Hodkinson HT-1
| {{Infobox aircraft begin
| name= | image=Hodkinson HT-1 Aero Digest September 1929.jpg | caption= }}{{Infobox aircraft type | type=Six or seven passenger transport | national origin=U.S. | manufacturer=Valley Manufacturing Co., a division of Hodkinson Aircraft | designer=Don R. Berlin | first flight=17 July 1929 | introduced= | retired= | status= | primary user= | more users= | produced= | number built=1 | program cost= | unit cost= }} |
The Hodkinson HT-1 was a U.S., eight place, three-engined sesquiplane, first flown in 1929. Despite an order for five, only one had been completed before Hodkinson Aircraft went bankrupt near the start of the Great Depression. It operated in Guatemala for several years.
Design and development
Hodkinson Aircraft was founded in 1929 by William Wadsworth Hodkinson, one of the pioneers of the film industry who in 1916 had organized Paramount Pictures. He later went into film distribution, founding the W.W.Hodkinson Co. and then moved into the aviation business. The HT-1 was built by Valley Manufacturing Co. a division of Hodkinson Aircraft based in Glendale, California. Its designer, Don R. Berlin, later designed the Curtiss P-40.
The wings of the HT-1 were both built around spruce spars and had rectangular plans out to rounded tips. The upper wing, with three-quarters of the total wing area, provided most of the lift and mounted narrow chord, Friese ailerons that reached from wingtips to above the outer engines. The short, lower wings were braced to the upper ones with parallel interplane struts between the wing spars.
The HT-1 was powered by three {{cvt|170|hp|kW}} Curtiss Challenger radial engines, one in the nose and the others on top of the lower wing, braced by vertical struts to the upper spars. Behind the central engine the fuselage was flat sided, with the wing centre-section fixed to it by inverted V cabane struts faired into the fuselage's chrome-molybdenum tube structure. These provided a clear rear view from the pilots' cabin under the leading edge of the wing. Pilot and co-pilot sat side-by-side with dual controls, though the co-pilot's controls could be removed to allow an extra passenger to be carried. Their cabin was normally accessed through doors on either side but there was also a door in the rear which led down to the passengers' windowed, six seat cabin. There was a toilet at the back and also a baggage compartment, though this was only accessible from outside. Cabin access was via doors on either side, opening just ahead of the rear seats.
Its tail was conventional, The fixed surfaces, like the fuselage, had chrome-molybdenum tube structures and the tailplane was mounted on top of the fuselage. The fin was braced to the tailplane and had a cropped, roughly triangular profile. The balanced rudder had a blunted rectangular profile.
The HT-1 had fixed, wide track, conventional ({{cvt|16|ft|6|in|m}}), landing gear. Its mainwheels, fitted with brakes, were on axles and drag struts from the lower fuselage longerons which placed them below the outer engines. Vertical shock absorber legs joined the lower wing engine mountings. There was a tailwheel at the rear.
Operational history
The HT-1 first flew on 17 July 1929. It was publicized at the Cleveland Aero Show in September 1929 and entered into the Cleveland based 1929 National Air Races. It won a contract for five examples from a Guatemalan airline, Companía Nacional de Aviación, which Hodkinson had founded but Hodkinson Aircraft were in financial difficulties in 1930 as the depression deepened. Though the company ceased trading in 1930, the prototype went to Guatemala and remained in use there for several years.
Specifications
{{Aircraft specs
|ref=Aero Digest (November 1929)
|prime units?=imp
|genhide=
|crew= two or one
|capacity= six or seven passengers
|length ft=36
|length in=3
|length note=
|upper span ft=56
|upper span in=
|upper span note=
|lower span ft=30
|lower span in=6
|lower span note=
|height ft=11
|height in=10
|height note=
|wing area sqm=
|wing area sqft=430
|wing area note= upper wing, {{cvt|139|sqft|m2}}
|aspect ratio=
|airfoil=
|empty weight lb=4300
|empty weight note=
|gross weight lb=6950
|gross weight note=
- Payload: {{cvt|1560|lb|kg}}
|max takeoff weight kg=
|max takeoff weight lb=
|max takeoff weight note=
|fuel capacity={{cvt|160|USgal|Impgal l}} total in two upper wing tanks
|more general=
|eng1 number=3
|eng1 name=Curtiss Challenger
|eng1 type=six cylinder, double row radial
|eng1 hp=170
|power original=
|thrust original=
|more power=
|prop blade number=2
|prop name=Hamilton Standard
|prop dia m=
|prop dia ft=
|prop dia in=
|prop dia note=
|perfhide=
|max speed mph=115
|max speed note=
|cruise speed mph=100
|cruise speed note=
|stall speed kmh=
|stall speed mph=
|stall speed kts=
|stall speed note=
- Landing speed: {{cvt|50|mph|km/h kn}}
|never exceed speed kmh=
|never exceed speed mph=
|never exceed speed kts=
|never exceed speed note=
|range miles=500
|range note=
|endurance=
|ceiling ft=13400
|ceiling note=
|g limits=
|roll rate=
|climb rate ftmin=860
|climb rate note=at sealevel
|time to altitude=
|lift to drag=
|wing loading kg/m2=
|wing loading lb/sqft=
|wing loading note=
|fuel consumption kg/km=
|fuel consumption lb/mi=
|power/mass=
|thrust/weight=
|more performance=
}}
References
{{reflist|refs=
|volume=15|number=5| publisher=Aeronautical Digest Publishing Corp| location=New York City}}
|volume=15|number=3| publisher=Aeronautical Digest Publishing Corp| location=New York City}}
{{cite web |url=https://www.imdb.com/name/nm0388314/bio|title=W.W.Hodkinson|website=IMDb |access-date=10 June 2020}}
}}