Nakajima ATD-X: Difference between revisions
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|program cost= CL₡408.4 million (2016 estimate) | |||
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|developed from= | |developed from= | ||
|variants with their own articles= | |variants with their own articles= | ||
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The '''Nakajima ATD-X''' ('''Advanced Technology Demonstrator – Experimental''') was an experimental [[Chilokver|Chilokveri]] aircraft used to test low-observable airframe shaping, {{wpl|Radiation-absorbent_material|radar-absorbent materials}}, {{wpl|Thrust_vectoring|thrust vectoring}}, and other fifth-generation aircraft technologies. The aircraft was developed by [[Nakajima Aircraft Company]] in collaboration with the [[Chilokveri Ministry of Defence]], and the sole prototype constructed was flown by the [[National Chilokveri Air Force]] (NCAF). The ATD-X's first flight was on November 21, 2014. | The '''Nakajima ATD-X''' ('''Advanced Technology Demonstrator – Experimental''') was an experimental [[Chilokver|Chilokveri]] aircraft used to test low-observable airframe shaping, {{wpl|Radiation-absorbent_material|radar-absorbent materials}}, {{wpl|Thrust_vectoring|thrust vectoring}}, and other fifth-generation aircraft technologies. The aircraft was developed by [[Nakajima Aircraft Company]] in collaboration with the [[Chilokveri Ministry of Defence]], and the sole prototype constructed was flown by the [[National Chilokveri Air Force]] (NCAF). The ATD-X's first flight was on November 21, 2014. | ||
==Development== | ==Development== | ||
The ATD-X project began in 2001 as the '''Advanced Combat Aircraft''' (ACA) programme to design, develop, and manufacture a next-generation fighter to replace the [[National Chilokveri Air Force|NCAF'S]] existing fleet of [[Shangtian CF-03 Falcon|CF-03 Falcon]] and [[Nakajima CF-04 Falconet|CF-04 Falconet]] multirole fighters. The initial requirements of the ACA programme, as originally proposed by the NCAF, were to develop a 5th generaton, single-seat, twin-engine fighter with stealth capabilities. In July 2001, the [[Chilokveri Ministry of Defence|Chilokveri Ministry of Defence's]] [[Research and Procurement Agency]] (RPA) awarded [[Nakajima Aircraft Company|Nakajima]] with a ₡24 million [[Chilokveri credit|credit]] contract for the development of a preliminary design. | |||
==Design== | ==Design== | ||
==Specifications== | ==Specifications== | ||
{{Aircraft specs | |||
|prime units?=met | |||
|crew=1 | |||
|capacity= | |||
|length m= 14.17 | |||
|length ft= | |||
|length in= | |||
|length note= | |||
|span m= 9.10 | |||
|span ft= | |||
|span in= | |||
|span note= | |||
|height m= 4.51 | |||
|height ft= | |||
|height in= | |||
|height note= | |||
|wing area sqm= | |||
|wing area sqft= | |||
|wing area note= | |||
|empty weight kg= 8900 | |||
|empty weight lb= | |||
|empty weight note= | |||
|gross weight kg= | |||
|gross weight lb= | |||
|gross weight note= | |||
|max takeoff weight kg= 13000 | |||
|max takeoff weight lb= | |||
|max takeoff weight note= | |||
|fuel capacity= | |||
|more general= | |||
|eng1 number= 2 | |||
|eng1 name= [[Kowasaki TF5]] | |||
|eng1 type= {{wpl|Bypass ratio|low-bypass}} {{wpl|Turbofan|turbofans}} | |||
|eng1 kn= | |||
|eng1 lbf= | |||
|eng1 note= | |||
|power original= | |||
|thrust original= | |||
|eng1 kn-ab= | |||
|eng1 lbf-ab= 11023 | |||
|max speed kmh= | |||
|max speed mph= | |||
|max speed kts= | |||
|max speed note= | |||
|max speed mach= 2.25 (2,778 km/h; 1,726 mph) | |||
**'''Supercruise:''' Mach 1.82 (2,247 km/h; 1,396 mph) | |||
|cruise speed kmh= | |||
|cruise speed mph= | |||
|cruise speed kts= | |||
|cruise speed note= | |||
|stall speed kmh= | |||
|stall speed mph= | |||
|stall speed kts= | |||
|stall speed note= | |||
|range km= 2,900 | |||
|range miles= | |||
|range nmi= 1,566 | |||
|range note= | |||
|combat range km= 761 | |||
|combat range miles= | |||
|combat range nmi= | |||
|combat range note= | |||
|ferry range km= 3,200 | |||
|ferry range miles= 1,988 | |||
|ferry range nmi= 1,728 | |||
|ferry range note= | |||
|endurance= | |||
|ceiling ft= 65000 | |||
|ceiling m= | |||
|ceiling note= | |||
|g limits= | |||
|roll rate= | |||
|glide ratio= | |||
|climb rate ms= | |||
|climb rate ftmin= | |||
|climb rate note= | |||
|time to altitude= | |||
|lift to drag= | |||
|wing loading kg/m2= | |||
|wing loading lb/sqft= | |||
|wing loading note= | |||
|fuel consumption kg/km= | |||
|fuel consumption lb/mi= | |||
|thrust/weight= | |||
|more performance= | |||
|avionics= | |||
}} | |||
==See also== | ==See also== | ||
[[category:Chilokver]] | [[category:Chilokver]] | ||
Latest revision as of 08:14, 4 October 2019
 | This article is incomplete because it is pending further input from participants, or it is a work-in-progress by one author. Please comment on this article's talk page to share your input, comments and questions. Note: To contribute to this article, you may need to seek help from the author(s) of this page. |
| ATD-X | |
|---|---|
| |
| The ATD-X during its maiden flight. | |
| Role | Experimental stealth aircraft |
| National origin |  Chilokver
|
| Manufacturer | Nakajima Aircraft Company |
| Status | Retired |
| Primary user | National Chilokveri Air Force |
| Number built | 1 |
| Program cost | CL₡408.4 million (2016 estimate) |
The Nakajima ATD-X (Advanced Technology Demonstrator – Experimental) was an experimental Chilokveri aircraft used to test low-observable airframe shaping, radar-absorbent materials, thrust vectoring, and other fifth-generation aircraft technologies. The aircraft was developed by Nakajima Aircraft Company in collaboration with the Chilokveri Ministry of Defence, and the sole prototype constructed was flown by the National Chilokveri Air Force (NCAF). The ATD-X's first flight was on November 21, 2014.
Development
The ATD-X project began in 2001 as the Advanced Combat Aircraft (ACA) programme to design, develop, and manufacture a next-generation fighter to replace the NCAF'S existing fleet of CF-03 Falcon and CF-04 Falconet multirole fighters. The initial requirements of the ACA programme, as originally proposed by the NCAF, were to develop a 5th generaton, single-seat, twin-engine fighter with stealth capabilities. In July 2001, the Chilokveri Ministry of Defence's Research and Procurement Agency (RPA) awarded Nakajima with a ₡24 million credit contract for the development of a preliminary design.
Design
Specifications
General characteristics
- Crew: 1
- Length: 14.17 m (46 ft 6 in)
- Wingspan: 9.10 m (29 ft 10 in)
- Height: 4.51 m (14 ft 10 in)
- Empty weight: 8,900 kg (19,621 lb)
- Max takeoff weight: 13,000 kg (28,660 lb)
- Powerplant: 2 × Kowasaki TF5 low-bypass turbofans, 49.03 kN (11,023 lbf) with afterburner
Performance
- Maximum speed: Mach 2.25 (2,778 km/h; 1,726 mph)
- Supercruise: Mach 1.82 (2,247 km/h; 1,396 mph)
- Range: 2,900 km (1,802 mi; 1,566 nmi)
- Combat range: 761 km (473 mi; 411 nmi)
- Ferry range: 3,200 km (1,988 mi; 1,728 nmi)
- Service ceiling: 20,000 m (65,000 ft)