Accession Number:

AD0014890

Title:

SPIN AND RECOVERY TESTS OF A 1/28-SCALE MODEL OF THE YF-93A AIRPLANE

Descriptive Note:

Corporate Author:

AERONAUTICAL SYSTEMS DIV WRIGHT-PATTERSON AFB OH FLIGHT CONTROL LAB

Personal Author(s):

• Rose, Eugene S., Jr.
• Parker, Dan M.

Report Date:

1952-08-01

Pagination or Media Count:

50.0

Abstract:

Spin tests were made in the Wright Field 12-ft vertical wind tunnel. Conclusions are presented on the basis of these tests regarding the spin and recovery characteristics of the aircraft at 20,000 ft. These include 1 for all load conditions and configurations tested, with ailerons held against the spin stick left for a right spin, recovery attempts by full rudder reversal will fail to termiate the spin 2 satisfactory to marginal recoveries will result from full rudder reversal and simulataneous movement of ailerons to full with the spin stick right for a right spin 3 the elevators should be full up during the first part of the spin recovery attempt for fastest recovery and 4 the gross weight at take-off and the design gross weight over target conditions are more adverse to recovery

Descriptors:

• *JET FIGHTERS
• *SPIN RECOVERY
• FLIGHT TESTING
• RECOVERY
• LOADS(FORCES)
• REVERSIBLE
• ADVERSE CONDITIONS
• TAKEOFF
• RUDDERS
• SPINNING(MOTION)
• AILERONS

Subject Categories:

• Aerodynamics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE