Ilyushin Il-16

Ilyushin Design Bureau

Industry	Aerospace
Founded	1933
Headquarters	Moscow , Soviet Union
Products	Military aircraft

Template:Infobox aircraft

The Ilyushin Il-16 (Russian: Илью́шин Ил-16) was a Soviet lightweight armored ground-attack aircraft prototype designed by the Ilyushin Design Bureau near the conclusion of World War II. Essentially a downsized iteration of the Ilyushin Il-10, it was equipped with the newly engineered Mikulin AM-43 engine, intended to surpass its predecessor in speed and agility. Nevertheless, persistent issues with the powerplant could not be resolved, leading to the termination of further development by mid-1946.

Development

Inspired by the relatively strong performance of the Il-10, the Ilyushin design team initiated work in 1944 on a lighter attack aircraft that would offer enhanced velocity and maneuverability through a more potent engine. This new model, designated Il-16, incorporated the liquid-cooled Mikulin AM-43NV engine generating 2,300 horsepower (1,700 kW) at takeoff. The Il-16's design closely mirrored that of the Il-10 in both aerodynamic profile and structural layout but was slightly reduced in size and mass. With the integration of the more powerful AM-43 engine, expectations were for a marked increase in speed compared to the older model. The aircraft retained Ilyushin's characteristic load-bearing armored shell; however, certain armor sections were thinner than those on the Il-10.

Armament on the Il-16 consisted of a pair of 23 millimetres (0.91 in) Nudelman-Suranov NS-23 cannons mounted in the wings, identical to those on the Il-10, supplemented by two 7.62 millimetres (0.300 in) ShKAS machine guns positioned in the outer wing panels. Defensive firepower included a 20 millimetres (0.79 in) Berezin B-20 (UB-20) cannon operated by a rear gunner. Additionally, a set of ten AG-2 aerial grenades was installed as a deterrent against pursuing enemy fighters. Initially, the bombload capacity was planned at 200 kilograms (440 lb), carried within two bomb bays located in the inner wings or on external racks beneath the wings, with an overload limit of 400 kilograms (880 lb). This was later increased to a standard load of 400 kg and an overload capacity raised to 500 kilograms (1,100 lb).

The precise count of prototypes constructed remains uncertain; some sources suggest three units, while photographic evidence confirms at least two. The first prototype took flight in 1945 but exhibited poor longitudinal stability due to engine torque combined with a short rear fuselage. To address this, modifications were made for the second prototype including an extension of the rear fuselage by 500 millimetres (20 in), enlargement of the vertical stabilizer's surface area, and addition of a trim tab on the rudder. These adjustments successfully enhanced flight stability; however, persistent engine difficulties prolonged testing into 1946. Ultimately, these unresolved problems led to cancellation of the program during summer 1946.