
  
  The Dale Weejet 800, or Weejet VT-1 was an early light jet intended for high-speed personal transport or primary military training.
  
  ## Design and development
  
  Harold Dale, an engineer at North American Aviation who had designed several homebuilt aircraft, teamed up with Edward Gagnier, a former North American engineer, to develop the Weejet. The name was registered in February 1952 and the prototype was built in 2 1/2 years.
  
  The Weejet was a two-seat side-by-side, mid-winged all-aluminum, retractable tricycle gear aircraft with a V-tail arrangement. The aircraft was powered by a 920lb thrust Continental-Turbomeca Marbore II J-69-T-15 engine. Air was fed to the engine through two triangular inlets mounted on the inboard wing roots. Fuel was carried in the leading edge of the wings, and tip tanks. The aircraft had oxygen tanks and was pressurized to 3 psi differential pressure. The seats were designed to accommodate parachutes. The rudder pedals were adjustable for different pilot heights.
  
  ## Operational history
  
  The first test flight was conducted by Harold Dale on 30 March 1956. The aircraft completed several spin tests, but during one test the canopy opened and the aircraft went into an inverted spin. The pilot bailed out safely and the prototype crashed after performing an unmanned inverted loop. It was later found that the trim tab was set to full nose-down attitude during the test. A scheduled demonstration of the aircraft for the U.S. Navy was canceled. No other Weejets were produced.
  
  ## Specifications (Dale Weejet 800)
  
  Data from Sport Aviation
  
  General characteristics
  
  * Capacity: two
  * Length: 24 ft 6 in (7.47 m)
  * Wingspan: 28 ft (8.5 m)
  * Height: 6 ft 7 in (2.01 m)
  * Wing area: 150 sq ft (14 $m^2)$ swept
  * Airfoil: NACA 23012
  * Empty weight: 2,481 lb (1,125 kg)
  * Gross weight: 3,000 lb (1,361 kg)
  * Fuel capacity: 232 U.S. gallons (880 L; 193 imp gal)
  * Powerplant: 1 × Continental-Turbomeca Marbore II J-69-T-15 , 920 lbf (4.1 kN) thrust
  
  Performance
  
  * Maximum speed: 301 kn (346 mph, 557 km/h)
  * Cruise speed: 268 kn (308 mph, 496 km/h)
  * Stall speed: 56 kn (64 mph, 103 km/h)
  * Range: 1,248 nmi (1,436 mi, 2,311 km) at 35,000 ft
  * Rate of climb: 2,500 ft/min (13 m/s) at sea level
  
  Avionics
  
  * AN/ARC-27 Comm
  * AN/ARA-25 ADF
  