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Static Longitudinal and Lateral Stability and Control Characteristics of a 1/15-Scale Model of the Grumman F9F-9 Airplane at a Mach Number of 1.41
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Author and Affiliation:
Palazzo, Edward B.(National Advisory Committee for Aeronautics. Langley Aeronautical Lab., Langley Field, VA, United States);
Spearman, M. Leroy(National Advisory Committee for Aeronautics. Langley Aeronautical Lab., Langley Field, VA, United States)
Abstract: An investigation has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel at a Mach number of 1.41 to determine the static stability and control and drag characteristics of a l/l5-scale model of the Grunman F9F-9 airplane. The effects of alternate fuselage shapes, wing camber, wing fences, and fuselage dive brakes on the aerodynamic characteristics were also investigated. These tests were made at a Reynolds number of 1.96 x l0 (exp 6) based on the wing mean aerodynamic chord of 0.545 foot. The basic configuration had a static margin of stability of 38.4 percent of the mean aerodynamic chord and a minimum drag coefficient of 0.049. For the maximum horizontal tail deflection investigated (-l0 deg), the maximum trim lift coefficient was 0.338. The basic configuration had positive static lateral stability at zero angle of attack and positive directional control throughout the angle-of-attack range investigated up to ll deg.
Publication Date: Jan 01, 1954
Document ID:
20090023310
(Acquired Jun 18, 2009)
Subject Category: AERODYNAMICS
Report/Patent Number: NACA-RM-SL54G08
Document Type: Technical Report
Financial Sponsor: National Advisory Committee for Aeronautics; Washington, DC, United States
Organization Source: National Advisory Committee for Aeronautics. Langley Aeronautical Lab.; Langley Field, VA, United States
Description: 33p; In English; Original contains black and white illustrations
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: No Copyright
NASA Terms: AERODYNAMIC BRAKES; AERODYNAMIC CHARACTERISTICS; AERODYNAMIC DRAG; ANGLE OF ATTACK; DIRECTIONAL CONTROL; F-9 AIRCRAFT; FUSELAGES; LATERAL STABILITY; LIFT; LONGITUDINAL STABILITY; MACH NUMBER; REYNOLDS NUMBER; SUPERSONIC WIND TUNNELS; WIND TUNNEL TESTS; WING CAMBER
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