Dynamic Longitudinal Stability Characteristics of a Swept-Wing Fighter-Type Airplane at Mach Numbers Between 0.36 and 1.45

Wolowicz, Chester H. (1957) Dynamic Longitudinal Stability Characteristics of a Swept-Wing Fighter-Type Airplane at Mach Numbers Between 0.36 and 1.45. Technical Report NACA RM H56H03, Research Engineering, NASA Dryden Flight Research Center.

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Abstract

As part of the flight research program conducted by the National Advisory Committee for Aeronautics on a swept-wing fighter-type airplane not equipped with an automatic pitch damper, pulse maneuvers were performed at altitudes from 10,000 to 40,000 feet over a Mach number range from 0.36 to 1.45 to determine the longitudinal stability characteristics and derivatives for an original-wing and an extended wing-tip configuration. The longitudinal dynamic behavior of the airplane during simulated combat maneuvers at altitudes of 30,000 to 40,000 feet was not considered satisfactory, especially at supersonic speeds, because of insufficient pitch damping. The addition of the wing-tip extensions caused a slight favorable shift in the aerodynamic center of the airplane. The static margin of the extended wing-tip configuration is of the order of 12 percent mean aerodynamic chord in the subsonic region and 29-percent mean aerodynamic chord at Mach numbers above 1.2. Wind-tunnel data for the two wing configurations investigated showed good agreement with transonic flight results for the lift-curve slope and the static stability derivative C (sub m, sub alpha); poor agreement was evident in the supersonic region.

EPrint Type:	NACA Report
Subjects:	Not Categorized (01 - 09) Aeronautics: (08) Aircraft Stability And Control NACA Publication
ID Code:	922
Deposited On:	01 June 2006
Additional Information:	29 pages.