Aircraft Specifications

			AHS Members

Additional Information on the Aircraft

Manufacturer/Builder: Bell Aircraft
Aircraft Designation: HTL-2
Country of Origin: USA
Period:1946-1949
Configuration: Single Main Rotor w/ Tail Rotor

GENERAL INFORMATION

Contract Number: USN Noa(S)-9317 Seats: 2

Registration: USN: 122952-122963 Rotor Type: Semi-Rigid

Rotor Control: First Flight: Dec. 1947

Transmission: Gearbox:
9:1 Main Rotor Reduction
1.667:1 Tail Rotor Reduction Source: Rotary Wing Handbooks. Prewitt Aircraft, ca. 1950

MAIN ROTOR

Main Rotors:
1 ft
Rotor Disc Loading: 2.23 lb/sq ft

Rotor Diameter: 35.12 ft Rotor Power Loading: 12.1 lb/hp

Flight RPM: 285-350 Blade Area:

No. Blades:
2
Blade Dimensions:

Rotor Airfoil:
NACA 0018 (Root)
NACA 0011 (Tip)
Rotor Blade Loading: 61.0 lb/sq ft

Rotor Disc Area: 965 sq ft Rotor Tip Speed: 710 fps

Rotor Solidity: .032 Collective Pitch Range: .5 to 11 deg.

TAIL ROTOR

Tail Rotor: 2 bladed Tip Speed: 536 fps @ 1800 rpm

Diameter: 5.68 ft Pitch Range: (-10.5) deg. to 8.5 deg.

Disc Area: 25.31 sq ft Airfoil: NACA 23015 (Root)
NACA 23011 (Tip)

Solidity: .086 Power Loss While Hovering: 8.5 hp

STRUCTURE

Stabilizer Area: 4.5 sq ft Height: 9.14 ft

Aspect Ratio: 2:1 Width: unknown

Angle of Incidence: (-9) deg. Primary Construction: Steel Tube

Fuselage Length: 27.33 ft

ENGINE

Model: Franklin O-335-3 Fuel Capacity: 25 gal

Max Continuous Power: 178 hp ea. @ 3000 hp Fuel Consumption: .588 lb/bhp/hr @ max rpm

PERFORMANCE

Max Level Speed: 92 mph Hover Alt. in Ground Effect: 3,000 ft

Cruise Speed: 80 mph Hover Alt. out of Ground Effect: 800 ft

Range: 180 mi @ 80MPH Service Ceiling 10,700 ft

Best Vertical Speed: 850 fpm Absolute Ceiling: 12,000 ft

Rate of Descent:

WEIGHT AND BALANCE

Gross Weight: 2,158 lb Useful Load: 576 lb

Empty Weight: 1,582 lb CG Range: 4.88 in

GENERAL INFORMATION
Contract Number:	USN Noa(S)-9317	Seats:	2
Registration:	USN: 122952-122963	Rotor Type:	Semi-Rigid
Rotor Control:		First Flight:	Dec. 1947
Transmission:	Gearbox: 9:1 Main Rotor Reduction 1.667:1 Tail Rotor Reduction	Source:	Rotary Wing Handbooks. Prewitt Aircraft, ca. 1950

MAIN ROTOR
Main Rotors:	1 ft	Rotor Disc Loading:	2.23 lb/sq ft
Rotor Diameter:	35.12 ft	Rotor Power Loading:	12.1 lb/hp
Flight RPM:	285-350	Blade Area:
No. Blades:	2	Blade Dimensions:
Rotor Airfoil:	NACA 0018 (Root) NACA 0011 (Tip)	Rotor Blade Loading:	61.0 lb/sq ft
Rotor Disc Area:	965 sq ft	Rotor Tip Speed:	710 fps
Rotor Solidity:	.032	Collective Pitch Range:	.5 to 11 deg.

TAIL ROTOR
Tail Rotor:	2 bladed	Tip Speed:	536 fps @ 1800 rpm
Diameter:	5.68 ft	Pitch Range:	(-10.5) deg. to 8.5 deg.
Disc Area:	25.31 sq ft	Airfoil:	NACA 23015 (Root) NACA 23011 (Tip)
Solidity:	.086	Power Loss While Hovering:	8.5 hp

STRUCTURE
Stabilizer Area:	4.5 sq ft	Height:	9.14 ft
Aspect Ratio:	2:1	Width:	unknown
Angle of Incidence:	(-9) deg.	Primary Construction:	Steel Tube
Fuselage Length:	27.33 ft

ENGINE
Model:	Franklin O-335-3	Fuel Capacity:	25 gal
Max Continuous Power:	178 hp ea. @ 3000 hp	Fuel Consumption:	.588 lb/bhp/hr @ max rpm

PERFORMANCE
Max Level Speed:	92 mph	Hover Alt. in Ground Effect:	3,000 ft
Cruise Speed:	80 mph	Hover Alt. out of Ground Effect:	800 ft
Range:	180 mi @ 80MPH	Service Ceiling	10,700 ft
Best Vertical Speed:	850 fpm	Absolute Ceiling:	12,000 ft
Rate of Descent:

WEIGHT AND BALANCE
Gross Weight:	2,158 lb	Useful Load:	576 lb
Empty Weight:	1,582 lb	CG Range:	4.88 in