Convair Model 48 Charger

https://en.wikipedia.org/wiki/Convair_Model_48_Charger

The Convair Model 48 Charger was a prototype light attack and observation
aircraft of the 1960s, developed to meet a requirement for a dedicated
counter-insurgency (COIN) aircraft. It was a two-seat, twin-boom aircraft
powered by two turboprop engines which lost out to the North American Rockwell
OV-10 Bronco of similar layout, only a single example being built.

In 1959, two United States Marine Corps officers developed the concept of a
small low cost aircraft capable of providing close air support to the U.S.
Marines, capable of operating from roads close to the battlefield, the concept
being known as the Light Light Marine Attack Aircraft (L2VMA). As interest in
such an aircraft grew, with interest from the US Army for a similar type, the
Convair Division of General Dynamics started studies into counter-insurgency
aircraft in 1961. In 1963, the various requirements were merged into a
tri-service specification for a Light Armed Reconnaissance Aircraft (LARA), to
be used not just by the U.S. Marines and Army, but also by the United States Air
Force for counter-insurgency and forward air control roles, and to be available
for export.

The specification produced responses from nine manufacturers, including Convair,
who submitted its Model 48 Charger in March 1964. The Model 48 was a twin-boom
monoplane, constructed mainly from aluminium, with fiberglass nose, rear
fuselage and wingtips, with a retractable nosewheel undercarriage. It was
powered by two Pratt & Whitney Canada PT-6 (military designation T-74), driving
three bladed propellers. Its wings were of relatively short (27 ft 6 in/8.38 m)
span, which meant that most of the wing was in the slipstream of the propellers,
increasing the effectiveness of the full-span trailing-edge slotted flaps and
leading edge slats inboard of the engines, which together acted to deflect the
slipstream, giving a form of vectored thrust, in order to reduce takeoff and
landing distances. The outer trailing-edge flaps doubled as ailerons, which were
supplemented by spoilers at low speed. The aircraft was fitted with a large,
all-moving tailplane which attached to the vertical fins located at the ends of
the tailboom(s), with the tailplane having somewhat greater span (20 ft (6.1 m))
than the distance between the tailbooms.

Pilot and observer sat in tandem under a sliding canopy, while the rear fuselage
held a cargo bay with a hinged tail cone capable of carrying 2,000 lb (910 kg)
of cargo, which could include a complete PT-6 engine, or five paratroopers, in
extremely cramped conditions, with a sixth paratrooper in the observer's seat.
Four 7.62 mm machine guns were mounted in pods on the side of the fuselage,
while 2,000 lb (910 kg) of external stores, including bombs, rockets and gun
pods, could be carried on hardpoints under the wings and fuselage. To meet the
specification's requirements for amphibious operations, it could be fitted with
two large floats.


Role
Light attack and observation aircraft

National origin
United States of America

Manufacturer
Convair

First flight
25 November 1964

Status
Prototype

Number built
1

Convair started construction of a prototype as a private venture before a winner
of the LARA competition was announced. In August 1964, the US Navy announced
North American Aviation's design, the NA-300 (later to become the OV-10 Bronco)
as the winner of the LARA competition. The U.S. Marine Corps and U.S. Air Force
favored the Charger, however, and protested against the U.S. Navy's decision,
and Convair continued construction of their prototype, which made its maiden
flight on 25 November 1964.

After initial flight tests, the Charger was modified with an increased wingspan
and modified tail to improve low-speed control. The Charger demonstrated
excellent STOL capability, taking off over a 50 ft (15 m) obstacle in 485 ft
(148 m) with a normal payload. This was better both than the LARA specifications
requirement of 800 ft (244 m), and the Bronco.

The Charger was awarded a 100-hour joint service flight test contract where the
prototype would be flown by representatives of the U.S. Navy, Marine Corps, Army
and Air Force. If orders followed, it was planned to build the production
aircraft with a deeper and longer fuselage allowing full dual controls to be
fitted. The prototype crashed on its 196th test flight on 19 October 1965, owing
to pilot error by its U.S. Navy test pilot, however, and further development was
abandoned.

Specifications (Long-span wings)

General characteristics
Crew: 2
Capacity: 6 paratroops in utility/cargo bay
Length: 34 ft 10 in (10.62 m)
Wingspan: 30 ft 1.25 in (9.1758 m)
Height: 13 ft 7 in (4.14 m)
Wing area: 216 sq ft (20.1 m2)
Empty weight: 4,457 lb (2,022 kg)
Gross weight: 10,460 lb (4,745 kg)
Fuel capacity: 258 US Gallon (977 L) internal
Powerplant: 2 × Pratt & Whitney Canada T74-CP-8/10 turboprop, 650 hp (480 kW)
each
Propellers: 3-bladed Hamilton Standard, 8 ft 6 in (2.59 m) diameter

Performance
Maximum speed: 319 mph (513 km/h, 277 kn) at sea level
Ferry range: 3,000 mi (4,800 km, 2,600 nmi)
Service ceiling: 21,300 ft (6,500 m)
Take-off to 50 ft (15 m): Less than 500 ft (152 m)
Landing from 50 ft (15 m): Less than 500 ft (152 m)

Armament

Guns: 4 × 7.62mm machine guns
Hardpoints: 5 with a capacity of 2,000 lb (910 kg) total,



*