12E 19?? = 2pCH; 305hp Lycoming VO-540A; rotor: 35'0" length: 27'8" v: 95/87/0 range: 400. Army version H-23.
206 19?? = No data.
360 1949 = 2-3pO-CH; 178hp Franklin 6V4; rotor: 36'6" length: 37'10" load: 747# v: 105/85/0 range: 212. $19,995. First transcontinental helicopter flight, San Francisco-New York, in 1949.
Hiller 1099 [N3776G]
1099 1961 = 6p prototype of a turbine-powered (P&W PT6) transport helicopter using dynamic components of earlier models with a new and larger fuselage.
C-142 SEE Vought-Hiller-Ryan C-142.
FH-100 SEE Fairchild-Hiller.
Flying Platform SEE VZ-1.
H-1X SEE X2-235.
H-23, OH-23 Raven - Army version of 360. 2-4pCH; Franklin and Lycoming; rotor: 35'0"-35'5" length: 27'9". Redesignated OH-23 in mid-1962.
YH-23 1950 = 2p prototype. POP: 1 [50-1254].
H-32 Hornet 1951 = 2pCH; two 31# Hiller 8RJ2B ramjets. First certificated helicopter to use jet engines. As YH-32.
H0-1E SEE VZ-1.
HO-5, H-5 1961 = Military version of 206. POP: 5.
HOE SEE HJ-1.
Hornet 195? = 1pCH. No data.
HJ-1 Hornet 1952 = 2pO-CH; two 31# Hiller 8RJ2B ramjets; rotor: 23'0" v: 80/69/0 range: 50. POP: ??; 12 to AF as YH-32, 3 to USN as HOE [138651/138653].
HTE - Military version of UH-12.
HTE-1 1950 = Data similar to UH-12A. POP: 17 [125532, 128637/128652].
J-5 1946 = 1pOH. Hiller's first single-rotor craft; first helicopter to fly with torque-converted jet power.
ROE Rotorcycle 1958 = One-man, open, foldable helicopter. 45hp Nelson H63B; rotor: 18'6" v: 70/52/0 range: 37-166. Empty wt: 300#. Experiment in battlefield transport for ground troops, with simplified control systems. Tripod base. Assembled from a kit by one person in less than 10 minutes. POP: 5 as XROE-1 for USMC, plus 10 for NATO evaluation, but was considered impractical.
UH-1 SEE X2-235.
Hiller UH-4 [NX68276] (William T Larkins)
"United" UH-4 and office (unknown magazine clip)
UH-4 Commuter 1946 = 2pCH; 125hp Lycoming O-290; rotor: 33'0" load: 480# v: 100/75/0 range: 200. Twin coaxial rotors; won the Grand Award at 1947 World Inventors' Congress.
UH-5 1947 = 2pCH. Featured "Rotormatic Control," Hiller's servo-paddle method of cyclic control.
UH-12 Raven - 3pCH; 175hp Franklin 6V4; rotor: 35'0" length: 26'6" load: 965# v: 84/76/0 range: 210 ceiling: 10,000' (data for UH-12A). First production Hiller, based on 360, primarily specific for the agricultural market.
UH-12A 1948 =
Hiller UH-44 (Stanley Hiller)
UH-44 (XH-44) Hillercopter 1944 = 1pOH; 90hp Franklin, replaced by 125hp Lycoming O-290. Stanley Hiller Jr. First successful coaxial rotor system. Prototype built in Hiller's garage in Berkeley; never having flown, he crashed on his first test flight in July 1944. Undaunted, he persisted and created a most succesful post-war aviation industry. Basic design evolved into X2-235 and, ultimately, 360.
X-18 1959 = Tilt-wing VTOL rebuilt from Chase YC-122C; two 5850hp Allison turboprop T40A-14s from the abandoned Lockheed XFV-1 and Convair XFY-1 VTOL experiments + one Westinghouse J34-WE; span: 48'0" length: 63'0" v (est): 250. Six-blade contra-rotating props; J34 was installed in the aft fuselage to provide pitch control during vertical flight. POP: 1 [57-3078]; ff(as a conventional aircraft): 11/24/59 (p: George Bright, Bruce Jones). Test results were later employed in LTV-Ryan-Hiller XC-142A.
Hiller X2-235 Addison Street (Berkeley) back yard (Stanley Hiller)
X2-235, UH-1 1945 = Metal 2pCH evolution of UH-44 with 235hp Lycoming and counterrotating rigid rotors. POP: 2, plus 1 unfinished ship procured by USN for wind tunnel tests at NACA, field designation as UH-1X.
VZ-1 Pawnee (aka Flying Platform) 1955 = Evaluative production of a standing one-man aerial platform developed from a 1950 concept of Charles H Zimmerman (he called it his "Flying Shoes"). 5' fiberglass ring with two 40hp Nelson H-56 (three in the second and third ships), two coaxial counter-rotating props; diameter: 5'0" (6'0" in second prototype) v: 15; ff: 2/x/55. Planned use for combat troops as a "flying motorcycle." POP: 3 (the first prototype was not serialized) [56-6944/6945]. Project cancelled because of sluggish performance, a result of the Army's insistence on adding a third "back-up" engine, which also added needless weight. Interim USN designation of YHO-1E also assigned.