Dassault Rafale

The Dassault Rafale (French pronunciation: [ʁafal], squall) is a French twin-engine delta-wing multi-role jet fighter aircraft designed and built by Dassault Aviation. It is called an "omnirole" fighter by its manufacturer.

Introduced in 2000, the Rafale is being produced both for land-based use with the French Air Force and for carrier-based operations with the French Navy. It has also been marketed for export to several countries, but has not yet received orders.

In the late 1970s, the Air Force and Navy were seeking replacements for its aircraft. To save development costs, France agreed with four other nations to produce an air dominance fighter, but subsequent disagreements led to a split. To satisfy stringent criteria formulated by the Ministry of Defense, Dassault built a technology demonstrator to prove the viability of its new product. Further development led to the current Rafale variants, which embody innovative avionics and aerodynamics, optimised for air supremacy operations.


General characteristics

    Crew: 1–2
    Length: 15.27 m (50.1 ft)
    Wingspan: 10.80 m (35.4 ft)
    Height: 5.34 m (17.5 ft)
    Wing area: 45.7 m² (492 ft²)
    Empty weight: 9,500 kg (C), 9,770 kg (B),[105] 10,196 kg (M)
    Loaded weight: 14,016 kg (30,900 lb)
    Max takeoff weight: 24,500 kg (C/D), 22,200 kg (M) (54,000 lb)
    Powerplant: 2 × Snecma M88-2 turbofans
        Dry thrust: 50.04 kN (11,250 lbf) each
        Thrust with afterburner: 75.62 kN (17,000 lbf) each
    Fuel capacity: 4,700 kg (10,000 lb) internal

Performance

    Maximum speed:
        High altitude: Mach 1.8+ (2,130+ km/h, 1,050+ knots)
        Low altitude: 1,390 km/h, 750 knots
    Range: 3,700+ km (2,000+ nmi)
    Combat radius: 1,852+ km (1,000+ nmi) on penetration mission
    Service ceiling: 16,800 m (55,000 ft)
    Rate of climb: 304.8+ m/s (60,000+ ft/min)
    Wing loading: 306 kg/m² (62.8 lb/ft²)
    Thrust/weight: 1.10 (100% fuel, 2 EM A2A missile, 2 IR A2A missile)

Armament

    Guns: 1× 30 mm (1.18 in) GIAT 30/719B autocannon with 125 rounds
    Hardpoints: 14 for Armée de l'Air version (Rafale B,C), 13 for Aéronavale version (Rafale M) with a capacity of 9,500 kg (21,000 lb) external fuel and ordnance and provisions to carry combinations of:
        Missiles:
            MBDA MICA IR or EM or Magic II and
            MBDA Meteor air-to-air mssiles in the future
        Air-to-ground:
            MBDA Apache or
            Storm Shadow-SCALP EG or
            AASM-Hammer or
            GBU-12 Paveway II
        Air-to-surface:
            AM 39-Exocet
        Deterrence:
            ASMP-A nuclear missile
        Other:
            Thales Damocles targeting pod
            RECO NG (New Generation) reconnaissance pod
            up to 5 drop tanks
            The Rafale can also carry a buddy-buddy refuelling pod[37]

Avionics

    Thales RBE2 radar
    Thales SPECTRA electronic warfare system.
    Thales/SAGEM-OSF Optronique Secteur Frontal infra-red search and track system.

Boeing AH-64 Apache

this post for military lovers....

The U.S. Army selected the AH-64 over the Bell YAH-63 in 1976, awarding Hughes Helicopters a pre-production contract for two more aircraft. In 1982, the Army approved full production. McDonnell Douglas continued production and development after purchasing Hughes Helicopters from Summa Corporation in 1984. The first production AH-64D Apache Longbow, an upgraded version of the original Apache, was delivered to the Army in March 1997. Production has been continued by Boeing Defense, Space & Security; over one thousand AH-64s have been produced to date.

The U.S. Army is the primary operator of the AH-64; it has also become the primary attack helicopter of multiple nations, including Greece, Japan, Israel, the Netherlands and Singapore; as well as being produced under license in the United Kingdom as the AgustaWestland Apache. U.S. AH-64s have served in conflicts in Panama, the Persian Gulf, Kosovo, Afghanistan, and Iraq. Israel has made active use of the Apache in its military conflicts in Lebanon and the Gaza Strip, while two coalition allies have deployed their AH-64s in Afghanistan and Iraq.

General characteristics

    Crew: 2 (pilot, and co-pilot/gunner)
    Length: 58.17 ft (17.73 m) (with both rotors turning)
    Rotor diameter: 48 ft 0 in (14.63 m)
    Height: 12.7 ft (3.87 m)
    Disc area: 1,809.5 ft² (168.11 m²)
    Empty weight: 11,387 lb (5,165 kg)
    Loaded weight: 17,650 lb (8,000 kg)
    Max takeoff weight: 23,000 lb (10,433 kg)
    Powerplant: 2 × General Electric T700-GE-701 and later upgraded to T700-GE-701C (1990–present) & T700-GE-701D (AH-64D block III) turboshafts, -701: 1,690 shp, -701C: 1,890 shp, -701D: 2,000 shp (-701: 1,260 kW, -701C: 1,490 kW, -701D: 1,490 kW) each
    Fuselage length: 49 ft 5 in (15.06 m)
    Rotor systems: 4 blade main rotor, 4 blade tail rotor in non-orthogonal alignment

Performance

    Never exceed speed: 197 knots (227 mph, 365 km/h)
    Maximum speed: 158 knots (182 mph, 293 km/h)
    Cruise speed: 143 knots (165 mph, 265 km/h)
    Range: 257 nmi (295 mi, 476 km) with Longbow radar mast
    Combat radius: 260 nmi (300 mi, 480 km)
    Ferry range: 1,024 nmi (1,180 mi, 1,900 km)
    Service ceiling: 21,000 ft (6,400 m) minimum loaded
    Rate of climb: 2,500 ft/min (12.7 m/s)
    Disc loading: 9.80 lb/ft² (47.9 kg/m²)
    Power/mass: 0.18 hp/lb (0.31 kW/kg)

Armament

    Guns: 1× 30 × 113 mm (1.18 × 4.45 in) M230 Chain Gun with 1,200 rounds
    Hardpoints: Four pylon stations on the stub wings. Longbows also have a station on each wingtip for an AIM-92 ATAS twin missile pack.[47][199]
    Rockets: Hydra 70 70 mm, and CRV7 70 mm air-to-ground rockets
    Missiles: Typically AGM-114 Hellfire variants; AIM-92 Stinger may also be carried.

Avionics

    Lockheed Martin / Northrop Grumman AN/APG-78 Longbow fire-control radar

Cessna 170

The Cessna 170 is a light, single-engine, general aviation aircraft produced by the Cessna Aircraft Company between 1948 and 1956.

Crew: 1

Powerplants    
170 - One 110kW (145hp) Continental C1452 flat six piston engine driving a two blade fixed pitch McCauley propeller.
170B - One 110kW (145hp) Continental O300A.

Performance    
170 - Max speed 225km/h (122kt), max cruising speed 195km/h (106kt). Initial rate of climb 690ft/min. Service ceiling 15,000ft. Range 952km (514nm)
170B - Max speed 230km/h (124kt), max cruising speed 195km/h (106kt). Initial rate of climb 690ft/min. Service ceiling 15,500ft. Range 950km (513nm).

Weights    
170 - Empty 554kg (1220lb), max takeoff 998kg (2200lb).
170B - Empty 547kg (1205lb), max takeoff 998kg (2200lb).

Dimensions    
Wing span 10.97m (36ft 0in), length 7.61m (24ft 11.5in), height 2.01m (6ft 7in). Wing area 16.2m2 (174sq ft).

Capacity    
Typical seating for four.

Production    
In production between 1948 and 1957, 5173 Cessna 170s were built, including 730 170s and 1537 170As.

hawker 400

ok.. today i gone a show you hawker 400 basic status..

The aircraft was originally designed as the Mitsubishi MU-300 Diamond, an all-new, all-jet development to complement and slot above the Mitsubishi MU-2 and provide Mitsubishi Heavy Industries with their top-of-the-line corporate aircraft model (hence the name "Diamond").[5] The aircraft first flew on 29 August 1978. It is a small, low-winged twin-turbofan aircraft of all metal construction, flown by a crew of two pilots and accommodating eight passengers in a pressurised cabin. Its wings use a computer designed, supercritical airfoil in order to minimise drag. Its two Pratt & Whitney Canada JT15D turbofans are mounted on the rear fuselage.
Beechcraft bought the production rights and began manufacturing it as their own model, initially re-designated as the Beechjet 400. The Beechjet 400 was certificated by the Federal Aviation Administration in May 1986.

Raytheon/Beechcraft steadily developed their own improvements to the model, leading to the 400A in 1990. Improvements in the 400A include longer range, higher take-off weights and improved luxury appointments. An all-glass flight deck was also offered. Beechcraft also developed a version for the United States Air Force known as the T-1A Jayhawk, used as a trainer for large aircraft crews (such as tankers and strategic transports). A total of 180 T-1A trainers were delivered between 1992 and 1997. Another military variant is the Japan Air Self-Defense Force 400T trainer which shares the same Type Certificate as the T-1A.

In 1993 Raytheon purchased the Hawker business jet product line from British Aerospace. The Beechjet 400 was eventually renamed the Hawker 400 to map it into the Hawker product line. The Hawker 400XP incorporates further aerodynamic, mechanical and interior improvements gleaned from the Hawker 800XP.

In October 2008, Hawker Beechcraft announced upgrades to the design, resulting in the new model designation Hawker 450XP. Upgrades were to include new, more fuel efficient engines (Pratt & Whitney PW535Ds with 2,965 pounds of thrust each). The Hawker 450XP was canceled in June 2009 due to poor economic conditions.

Nextant Aerospace developed a program to remanufacture the Beechjet 400A, replacing the Pratt & Whitney engines with Williams FJ44s, plus a new avionics suite and interior, among other improvements. The remanufactured aircraft, called the Nextant 400XT, received FAA certification in October 2011.

General characteristics

    Crew: 2 pilots
    Capacity: 7—9 passengers
    Length: 48 ft 5 in (14.76 m)
    Wingspan: 43 ft 6 in (13.26 m)
    Height: 13 ft 11 in (4.24 m)
    Wing area: 241.4 sq ft (22.43 m²)
    Empty weight: 10,050 lb (4,558 kg)
    Useful load: 5,850 lb (2,653 kg)
    Max takeoff weight: 16,100 lb (7,303 kg)
    Powerplant: 2 × Pratt & Whitney Canada JT15D-5 turbofan, 2,900 lbf (12.9 kN) each

Performance

    Maximum speed: 468 knots (866 km/h, 539 mph) (Mach 0.78 MMO)
    Cruise speed: 443 knots (820 km/h, 510 mph) at 23,000 ft (7,000 m)
    Stall speed: 92 knots (171 km/h, 106 mph) (full flaps)
    Range: 1,693 nmi (3,135 km, 1,949 mi) at 45,000 ft (13,700 m)
    Service ceiling: 45,000 ft (13,700 m)
    Rate of climb: 3,770 ft/min (19.2 m/s)

Ka-50 "Black Shark"

The Kamov Ka-50 "Black Shark" is a single-seat Russian attack helicopter with the distinctive coaxial rotor system of the Kamov design bureau. It was designed in the 1980s and adopted for service in the Russian army in 1995. It is currently manufactured by the Progress company in Arsenyev.

During the late 1990s, Kamov and Israel Aerospace Industries developed a tandem-seat cockpit version, the Kamov Ka-50-2 "Erdogan", to compete in Turkey's attack helicopter competition. Kamov also designed another two-seat variant, the Kamov Ka-52 "Alligator" (Russian: Аллигатор, NATO reporting name: Hokum B).

General characteristics

Crew: One (for Ka-52: two)
Length: 16.0 m (52 ft 6 in)
Rotor diameter: 14.5 m (47 ft 7 in)
Height: 4.93 m (16 ft 2 in)
Disc area: 330.3 m² (3,555 ft²)
Empty weight: 7,700 kg (17,000 lb)
Loaded weight: 9,800 kg (21,600 lb)
Max takeoff weight: 10,800 kg (23,810 lb)
Powerplant: 2 × Klimov TV3-117VK turboshafts, 1,641 kW (2,200 shp) each
For Ka-52:
Loaded weight: 10,400 kg (22,930 lb)

Performance

Never exceed speed: 350 km/h (189 knots, 217 mph) in dive
Maximum speed: 315 km/h (170 knots, 196 mph) in level flight
Cruise speed: 270 km/h (146 knots, 168 mph)
Range: 545 km (339 miles)
Ferry range: 1,160 km (720 mi) with 4 drop tanks
Service ceiling: 5,500 m (18,000 ft)
Rate of climb: 10 m/s (32.8 ft/s)
Disc loading: 30 kg/m² (6 lb/ft²)
Power/mass: 0.33 kW/kg (0.20 hp/lb)

Armament

1x mobile semi-rigid 30 mm Shipunov 2A42 cannon (460 rounds total, dual feeding AP or HE-Frag)
A variety of payloads on the four under-wing hardpoints, including 23 mm UPK-23-250 gun pods (240 rounds each), 2 x APU-6 Missle racks, able to accommodate a total of 12 9K121 Vikhr anti-tank missiles, Vympel R-73 (NATO: AA-11 Archer) air-to-air missiles, 80 x 80 mm S-8 rockets and 20 x 122 mm S-13 rocket, Kh-25 semi-active laser guided tactical air-to-ground missiles, presumably S-25/S-25L high caliber rockets, 4x 250 kg (550 lb) bombs or 2x 500 kg (1,100 lb) bombs, 500 L (130 US gal) external fuel tanks. Reportedly, twin Igla light air-to-air missile launchers under each wingtip countermeasure pod (total 4 missiles). Maximum total payload 2,000 kg.
Two pods on the wingtips with flare and chaff countermeasure dispensers, 4 UV-26 dispensers each (total 512 chaff/flare cartridges in each pod)

F-16 Fighting Falcon

The General Dynamics F-16 Fighting Falcon is a multirole jet fighter aircraft originally developed by General Dynamics for the United States Air Force (USAF). Designed as an air superiority day fighter, it evolved into a successful all-weather multirole aircraft. Over 4,400 aircraft have been built since production was approved in 1976. Although no longer being purchased by the U.S. Air Force, improved versions are still being built for export customers. In 1993, General Dynamics sold its aircraft manufacturing business to the Lockheed Corporation, which in turn became part of Lockheed Martin after a 1995 merger with Martin Marietta.

The Fighting Falcon is a fighter with numerous innovations including a frameless bubble canopy for better visibility, side-mounted control stick to ease control while maneuvering, a seat reclined 30 degrees to reduce the effect of g-forces on the pilot, and the first use of a relaxed static stability/fly-by-wire flight control system that makes it a highly nimble aircraft. The F-16 has an internal M61 Vulcan cannon and has 11 hardpoints for mounting weapons, and other mission equipment. Although the F-16's official name is "Fighting Falcon", it is known to its pilots as the "Viper", due to it resembling a viper snake and after the Battlestar Galactica Colonial Viper starfighter.

In addition to active duty US Air Force, Air Force Reserve Command, and Air National Guard units, the aircraft is also used by the USAF aerial demonstration team, the U.S. Air Force Thunderbirds, and as an adversary/aggressor aircraft by the United States Navy. The F-16 has also been procured to serve in the air forces of 25 other nations.


General characteristics

Crew: 1
Length: 49 ft 5 in (15.06 m)
Wingspan: 32 ft 8 in (9.96 m)
Height: 16 ft (4.88 m)
Wing area: 300 ft² (27.87 m²)
Airfoil: NACA 64A204 root and tip
Empty weight: 18,900 lb (8,570 kg)
Loaded weight: 26,500 lb (12,000 kg)
Max takeoff weight: 42,300 lb (19,200 kg)
Powerplant: 1 × F110-GE-100 afterburning turbofan
Dry thrust: 17,155 lbf (76.3 kN)
Thrust with afterburner: 28,600 lbf (127 kN)

Performance

Maximum speed:
At sea level: Mach 1.2 (915 mph, 1,470 km/h)[44]
At altitude: Mach 2+ (1,500 mph, 2,410 km/h[1]) clean configuration
Combat radius: 340 mi (295 nmi, 550 km) on a hi-lo-hi mission with six 1,000 lb (450 kg) bombs
Ferry range: 2,280 NM (2,620 mi, 4,220 km) with drop tanks
Service ceiling: 60,000+ ft (18,000+ m)
Rate of climb: 50,000 ft/min (254 m/s)
Wing loading: 88.3 lb/ft² (431 kg/m²)
Thrust/weight: 1.095

Armament

Guns: 1× 20 mm (0.787 in) M61 Vulcan 6-barreled gatling cannon, 511 rounds
Hardpoints: 2× wing-tip Air-to-air missile launch rails, 6× under-wing & 3× under-fuselage pylon stations holding up to 17,000 lb (7,700 kg) of payload
Rockets:
4× LAU-61/LAU-68 rocket pods (each with 19× /7× Hydra 70 mm rockets, respectively) or
4× LAU-5003 rocket pods (each with 19× CRV7 70 mm rockets) or
4× LAU-10 rocket pods (each with 4× Zuni 127 mm rockets)
Missiles:
Air-to-air missiles:
2× AIM-7 Sparrow or
6× AIM-9 Sidewinder or
6× IRIS-T or
6× AIM-120 AMRAAM or
6× Python-4
Air-to-ground missiles:
6× AGM-45 Shrike or
6× AGM-65 Maverick or
4× AGM-88 HARM
Anti-ship missiles:
2× AGM-84 Harpoon or
4× AGM-119 Penguin
Bombs:
8× CBU-87 Combined Effects Munition
8× CBU-89 Gator mine
8× CBU-97 Sensor Fuzed Weapon
Wind Corrected Munitions Dispenser capable
4× GBU-10 Paveway II
6× GBU-12 Paveway II
4× JDAM
4× Mark 84 general-purpose bombs
8× Mark 83 GP bombs
12× Mark 82 GP bombs
8× Small Diameter Bomb
3× B61 nuclear bomb
Others:
SUU-42A/A Flares/Infrared decoys dispenser pod and chaff pod or
AN/ALQ-131 & AN/ALQ-184 ECM pods or
LANTIRN, Lockheed Martin Sniper XR & LITENING targeting pods or
up to 3× 300/330/370 US gallon Sargent Fletcher drop tanks for ferry flight/extended range/loitering time.

Avionics

AN/APG-68 radar

Mil Mi-24

The Mil Mi-24 is a large helicopter gunship and attack helicopterand low-capacity troop transport with room for 8 passengers. It is produced by Mil Moscow Helicopter Plant and operated since 1972 by the Soviet Air Force, its successors, and by over thirty other nations.

In NATO circles, the export versions, Mi-25 and Mi-35, are denoted with a letter suffix as "Hind D" and "Hind E" respectively. Soviet pilots called the aircraft "flying tank"(letayushchiy tank). More common unofficial nicknames were "Crocodile" due to the helicopter's camouflage scheme and "Glass" because of the flat glass plates which surround the

General characteristics

Crew: 2–3: pilot, weapons system officer and technician (optional)
Capacity: 8 troops or 4 stretchers
Length: 17.5 m (57 ft 4 in)
Rotor diameter: 17.3 m (56 ft 7 in)

Wingspan: 6.5 m (21 ft 3 in)

Height: 6.5 m (21 ft 3 in)
Disc area: 235 m² (2,530 ft²)
Empty weight: 8,500 kg (18,740 lb)
Max takeoff weight: 12,000 kg (26,500 lb)
Powerplant: 2 × Isotov TV3-117 turbines, 1,600 kW (2,200 hp) each

Performance

Maximum speed: 335 km/h (208 mph)
Range: 450 km (280 miles)
Service ceiling: 4,500 m (14,750 ft)

Armament

Possible armament configuration on Mi-24W
Yakushev-Borzov YakB-12.7 machine gun

Internal guns

flexible 12.7 mm Yakushev-Borzov Yak-B Gatling gun on most variants. Maximum of 1,470 rounds of ammunition.
fixed twin-barrel GSh-30K on the Mi-24P. 750 rounds of ammunition.
flexible twin-barrel GSh-23L on the Mi-24VP and Mi-24VM. 450 rounds of ammunition.
PKT passenger compartment window mounted machine guns

External stores

Total payload is 1,500 kg of external stores.
Inner hardpoints can carry at least 500 kg
Outer hardpoints can carry up to 250 kg
Wing-tip pylons can only carry the 9M17 Phalanga (in the Mi-24A-D) or the 9K114 Shturm complex (in the Mi-24V-F).

Bomb-load

Bombs within weight range (presumably ZAB, FAB, RBK, ODAB etc.), Up to 500 kg.
MBD multiple ejector racks (presumably MBD-4 with 4xFAB-100)
KGMU2V submunition/mine dispenser pods

First-generation armament (standard production Mi-24D)

GUV-8700 gunpod (with a 12.7 mm Yak-B + 2x7.62 mm GShG-7.62 mm combination or one 30 mm AGS-17)
UB-32 S-5 rocket launchers
S-24 240 mm rocket
9M17 Phalanga (a pair on each wingtip pylon)

Second-generation armament (Mi-24V, Mi-24P and most upgraded Mi-24D)

UPK-23-250 gunpod carrying the GSh-23L
B-8V20 a lightweight long tubed helicopter version of the S-8 rocket launcher
9K114 Shturm in pairs on the outer and wingtip pylons