Nicholson Junior KN-2
| {{Infobox aircraft begin
| name=Junior KN-2 | image=File:Nicholson_Junior_KN-2.jpg | caption= }}{{Infobox aircraft type | type=Low power, two seat civil monoplane | national origin=United States | manufacturer=Kenny Flying Services | designer=Hugh G. Nicholson | first flight=early 1931 | introduced= | retired= | status= | primary user= | more users= | produced= | number built=1 | program cost= | unit cost= | developed from= | variants with their own articles= }} |
The Nicholson Junior KN-2 was a low power, high wing, two seat, cabin monoplane intended for sport or flight training in the United States in the late 1920s. Only one was built.
Design and development
The Junior KN-2 (KN came from the initials of builder Kenny and designer Nicholson) was a high wing monoplane with 5° of sweep and 1.5° of dihedral. The fabric-covered wings used the popular, flat-bottomed Clark Y profile and were built around laminated spars, aluminium alloy (Hyblum) ribs and steel tube drag struts. The ailerons were of the Frise type and had dural structures. The wings could be folded for transport or storage.
The fuselage was a Chromium-Molybdenum steel tube structure of Warren truss form and was fabric-covered. The engine was nose-mounted, with a choice between the Continental A40 flat four and the Szekely SR-3 three cylinder radial engines. Both provided about {{cvt|40|hp|kW}}. The Junior's two seat cabin was under the wing and provided two side-by-side seats with dual control. Behind the wing the fuselage tapered to the tail with the tailplane mounted on top, wire-braced from a triangular fin which carried a broad and largely straight-edged rudder.
The Junior's landing gear was fixed and conventional, with a long tailskid. It had Goodyear Airwheel mainwheels, with large, low pressure tyres on split axles with semi-oleo landing struts from the upper fuselage longerons and drag struts from the lower longerons. The wheeled undercarriage was designed so it could be easily replaced by floats.
Its benign flight characteristics had been established by June 1931 but with the Great Depression deepening, only one was completed.
Specifications
{{Aircraft specs
|prime units?=imp
|genhide=
|crew=one
|capacity=one passenger or student
|length m=
|length ft=23
|length in=
|length note=
|span m=
|span ft=37
|span in=
|span note=
|height m=
|height ft=
|height in=
|height note=
|wing area sqm=
|wing area sqft=190
|wing area note=plus {{cvt|21.5|sqft|m2}} ailerons
|aspect ratio=
|airfoil=Clark Y
|empty weight kg=
|empty weight lb=540
|empty weight note=
|gross weight kg=
|gross weight lb=980
|gross weight note=
|max takeoff weight kg=
|max takeoff weight lb=
|max takeoff weight note=
|fuel capacity={{cvt|11|USgal|Impgal l}}
|more general=
|eng1 number=1
|eng1 name=Continental A40 flat four or Szekely SR-3 3 cylinder radial engine
|eng1 type=
|eng1 kw=
|eng1 hp=40
|eng1 note= approximately. Source does not state which engine led to the given performance figures.
|power original=
|more power=
|prop blade number=2
|prop name=
|prop dia m=
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|perfhide=
|max speed kmh=
|max speed mph=85
|max speed kts=
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|cruise speed kmh=
|cruise speed mph=75
|cruise speed kts=
|cruise speed note=
- Landing speed: {{cvt|28|mph|km/h kn}}
- Take-off time: 8 s
|stall speed kmh=
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|never exceed speed kmh=
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|never exceed speed kts=
|never exceed speed note=
|range km=
|range miles=315
|range nmi=
|range note=
|endurance=
|ceiling m=
|ceiling ft=10000
|ceiling note=
|g limits=
|roll rate=
|glide ratio=12:1
|climb rate ms=
|climb rate ftmin=650
|climb rate note=initial
|time to altitude=
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|lift to drag=
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}}