Cessna Citation II Bravo

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Cessna Citation II Bravo Cessna Citation II Bravo http://bravo.cessna.com/gallery.chtml By: Rich Harris, Jenny Totten, and Josh DeMoss History History   Citation II Citation II intial intial design was announced in 1976 design was announced in 1976   The first deliveries were made in 1978 The first deliveries were made in 1978   Small business jet transport Small business jet transport   Design objectives Design objectives – – Low first costs Low first costs – – Economy of operation Economy of operation – – Safety Safety – – Good handling characteristics Good handling characteristics History History   The aircraft has wide operational flexibility The aircraft has wide operational flexibility   Designed to take off and land from most fields used by light and Designed to take off and land from most fields used by light and medium twin-engine propeller-driven aircraft, and from unpaved medium twin-engine propeller-driven aircraft, and from unpaved runways runways   Citation II is somewhat larger and heavier than the Citation I and Citation II is somewhat larger and heavier than the Citation I and has a longer range capability has a longer range capability   The Citation II was upgraded in 1984 with the improved Citation The Citation II was upgraded in 1984 with the improved Citation S-550 (S/II) S-550 (S/II)   Improvements were mainly aerodynamic Improvements were mainly aerodynamic – – New wing designed using supercritical technology New wing designed using supercritical technology – – JT15D4B turbofans JT15D4B turbofans   Citation II Bravo was introduced in 1994 Citation II Bravo was introduced in 1994 – – Certified in 1996 Certified in 1996 – – Improvements include upgraded avionics, trailing link Improvements include upgraded avionics, trailing link landing gear, more speed, range and payload landing gear, more speed, range and payload – – Deliveries began in February 1997 Deliveries began in February 1997 Basics Basics   The Citation II has an The Citation II has an unswept unswept, tapered wing , tapered wing   Aspect ratio = 7.8 Aspect ratio = 7.8   Airfoil-section thickness ratios that vary from 14 percent at the Airfoil-section thickness ratios that vary from 14 percent at the root to 12 percent at the tip. root to 12 percent at the tip.   Horizontal tail Horizontal tail – – Located near root of vertical fin Located near root of vertical fin – – Incorporates a small amount of dihedral to reduce immersion Incorporates a small amount of dihedral to reduce immersion in the jet exhaust in the jet exhaust   Vertical tail Vertical tail – – Relatively large dorsal fin Relatively large dorsal fin – – Small ventral fin Small ventral fin – – Improves directional stability Improves directional stability   Power supplied by two Pratt & Whitney PW503A turbofan engines Power supplied by two Pratt & Whitney PW503A turbofan engines – – 2885 pounds thrust each 2885 pounds thrust each – – Bypass ratio of 3.3 Bypass ratio of 3.3 High Lift & Control High Lift & Control   Single-slotted trailing-edge flap Single-slotted trailing-edge flap   No leading-edge devices No leading-edge devices   Spoilers located on the upper wing surface ahead of the flap Spoilers located on the upper wing surface ahead of the flap – – Used as air brakes Used as air brakes – – Not part of the lateral control system, which utilizes only Not part of the lateral control system, which utilizes only ailerons. ailerons.   Longitudinal control is by elevators Longitudinal control is by elevators   Trim obtained by an electrically operated trim tab on the elevator Trim obtained by an electrically operated trim tab on the elevator   All controls are manually operated All controls are manually operated 3 View Drawing 3 View Drawing http://www.aoc.noaa.gov/aircraft_cessna.htm Geometry Geometry 10 10 tail dihedral (deg) tail dihedral (deg) 4.5 4.5 wing dihedral (deg) wing dihedral (deg) 12.8 12.8 tail scrape angle (deg) tail scrape angle (deg) 0.445 0.445 tail taper ratio tail taper ratio 0.316 0.316 wing taper ratio wing taper ratio 0.12 0.12 wing t/c wing t/c tip tip 0.14 0.14 wing t/c wing t/c root root 0 0 sweep (deg) sweep (deg) 7.8 7.8 AR AR 67.07 67.07 S Stail tail (ft (ft22)) 1910 1910 S Swet wet (ft (ft22)) 323 323 S (ft S (ft22)) 47.2 47.2 L (ft) L (ft) 19 19 b btail tail (ft) (ft) 52.2 52.2 b bwing wing (ft) (ft) Other Dimensions Other Dimensions 947 cu ft 947 cu ft Cabin Baggage: Cabin Baggage: 28 cu ft 28 cu ft Nose Baggage: Nose Baggage: 491 cu ft 491 cu ft Useable Volume: Useable Volume: 4.9 ft 4.9 ft Cabin Width: Cabin Width: 20.9 ft 20.9 ft Cabin Length: Cabin Length: 22 in x 27 in 22 in x 27 in Baggage Doors (rear): Baggage Doors (rear): 39 in x 21.25 in 39 in x 21.25 in Cabin Doors: Cabin Doors: 14 ft 9.6 in 14 ft 9.6 in Tail Height: Tail Height: 4.8 ft 4.8 ft Fuselage Height: Fuselage Height: http://www.aoc.noaa.gov/aircraft_cessna.htm Performance Performance 2500 ft/min at sea level Rate of Climb 43,000 feet Ceiling 45.8 Wg/S 0.39 T/Wg 5008 Wfuel (lbs) 7800 We (lbs) 1992 WL (lbs) 14800 Wg (lbs) Aerodynamics Aerodynamics Tail carries 10.7% of lift Wing carries 89.3% of lift Load Split 17.75 ft back from Nose Center of Gravity 4.33 ft back from LE Neutral Point 158.4 Vstall (ft/s) 0.1785 CL alpha (per deg) 1.5359 CL max (TO) 26.31 (L/D)max 0.4192 CL cruise 0.0453 K Climb Performance Climb Performance 681 681 520 520 400 400 43,000 43,000 597 597 475 475 372 372 41,000 41,000 539 539 438 438 347 347 39,000 39,000 456 456 378 378 304 304 35,000 35,000 305 305 258 258 211 211 25,000 25,000 14,800 14,800 13,000 13,000 11,000 11,000 Altitude (ft) Altitude (ft) TAKEOFF WEIGHT (lbs) TAKEOFF WEIGHT (lbs) Fuel (lbs) Fuel (lbs) 141 141 100 100 74 74 43,000 43,000 109 109 84 84 63 63 41,000 41,000 90 90 71 71 55 55 39,000 39,000 66 66 54 54 43 43 35,000 35,000 34 34 28 28 23 23 25,000 25,000