Accession Number:

AD0625819

Title:

HEAVY-LIFT TIP TURBOJET ROTOR SYSTEM. VOLUME 2. PARAMETRIC DESIGN STUDY

Descriptive Note:

Engineering rept.

Corporate Author:

HILLER AIRCRAFT CORP PALO ALTO CA

Personal Author(s):

Report Date:

1965-10-01

Pagination or Media Count:

103.0

Abstract:

The parametric analysis determines the optimum design parameters of a 24,000-lb.-payload helicopter powered by turbojet engines installed at the rotor blade tips. The method used determined a gross weight which would satisfy statistical component weight equations and aerodynamic equations simultaneously. The optimizing criterion was the minimum gross weight required to perform a specific mission. The results of the analysis indicate that the optimum configuration using the Continental Model 357-1 engine is a helicopter with a four blades, b two engines per blade, and c a crane-type fuselage. The optimum configuration with a generalized or rubber engine is a helicopter with a three blades, b one engine per blade, and c a crane-type fuselage.

Descriptors:

• *HELICOPTER ROTORS
• AERODYNAMIC CHARACTERISTICS
• HELICOPTERS
• LIFT
• OPTIMIZATION
• ROTOR BLADES(ROTARY WINGS)
• TURBOJET ENGINES
• WEIGHT

Subject Categories:

• Helicopters
• Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE