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The A-10 Thunderbolt II by Andy Ko February 11, 2000

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Presentation on theme: "The A-10 Thunderbolt II by Andy Ko February 11, 2000"— Presentation transcript:

1 The A-10 Thunderbolt II by Andy Ko February 11, 2000

2 History Lessons learned from Korea and Vietnam War –Need for close air support –Model the A-1 Skyraider AX Program –June 1966 - USAF send RFP to 21 companies Parallel Paid Study Contract –1970 - Requirements finalized, bidding starts Northtrop & Fairchild Republic selected for fly-off –1972 - Fly-off begins –Jan 1973 - Fairchild’s A-10 announced to be the winner

3 Requirements Speed: 350-400 kts. 250 nm. operational radius with: –9500 lbs external stores and internal ammunition Field Length = 4000 ft. at Max TOGW Simplicity –Only proven/off-the-shelf technology –Exception: High BPR turbofans Survivability –Redundancy Cheap –$3.02 Million (F-16,F-18, Harrier) F-16, $9.5 - $12.8 Million F-18, $24 Million AV-8B, $23.7 Million

4 Graphics from Dana Bell, “A-10 Warthog in detail & Scale”, Dimensions Wing span57ft 6in Length overall53ft 4in Height overall14ft 8in Weights Operating empty24959lbs Basic design weight30384lbs Internal fuel10700lbs Max external load16000lbs Take-off weights Maximum50000lbs CAS mission47094lbs Anti-armour mission42071lbs Ferry49774lbs Never-exceed speed450kts Max level speed at sea level, clean381kts Combat speed at 5000ft with six380kts Mk82 bombs Cruising speed at sea level300kts Sea-level rate of climb at design weight6000ft/min Service ceiling45000ft Anti-armour configuration, 30min combat, 252nm 40nm penetration and exit CAS configuration, 1.88hr single-engine250nm loiter at 5000ft, 10min combat Ferry range, 50kt headwinds,2240nm 20 min reserve Performance Combat radii

5 Configuration Cantilever Low wing Airfoils –NACA 6716 on centerline, NACA 6713 at tip –Provides low wing loading (92.14 lb/sq ft) Wide Chords –Mean wing chord = 8ft 11.32in 2 segment, 3 position Fowler flaps –No leading edge devices Wide span ailerons –Dual upper and lower surfaces for airbrakes –SAS (Stability Augmentation System) H-Tail –No deep stall –Spin resistance Graphics from Dana Bell, “A-10 Warthog in detail & Scale”,

6 Configuration (Cont’d) Little Sweep –Mach number no greater than 0.68 Aspect Ratio = 6.54 Taper ratio = 0.65 Engines –TF34-GE-100 (6.2 BPR) –9065 lbs. Static thrust –Turbofan vs. Turboprop vs. Turbojet? –Placement Nozzles are canted 9º upward Landing Gear –Forward retracting –Exposed wheels when retracted

7 Improvements / Fixes Stall problem –Initially a fixed slat was installed, later changed to a movable slat –Stall strip added to the leading edge –Wing root modified with a fillet –Forward projecting strakes Drag improvements –Increased wing-span by 30 in. –Hoerner wingtips Induced drag Aileron effectiveness –Canopy and windscreen shapes refined –Pylons shortened and streamlined –Reduced landing gear pod cross section

8 Comparison with other Attack Aircraft * With combat load ** With external fuel tanks (tanks retained)

9 Survivability and Lethality Redundant control system –2 hydraulic controls (separated) and 1 cable manual reversion –H-tail provides 2 separated control surfaces Redundant structure Titanium bathtub for pilot –1.5 in thick bulletproof canopy Weapon loads –GAU-8/A Avenger 30mm seven barrel gun 1350 rounds at 2100 or 4200 rounds/min –11 store pylons with max external load of 16000 lbs Smithsonian Air & Space Magazine, March 1999, pg 27

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