Accession Number:

AD0882220

Title:

Engineering flight Test AH-1G Helicopter (Hueycobra). Phase D. Airworthiness and Flight Characteristics. Part 2. Performance, Addendum

Descriptive Note:

Final rept. May 1968-Jan 1970

Corporate Author:

ARMY AVIATION SYSTEMS TEST ACTIVITY EDWARDS AFB CA

Personal Author(s):

• Finnestead, Rodger L.
• Connor, William J.
• Buss, Marvin W.

Report Date:

1971-03-01

Pagination or Media Count:

99.0

Abstract:

This addendum to the performance report presents the results of turning performance, in-ground-effect IGE level acceleration and deceleration performance and dive recovery tests. These three tests were conducted to validate portions of the AH-1G operators manual TM 55-1520-221-10 and enhance the knowledte of interested government agencies as to the limitations and capabilities of the AH-1G helicopter. Three major limitations were encountered during testing that restricted the pilot from achieving maximum performance level acceleration and deceleration performance IGE is limited by extreme pitch attitudes level deceleration performance is limited by the pilots ability to maintain rotor speed below the maximum limit 339 rpm the cyclic control feedback limits aircraft turning and dive recovery performance at heavy gross weight andor when high load factors are encountered.

Descriptors:

• *HELICOPTERS
• ACCELERATION
• DECELERATION
• FLIGHT TESTING
• HELICOPTER ROTORS
• LEVEL FLIGHT
• LOADS(FORCES)
• PITCH(MOTION)
• TURNING FLIGHT
• VELOCITY

Subject Categories:

• Helicopters

Distribution Statement:

APPROVED FOR PUBLIC RELEASE