Nikita NB-160 Durva: Difference between revisions
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{|{{Infobox aircraft begin | {|{{Infobox aircraft begin | ||
|name = Nikita NB-160 Durva | |name = Nikita NB-160 Durva | ||
|image = | |image = XB-38.jpg | ||
|caption = Placeholder Image | |||
|alt = | |alt = | ||
}}{{Infobox aircraft type | }}{{Infobox aircraft type | ||
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| more users = | | more users = | ||
| produced = 1935-1950 | | produced = 1935-1950 | ||
| number built = | | number built = 8,389 | ||
| program cost = | | program cost = | ||
| unit cost = | | unit cost = | ||
| developed from = | | developed from = | ||
| variants with their own articles = | | variants with their own articles = | ||
| developed into = | | developed into = Nikita NB-170 | ||
}} | }} | ||
|} | |} | ||
The Nikita NB-160 Durva | The Nikita NB-160 Durva was a four-engined heavy bomber developed in the 1930s for the Royal Tennaiite Air Force. The bomber saw extensive use during the Siduri war were it proved a reliable and effective bomb platform. | ||
==Specifications (NB-160 | ==Development== | ||
In 1932, Tennaiite military personnel undertook work to flesh out a new all- modern bomber - one that could carry a war load of at least 2,500 lb out to distances of 5,000 miles while maintaining a speed of 200 miles per hour. The Royal Tennaiite Air Force (RTAF) developed "Project-A" around these specifications and this was presented in 1933 to large-aircraft makers Cheppali and Devati. The intent was to develop an bombing platform capable of reaching (and subsequently protecting) far-off Tennaiite interests at home and abroad. | |||
Devati's submission to the project was known internally as "Model 155". To contend with the requested range and performance, a four-engined layout was selected - power stemming from 4 x Kamala TU-1710 liquid-cooled inline piston engines of 1,100 horsepower each. This proved something of a departure for the RTAF as its contemporary stock of large aircraft relied heavily on trusty air-cooled radial piston engines. Liquid-cooled inline engines aided high-altitude performance and could be fitted within more streamlined nacelles, therefore inherently improving aerodynamic efficiency. The trade off in selecting an inline engine, however, was in the increased vulnerability to enemy fire due to the internally fragile nature of such an engine. | |||
The wide-spanning wing elements (showcasing a combined 140 foot span) were mid-mounted. Each wing was held a pair of engine nacelles that were well-contoured into the general shape of the wing elements themselves. The cockpit was stepped (the pilot's overlooking the aircraft's nose section) and window panes accompanied the bombardier's position at the nose. | |||
==Design== | |||
==Variants== | |||
*A1 | |||
*A2 | |||
*A3 | |||
*B1 | |||
*B2 | |||
*C1 | |||
*C2 | |||
==Operational History== | |||
===Siduri War=== | |||
==Operators== | |||
{{flag|Tennai}} | |||
==Specifications (NB-160 C2)== | |||
{{Aircraft specs | {{Aircraft specs | ||
|prime units?=met | |prime units?=met | ||
| Line 43: | Line 65: | ||
|empty weight kg=14500 | |empty weight kg=14500 | ||
|empty weight note= | |empty weight note= | ||
|gross weight kg= | |gross weight kg=19285 | ||
|gross weight note= | |gross weight note= | ||
|max takeoff weight kg=47600 | |max takeoff weight kg=47600 | ||
|max takeoff weight note= | |max takeoff weight note= | ||
|fuel capacity= | |fuel capacity= | ||
|more general= | |more general= | ||
| Line 53: | Line 75: | ||
--> | --> | ||
|eng1 number=4 | |eng1 number=4 | ||
|eng1 name=Kamala TU- | |eng1 name=Kamala TU-1717 | ||
|eng1 type=V-12 inverted liquid-cooled piston engines | |eng1 type= turbosupercharged V-12 inverted liquid-cooled piston engines | ||
|eng1 kw= | |eng1 kw=1268 | ||
|eng1 hp= | |eng1 hp= | ||
|eng1 shp=<!-- prop engines --> | |eng1 shp=<!-- prop engines --> | ||
|eng1 kn=<!-- jet/rocket engines --> | |eng1 kn=<!-- jet/rocket engines --> | ||
|eng1 lbf=<!-- jet/rocket engines --> | |eng1 lbf=<!-- jet/rocket engines --> | ||
|eng1 note= | |eng1 note= | ||
|prop blade number=4 | |prop blade number=4 | ||
|prop name=constant-speed propellers | |prop name=constant-speed propellers | ||
|prop dia m= | |prop dia m=5.5 | ||
|prop dia note= | |prop dia note= | ||
<!-- | <!-- | ||
Performance | Performance | ||
--> | --> | ||
|max speed kmh= | |max speed kmh=580 | ||
|max speed note=at {{cvt|7000|m|0}} | |max speed note=at {{cvt|7000|m|0}} | ||
|cruise speed kmh= | |cruise speed kmh=377 | ||
|cruise speed note= | |cruise speed note= | ||
|stall speed kmh= | |stall speed kmh= | ||
|stall speed note= | |stall speed note= | ||
|never exceed speed kmh= | |never exceed speed kmh= | ||
| Line 86: | Line 107: | ||
|ferry range note= | |ferry range note= | ||
|endurance=<!-- if range unknown --> | |endurance=<!-- if range unknown --> | ||
|ceiling m= | |ceiling m=13000 | ||
|ceiling note= | |ceiling note= | ||
|g limits=<!-- aerobatic --> | |g limits=<!-- aerobatic --> | ||
| Line 102: | Line 123: | ||
--> | --> | ||
|guns=<br/> | |guns=<br/> | ||
** 14 × {{cvt|12.72|mm|3}} machine guns (2 in the chin turret, 2 on nose cheeks, 2 staggered waist guns, 2 in upper turret, 2 in ball turret in belly, 2 in the tail and 2 firing upwards from radio compartment behind bomb bay) | |||
*'''Bombs''' | |||
** Up to {{convert|6351|kg|lb|0|abbr=on}} bombs | |||
* | |||
** | |||
}} | }} | ||
Latest revision as of 19:52, 27 February 2021
| Nikita NB-160 Durva | |
|---|---|
| |
| Placeholder Image | |
| Role | Heavy Bomber |
| National origin | Tennai |
| Manufacturer | Nikita Aircraft |
| Designer | Kapishan Mishaani |
| First flight | February 1934 |
| Introduction | July 1935 |
| Retired | 1955 |
| Status | Retired |
| Primary user | Royal Tennaiite Air Force |
| Produced | 1935-1950 |
| Number built | 8,389 |
| Developed into | Nikita NB-170 |
The Nikita NB-160 Durva was a four-engined heavy bomber developed in the 1930s for the Royal Tennaiite Air Force. The bomber saw extensive use during the Siduri war were it proved a reliable and effective bomb platform.
Development
In 1932, Tennaiite military personnel undertook work to flesh out a new all- modern bomber - one that could carry a war load of at least 2,500 lb out to distances of 5,000 miles while maintaining a speed of 200 miles per hour. The Royal Tennaiite Air Force (RTAF) developed "Project-A" around these specifications and this was presented in 1933 to large-aircraft makers Cheppali and Devati. The intent was to develop an bombing platform capable of reaching (and subsequently protecting) far-off Tennaiite interests at home and abroad.
Devati's submission to the project was known internally as "Model 155". To contend with the requested range and performance, a four-engined layout was selected - power stemming from 4 x Kamala TU-1710 liquid-cooled inline piston engines of 1,100 horsepower each. This proved something of a departure for the RTAF as its contemporary stock of large aircraft relied heavily on trusty air-cooled radial piston engines. Liquid-cooled inline engines aided high-altitude performance and could be fitted within more streamlined nacelles, therefore inherently improving aerodynamic efficiency. The trade off in selecting an inline engine, however, was in the increased vulnerability to enemy fire due to the internally fragile nature of such an engine.
The wide-spanning wing elements (showcasing a combined 140 foot span) were mid-mounted. Each wing was held a pair of engine nacelles that were well-contoured into the general shape of the wing elements themselves. The cockpit was stepped (the pilot's overlooking the aircraft's nose section) and window panes accompanied the bombardier's position at the nose.
Design
Variants
- A1
- A2
- A3
- B1
- B2
- C1
- C2
Operational History
Siduri War
Operators
Specifications (NB-160 C2)
General characteristics
- Crew: 10 ( Pilot, co-pilot, navigator, bombardier/nose gunner, flight engineer/top turret gunner, radio operator, waist gunners (2), ball turret gunner, tail gunner)
- Length: 35 m (114 ft 10 in)
- Wingspan: 43 m (141 ft 1 in)
- Height: 5.5 m (18 ft 1 in)
- Wing area: 161.3 m2 (1,736 sq ft)
- Empty weight: 14,500 kg (31,967 lb)
- Gross weight: 19,285 kg (42,516 lb)
- Max takeoff weight: 47,600 kg (104,940 lb)
- Powerplant: 4 × Kamala TU-1717 turbosupercharged V-12 inverted liquid-cooled piston engines, 1,268 kW (1,700 hp) each
- Propellers: 4-bladed constant-speed propellers, 5.5 m (18 ft 1 in) diameter
Performance
- Maximum speed: 580 km/h (360 mph; 313 kn) at 7,000 m (22,966 ft)
- Cruise speed: 377 km/h (234 mph; 204 kn)
- Range: 8,047 km (5,000 mi; 4,345 nmi)
- Combat range: 4,828 km (3,000 mi; 2,607 nmi)
- Service ceiling: 13,000 m (43,000 ft)
- Rate of climb: 24 m/s (4,700 ft/min)
- Time to altitude: 6,000 m (19,685 ft) in 5 minutes 12 seconds
Armament
- Guns:
- 14 × 12.72 mm (0.501 in) machine guns (2 in the chin turret, 2 on nose cheeks, 2 staggered waist guns, 2 in upper turret, 2 in ball turret in belly, 2 in the tail and 2 firing upwards from radio compartment behind bomb bay)
- Bombs
- Up to 6,351 kg (14,002 lb) bombs