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Bushby Midget Mustang II

midgmust2

 


In 1963 Robert Bushby began work on a two place design based on the Midget Mustang. In 1965 the first ever Mustang II (N1117M) was brought to the EAA convention at Rockford (by trailer). In July 1966 the prototype was flown to the convention and was well received.


The Mustang II is a high performance side by side seating aircraft, featuring a tapered wing with a laminar flow airfoil to give the Mustang a cruising speed of 215mph on 180hp.


Due to aerodynamic as well as geometric washout in the wing, the Mustang has very good stall characteristics. At gross weight the wing loading is 16.5 lb/ft^2, high enough for a good ride but still allowing for a stall speed of 58mph in the landing configuration. The Mustang II has an excellent stall/spin safety record and compares quite favorably to other homebuilt as well as factory built designs. Most new Mustang flyers have less than 300 hours total time. Transitioning into a Mustang II can be compared to stepping up to a Cessna 182 Skylane. With fixed landing gear it has very good short field capabilities operating off of sod strips as short as 1600 feet with a large safety margin.


Construction is all metal with stressed skins There are no complicated fittings or parts that require special skills or tools. The wings are made in three parts, namely a constant chord centre section and tapered outer panels. The wing is a two spar flush riveted stress skin aluminium structure having aluminium ailerons and plain trailing edge flaps. The fuselage is a flush riveted stressed skin aluminium monocoque structure. The empennage is acantilever all metal structure with a controllable trim tab on the starboard elevator. A 10 Imp.gal. fuel tank is fitted behind the firewall. The Mustang II can now be equipped with the 150-hp Lycoming and Rayjay RJ0325 turbocharger.
Price in 1982:  $4,500. All metal components included. Other parts available separately. Units delivered to June 1982: 1100.


The cockpit is about 39 inches wide, with a sliding bubble canopy.  It can be custom fit for the tallest of pilots.  The baggage compartment located behind the seats will hold up to 80lbs.  There is space in the tailcone for additional storage if careful attention is given to the center of gravity.


At 1350 pounds gross the design is fully aerobatic to +6/-4.5 G's. Ultimate strength is 9 G's and it has a roll rate of over 180 degrees per second. It's controls are light and responsive making it a good "sport" aerobatic airplane with proper training.

 

midgmust2-2


In 1963 Robert Bushby began work on a two place design based on the Midget Mustang. In 1965 the first ever Mustang II (N1117M) was brought to the EAA convention at Rockford (by trailer). In July 1966 the prototype was flown to the convention and was well received.


The Mustang II is a high performance side by side seating aircraft, featuring a tapered wing with a laminar flow airfoil to give the Mustang a cruising speed of 215mph on 180hp.


Due to aerodynamic as well as geometric washout in the wing, the Mustang has very good stall characteristics. At gross weight the wing loading is 16.5 lb/ft^2, high enough for a good ride but still allowing for a stall speed of 58mph in the landing configuration. The Mustang II has an excellent stall/spin safety record and compares quite favorably to other homebuilt as well as factory built designs. Most new Mustang flyers have less than 300 hours total time. Transitioning into a Mustang II can be compared to stepping up to a Cessna 182 Skylane. With fixed landing gear it has very good short field capabilities operating off of sod strips as short as 1600 feet with a large safety margin.


Construction is all metal with stressed skins There are no complicated fittings or parts that require special skills or tools. The wings are made in three parts, namely a constant chord centre section and tapered outer panels. The wing is a two spar flush riveted stress skin aluminium structure having aluminium ailerons and plain trailing edge flaps. The fuselage is a flush riveted stressed skin aluminium monocoque structure. The empennage is acantilever all metal structure with a controllable trim tab on the starboard elevator. A 10 Imp.gal. fuel tank is fitted behind the firewall. The Mustang II can now be equipped with the 150-hp Lycoming and Rayjay RJ0325 turbocharger.
Price in 1982:  $4,500. All metal components included. Other parts available separately. Units delivered to June 1982: 1100.


The cockpit is about 39 inches wide, with a sliding bubble canopy.  It can be custom fit for the tallest of pilots.  The baggage compartment located behind the seats will hold up to 80lbs.  There is space in the tailcone for additional storage if careful attention is given to the center of gravity.


At 1350 pounds gross the design is fully aerobatic to +6/-4.5 G's. Ultimate strength is 9 G's and it has a roll rate of over 180 degrees per second. It's controls are light and responsive making it a good "sport" aerobatic airplane with proper training.


The prototype has been upgraded from an O-290 to an O-320 160hp Lycoming. It has had a tri-gear conversion, various wood props, a constant speed prop, and a folding wing design added to it. Since 1965, N1117M has flown to every yearly national EAA convention (Rockford, Milwaukee, or Oshkosh) except one (1997).


After 30+ years of developing and supporting the Mustang II and Midget, Robert Bushby sold the design rights to Mustang Aeronautics headed by Chris Tieman in 1992. Both designs were originally plans built only. Today, the kits have been refined to modern advanced assembly kits that greatly simplify construction. This has resulted in a strong resurgence in the popularity of the Mustang II as build times of less than 3 years part time work (10-15 hrs/week) are typical.

Engine: Lycoming O-320, 160 hp
Cockpit width: 40 in
Wing span: 24 ft 4 in
Length: 19 ft 6 in
Height: 5 ft 5 in
Wing area: 97.1 sq.ft
Aileron area: 4.80 sq.ft
Flap area: 8.0 sq.ft
Stabilizer area: 9.5 sq.ft
Elevator area: 6.4 sq.ft
Fin area: 4.2 sq.ft
Rudder area: 3.7 sq.ft
Wheel tread: 6 ft 10 in
Overall folded width: 8 ft 5 in
Width wings removed: >8 ft
Empty weight: 930 to 1100 lb
Recommended gross weight: 1600 lbs. (utility cat.)
Wing loading: 16.5 lb/sq.ft
Fuel: 25 to 61 USgal
Baggage: 80 lbs.
Top speed (sea level): 210 mph
Cruise speed (TAS, 75% power @ 8000 ft.): 195 mph
Range @ 75% POWER (37 USgal. version): 780 miles
Range @ 75% pwr (48 USgal w/ wet wing): 1000 miles
Rate of climb: 1500 fpm
Service ceiling: 17,000 ft
Stall speed (clean): 62 mph
Stall speed (full flap): 58 mph
Take off distance: 570 ft
Landing distance: 680 ft
Roll rate: 1900/sec
Power loading:10.0 lb/hp

Engine: Lycoming IO-360, 200 hp
Cockpit width: 40 in
Wing span: 24 ft 4 in
Length: 19 ft 6 in
Height: 5 ft 5 in
Wing area: 97.1 sq.ft
Aileron area: 4.80 sq.ft
Flap area: 8.0 sq.ft
Stabilizer area: 9.5 sq.ft
Elevator area: 6.4 sq.ft
Fin area: 4.2 sq.ft
Rudder area: 3.7 sq.ft
Wheel tread: 6 ft 10 in
Overall folded width: 8 ft 5 in
Width wings removed: >8 ft
Empty weight: 930 to 1100 lb
Recommended gross weight: 1600 lbs. (utility cat.)
Wing loading: 16.5 lb/sq.ft
Fuel: 25 to 61 USgal
Baggage: 80 lbs.
Top speed (sea level): 230 mph
Cruise speed (TAS, 75% power @ 8000 ft.): 220 mph
Range @ 75% POWER (37 USgal. version): 770 miles
Range @ 75% pwr (48 USgal w/ wet wing): 990 miles
Rate of climb: 1900 fpm
Service ceiling: 20,000 ft
Stall speed (clean): 62 mph
Stall speed (full flap): 58 mph
Take off distance: 470 ft
Landing distance: 680 ft
Roll rate: 1900/sec
Power loading: 8.0 lb/hp

 

 


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