Accession Number : AD0627132
Title : PRELIMINARY FLIGHT TEST DATA UH-2A JET AUGMENTED RESEARCH HELICOPTER MANEUVERABILITY AND DYNAMIC STABILITY EVALUATION.
Descriptive Note : Interim rept. no. 10.
Corporate Author : ARMY TRANSPORTATION RESEARCH COMMAND FORT EUSTIS VA
Report Date : JAN 1965
Pagination or Media Count : 43
Abstract : The report describes and presents the results of a flight research program to investigate the effect of horizontal thrust augmentation from an auxiliary jet engine on the maneuverability and dynamic stability of the UH-2 helicopter. The effect of transient and steady state load factors on the air-speed envelope, as limited by retreating blade stall, was examined for three values of thrust augmentation. The onset of blade stall is shown to be delayed to higher airspeed by the application of thrust augmentation; the extent of the delay increases with load factor. For a given amount of thrust augmentation, the load factor in transient maneuvers is shown to be higher than for steady accelerated flight conditions. The dynamic response of the helicopter in pitch and yaw to simulated gust inputs was examined for various combinations of thrust augmentation and airspeed. Thrust augmentation tends to decrease control sensitivity and to provide increased damping about both pitch and yaw axes following a disturbance. Qualitative pilot opinion indicates that the helicopter is generally easier to fly as thrust augmentation is added. (Author)
Descriptors : (*HELICOPTERS, HANDLING), MANEUVERABILITY, STABILITY, FLIGHT TESTING, THRUST AUGMENTATION, STALLING, JET ENGINES.
Subject Categories : Attack and Fighter Aircraft
Distribution Statement : APPROVED FOR PUBLIC RELEASE