1956•Unpublished venueRequires access
Static longitudinal stability and control characteristics of a model of a 45 degree swept-wing fighter airplane at Mach numbers of 1.41, 1.61, and 2.01
Cornelius Driver, Gerald V. Foster
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Abstract
Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel to determine the static longitudinal stability and control characteristics of a model of a 45 degree swept-wing fighter airplane at three Mach numbers. The results indicate that the static margin, which was fairly constant through the lift range, decrease from 32 to 27 percent mean aerodynamic chord with increase in Mach number from 1.41 to 2.01.