Blackburn Botha

First flight		28 December 1938
Introduced		12 December 1939
Retired		September 1944
Number built		580

The Blackburn B.26 Botha was a competitor to the Bristol, and entered service with the RAF in 1939. It was underpowered and was quickly withdrawn from operations.

In service, the Botha proved to be severely underpowered and unstable and there were a number of fatal crashes in 1940. Both airframe and engine were subject to further development work, but it was decided to withdraw the type from front-line service. At this point, the Air Staff made the ill-advised decision to transfer the surviving aircraft to training units, which inevitably resulted in further casualties.

The type was finally retired in September 1944. In total, 580 aircraft were built.

Variants

• Botha Mk I : Four-seat reconnaissance, torpedo bomber aircraft.
• Botha TT Mk I : Target tug aircraft.

General characteristics

• Crew: 4
• Length: 51 ft 1.5 in (15.58 m)
• wingspan: 59 ft (17.98 m)
• Height: 14 ft 7.5 in (4.46 m)
• Wing area: 518 ft² (48.12 m²)
• Max take off weight: 18,450 lb (8,369 kg)
• Powerplant: 2× Bristol Perseus radial engine, 930 hp (694 kW) each

Armament

• 3 × 0.303 in (7.7 mm) machine guns (one fixed forward-firing, two in dorsal turret)
• internal torpedo, depth charges or bombs up to 2,000 lb (907 kg)

Mil Mi-46

• The Mil Mi-46 is a projected passenger/cargo/flying crane aircraft
  
• Announced first in 1992
• . The aircraft was split into two versions: Mi-46T and Mi-46K.
  
• The Mi-46T was the passenger/cargo transport version.
• The Mi-46T just half the weight of the Mi-26,
• The Mi-46T fit to replace the aging Mi-26.
  
• The Mi-46K was the flying crane version fit to replace the Mi-10K.

Boeing Bird of Prey

las / Boeing

Role	Stealth testbed
Manufacturer	Mc Dnnnell Douglas / Boeing
First flight	1996
Retired	1999
Status	Experimental
Number built	1

• Crew: 1
• Length: approximately 47 ft (14.30 m)
• wingspan: approximately 23 ft (7.00 m)
• Height: 6 ft (1.83 m)
• max take off weight: 7,380 lb (3,350 kg)
• Powerplant: 1× Pratt & Whitney Canada JT 15D - 5C , 2,900 lbf (12.9 kN)

Performance

• max speed: 260 knots (482 km/h)
• service ceiling: 20,000 ft (6,100 m)

The Bird of Prey aircraft was developed intending to demonstrate stealth technology . it was a low cost program ( a price of $67 million) compared to many other programs . It developed technology and materials which would later be used on Boeing's X-45 unmanned combat air vehicle. It is characterized as a technology demonstrator.Development of the Bird of Prey began in 1992 by McDonnell Douglas's Phantom Works division for special projects. The first flight was in 1996, and 39 more were performed through the program's conclusion in 1999.The Bird of Prey is designed to prevent shadows and is believed to have been used to test active camouflage , which would involve its surfaces changing color or luminosity to match the surroundings.

The AASI Jetcruzer

The AASI Jetcruzer
Country of origin :United States of America
Powerplants :
One rear mounted 1172kW (1572shp) Pratt & Whitney Canada PT6A-66A turboprop driving a five blade constant speed Hartzell propeller.
Performance :
Max cruising speed 576km/h (318kt). Service ceiling 30,000ft. Max range at economical cruising speed with reserves 2574km (1391nm).
Weights :Max takeoff 2495kg (5500lb).
Dimensions :Wing span 12.85m (42ft 2in), length approx 10.5m (34.4ft).
Capacity :
Typical accommodation for six including pilot. Can be configured for ambulance, cargo and other utility work. Optional aft lavatory.
Production :
450 - 3 were built. 500 - by November 2001, 2 had been converted from 450s, 1 new one was built, and 197 were on order. Basic unit price (2001) $US1.495.000.
Type :Business and utility transport
History :
The innovative Jetcruzer 500 is designed to be a high speed low cost single engine corporate turboprop and is the product of California based Advanced Aerodynamics and Structures Inc (AASI).
The Jetcruzer 500 is based on the smaller, unpressurised Jetcruzer 450. Early design work for what would become the Jetcruzer 450 began in 1983. Construction of an Allison 250-C20S powered prototype began in 1988. It flew for the first time on January 11 1989.
The preproduction prototype first flew April 1991, and the first production standard Jetcruzer 450 on September 13 1992. When FAA Part 23 certification was granted on June 14 1994 the Jetcruzer became the first aircraft in the world to be certificated as spin resistant.
AASI elected not to place the 450 into production and instead focused its efforts on the pressurised 500. Initial work was on the 500P, which featured a modest 25cm (10in) fuselage stretch, but AASI instead decided to enlarge the design further. The definitive Jetcruzer features a 1.83m (6ft) fuselage stretch over the 450 (increasing cabin length by 90cm (3ft), plus a significantly more powerful PT6A66 turboprop driving a five (rather than three) blade prop, pressurisation to 30,000ft, an airstair entry door on the right hand side and additional cabin windows.
First flight of the prototype 500 (the modified preproduction prototype 450) was in August 22 1997, followed by the second prototype (the modified production 450) on November 7 1997.
Other notable Jetcruzer 500 design features include its canard configuration (which allows the main wing to be positioned further aft than normal, so the wing spars do not intrude into the cabin), lack of flaps (reducing pilot work load and manufacturing costs and saving weight), and optional EFIS avionics. Like the 450 the 500 will be certificated as spin resistant. The fuselage is made from composites while the wing and canard are aluminium.
On February 8 2002, AASI announced that it was taking over the Mooney assets, and that the name Mooney would be used for the combined companies. Headquarters, development, and marketing would remain at AASI's facility at Long Beach in California, but production of the Jetcruzer would be at Mooney's Kerrville, Texas plant.
The company is also working on the Stratocruzer 1250, a 13 place twin WilliamsRolls FJ-44 powered light corporate jet development.

McDonnell Douglas F-15 Eagle

The McDonnell Douglas (now Boeing) F-15 Eagle is a twin-engine, all-weather tactical fighter designed to gain and maintain air superiority in aerial combat. It is considered among the most successful modern fighters with over 100 aerial combat victories with no losses in dogfights.

• Role:Air superiority fighter
  Manufacturer:McDonnell Douglas, Boeing IDS
  First flight:27 July 1972
  Introduction:9 January 1976
  Status:Active
  Primary users:United States Air Force, Japan Air Self-Defense Force, Royal Saudi Air Force, Israeli Air Force
  Number built:F-15A/B/C/D/J/DJ: 1,198
  Unit cost:F-15A/B: US$27.9 million (1998),F-15C/D: US$29.9 million (1998)
  Variants:F-15E Strike Eagle, F-15SE Silent Eagle, F-15 S/MTD
• General characteristics
  Crew: 1
  Length: 63 ft 9 in (19.43 m)
  Wingspan: 42 ft 10 in (13.05 m)
  Height: 18 ft 6 in (5.63 m)
  Wing area: 608 ft² (56.5 m²)
  Airfoil: NACA 64A006.6 root, NACA 64A203 tip
  Empty weight: 28,000 lb (12,700 kg)
  Loaded weight: 44,500 lb (20,200 kg)
  Max takeoff weight: 68,000 lb (30,845 kg)
  Powerplant: 2× Pratt & Whitney F100-100, -220 or -229 afterburning turbofans
  Dry thrust: 17,450 lbf (77.62 kN) each
  Thrust with afterburner: 25,000 lbf for -220; 29,000 lbf for -229 (111.2 kN for -220; 129.0 kN for -229) each
• Performance
  Maximum speed:
  High altitude: Mach 2.5+ (1,650+ mph, 2,660+ km/h)
  Low altitude: Mach 1.2 (900 mph, 1,450 km/h)
  Combat radius: 1,061 nmi (1,222 mi, 1,967 km) for interdiction mission
  Ferry range: 3,450 mi (3,000 nmi, 5,550 km) with conformal fuel tanks and three external fuel tanks
  Service ceiling: 65,000 ft (20,000 m)
  Rate of climb: >50,000 ft/min (254 m/s)
  Wing loading: 73.1 lb/ft² (358 kg/m²)
  Thrust/weight: 1.12 (-220), 1.30 (-229)
• Armament
  Guns: 1× internally mounted 20 mm (0.787 in) M61A1 gatling gun, 940 rounds
  Hardpoints: four wing, four fuselage, two wing stations, centerline station, optional fuselage pylons with a capacity of 16,000 lb (7,300 kg)
  Missiles:
  AIM-7 Sparrow
  AIM-120 AMRAAM
  AIM-9 Sidewinders
• Avionics
  Radar:
  Raytheon AN/APG-63 or AN/APG-70 or
  Although several F-15C aircraft were produced with APG-70 radar, all have been retrofitted to the AN/APG-63(V)1 configuration
  Raytheon AN/APG-63(V)1 or
  Raytheon AN/APG-63(V)2 Active Electronically Scanned Array (AESA) or
  Raytheon AN/APG-63(V)3 Active Electronically Scanned Array (AESA)
  Both active AF and ANG F-15Cs will receive another (up to) 48 V3 units between 2009-2015, over the existing 19 aircraft.
  Countermeasures:
  AN/APX-76 or AN/APX-119 Identify Friend/Foe (IFF) interrogator
  Magnavox AN/ALQ-128 Electronic Warfare Warning Set (EWWS) -part of Tactical Electronic Warfare Systems (TEWS)
  Loral AN/ALR-56 Radar Warning Receiver (RWR)-part of Tactical Electronic Warfare Systems (TEWS)
  Northrop ALQ-135 Internal Countermeasures System (ICS) - part of Tactical Electronic Warfare Systems (TEWS)
  AN/ALE-45 chaff/flare dispensers
  Pratt & Whitney F100 turbofan engines of an F-15C Eagle
  Others:
  Joint Helmet Mounted Cueing System
  MXU-648 Cargo/Travel Pod - to carry personal belongings, and small pieces of maintenance equipment.

Lockheed Martin F-22 Raptor

The Lockheed Martin/Boeing F-22 Raptor is a single-seat, twin-engine fifth-generation fighter aircraft that uses stealth technology. It was designed primarily as an air superiority fighter, but has additional capabilities that include ground attack, electronic warfare, and signals intelligence.

Role:Stealth Air superiority fighter, multirole fighter
National origin:United States
Manufacturer:
Lockheed Martin Aeronautics
Boeing Integrated Defense Systems
First flight:
YF-22: 29 September 1990
F-22: 7 September 1997
Introduced:15 December 2005
Status:In service
Primary user:United States Air Force
Number built:168 as of May 2010 (187 planned)
Program cost:US$65 billion
Unit cost:US$150 million(2009 flyaway cost)
Developed into:X-44 MANTA, FB-22

• General characteristics
  Crew: 1
  Length: 62 ft 1 in (18.90 m)
  Wingspan: 44 ft 6 in (13.56 m)
  Height: 16 ft 8 in (5.08 m)
  Wing area: 840 ft² (78.04 m²)
  Airfoil: NACA 64A?05.92 root, NACA 64A?04.29 tip
  Empty weight: 43,430 lb (19,700 kg)
  Loaded weight: 64,460 lb (29,300 kg)
  Max takeoff weight: 83,500 lb (38,000 kg)
  Powerplant: 2× Pratt & Whitney F119-PW-100 Pitch Thrust vectoring turbofans
  Dry thrust: 23,500 lb (104 kN) each
  Thrust with afterburner: 35,000+ lb (156+ kN) each
  Fuel capacity: 18,000 lb (8,200 kg) internally, or 26,000 lb (11,900 kg) with two external fuel tanks
• Performance
  Maximum speed:
  At altitude: Mach 2.25 (1,500 mph, 2,410 km/h)
  Supercruise: Mach 1.82 (1,220 mph, 1,963 km/h)
  Range: 1,600 nmi (1,840 mi, 2,960 km) with 2 external fuel tanks
  Combat radius: 410 nmi (471 mi, 759 km)
  Ferry range: 2,000 mi (1,738 nmi, 3,219 km)
  Service ceiling: 65,000 ft (19,812 m)
  Wing loading: 77 lb/ft² (375 kg/m²)
  Thrust/weight: 1.08 (1.26 with loaded weight & 50% fuel)
  Maximum design g-load: -3.0/+9.0 g
• Armament
  Guns: 1× 20 mm (0.787 in) M61A2 Vulcan gatling gun in starboard wing root, 480 rounds
  Air to air loadout:
  6× AIM-120 AMRAAM
  2× AIM-9 Sidewinder
  Air to ground loadout:
  2× AIM-120 AMRAAM and
  2× AIM-9 Sidewinder for self-protection, and one of the following:
  2× 1,000 lb (450 kg) JDAM or
  2× Wind Corrected Munitions Dispensers (WCMDs) or
  8× 250 lb (110 kg) GBU-39 Small Diameter Bombs
  Hardpoints: 4× under-wing pylon stations can be fitted to carry 600 US gallon drop tanks or weapons, each with a capacity of 5,000 lb (2,268 kg).
• Avionics
  RWR (Radar warning receiver): 250 nmi (463 km) or more
  Radar: 125-150 miles (200-240 km) against 1 m2 (11 sq ft) targets (estimated range)
  Chemring MJU-39/40 flares for protection against IR missiles.

Grumman F-14 Tomcat

The Grumman F-14 Tomcat is a supersonic, twin-engine, two-seat, variable-sweep wing fighter aircrat.

• Role:Interceptor, multirole fighter aircraft
  Manufacturer:Grumman
  First flight:21 December 1970
  Introduction:September 1974
  Retired:US Navy: 22 September 2006
  Status:Active service with Iran
  Primary users:United States Navy (former)Islamic Republic of Iran Air Force
  Number built:712
  Unit cost:US$38 million in 1998

General characteristics
Crew: 2 (Pilot and Radar Intercept Officer)
Length: 62 ft 9 in (19.1 m)
Wingspan:
Spread: 64 ft (19.55 m)
Swept: 38 ft (11.58 m)
Height: 16 ft (4.88 m)
Wing area: 565 ft² (54.5 m²)
Airfoil: NACA 64A209.65 mod root, 64A208.91 mod tip
Empty weight: 43,735 lb (19,838 kg)
Loaded weight: 61,000 lb (27,700 kg)
Max takeoff weight: 74,350 lb (33,720 kg)
Powerplant: 2× General Electric F110-GE-400 afterburning turbofans
Dry thrust: 13,810 lbf (61.4 kN) each
Thrust with afterburner: 27,800 lbf (124.7 kN) each
Maximum fuel capacity: 16,200 lb internal; 20,000 lb with 2x 267 gallon external tanks
Performance
Maximum speed: Mach 2.34 (1,544 mph, 2,485 km/h) at high altitude
Combat radius: 500 nmi (575 mi, 926 km)
Ferry range: 1,600 nmi (1,840 mi, 2,960 km)
Service ceiling: 50,000 ft (15,200 m)
Rate of climb: >45,000 ft/min (229 m/s)
Wing loading: 113.4 lb/ft² (553.9 kg/m²)
Thrust/weight: 0.91
Armament
Guns: 1× 20 mm (0.787 in) M61 Vulcan Gatling Gun, with 675 rounds
Hardpoints: 10 total: 6× under-fuselage, 2× under nacelles and 2× on wing gloves with a capacity of 14,500 lb (6,600 kg) of ordnance and fuel tanks
Missiles:
Air-to-air missiles: AIM-54 Phoenix, AIM-7 Sparrow, AIM-9 Sidewinder
Loading configurations:
2× AIM-9 + 6× AIM-54 (Rarely used due to weight stress on airframe)
2× AIM-9 + 2× AIM-54 + 3× AIM-7 (Most common load during Cold War era)
2× AIM-9 + 4× AIM-54 + 2× AIM-7
2× AIM-9 + 6× AIM-7
4× AIM-9 + 4× AIM-54
4× AIM-9 + 4× AIM-7
Bombs:
JDAM Precision-guided munition (PGMs)
Paveway series of Laser guided bombs
Mk 80 series of unguided iron bombs
Mk 20 Rockeye II
Others:
LANTIRN targeting pod
2× 267 US gallon drop tanks for extended range/loitering time
Avionics
Hughes AN/APG-71 radar
AN/ASN-130 INS, IRST, TCS
Remotely Operated Video Enhanced Receiver (ROVER) upgrade