NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login
Back to Results
Spin and Recovery Characteristics of the Northrop XF-89 AirplaneThe spin and recovery characteristics of the Northrop XF-89 airplane, as well as the spin-recovery parachute requirements, the control forces that would be encountered in the spin, and the best method for the crew to attempt an emergency escape are presented in this report. The characteristics were mainly estimated rather than determined by model tests because the XF-89 dimensional and mass characteristics were such as to make this airplane similar to several others, models of which have previously been tested. Brief tests were made on an available model of similar design to augment the estimation. The results indicate that the recovery characteristics will be satisfactory for all airplane loadings if recovery is attempted by use of rudder followed by moving the elevator down. The rudder pedal forces will be within the capabilities of the pilot but the elevator stick forces will be beyond the pilot's capabilities unless a trim tab, or a booster is used. A 9.5-foot-diameter flat-type tail parachute or a 5.0-foot-diameter flat-type wing-tip parachute with a drag coefficient of 0.7 will be a satisfactory emergency spin-recovery device for spin demonstrations and if it is necessary for the crew to abandon the spinning airplane, they should leave from the outboard side of the cockpit.
Document ID
20090026468
Acquisition Source
Legacy CDMS
Document Type
Other - NACA Research Memorandum
Authors
Berman, Theodore (National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Date Acquired
August 24, 2013
Publication Date
February 28, 1949
Subject Category
Aircraft Stability And Control
Report/Patent Number
NACA-RM-SL9B28a
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

Related Records

There are no records associated with this record.
No Preview Available