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Transonic-Flutter Investigation of Wings Attached to Two Low-Acceleration Rocket-Propelled Vehicles

Flight Investigation of the Jettisonable-Nose Method of Pilot Escape Using Rocket-Propelled Models

Free-flight investigation of the full-scale Hughes Falcon missile, D configuration, to determine aileron effectiveness and damping in roll

Free-flight tests of 45 degree swept wings of aspect ratio 3.15 and taper ratio 0.54 to measure wing damping of the first bending mode and to investigate the possibility of flutter at transonic speeds

Free-Flight Investigation of the Full-Scale Hughes Falcon Missile, D Configuration, to Determine Aileron Effectiveness and Damping in Roll

Free-flight Tests of 45 Deg Swept Wings of Aspect Ratio 3.15 and Taper Ratio 0.54 to Measure Wing Damping of the First Bending Mode and to Investigate the Possibility of Flutter at Transonic Speeds

Some Effects of Roll Rate on the Longitudinal Stability Characteristics of the Hughes Falcon Missile, ''C'' Configuration, for a Mach Number Range of 1.1 to 1.8 as Determined From Flight Test

Some Effects of Roll Rate on the Longitudinal Stability Characteristics of a Cruciform Missile Configuration as Determined From Flight Test for a Mach Number Range of 1.1 to 1.8

Some Effects of Roll Rate on the Longitudinal Stability Characteristics of a Cruciform Missile Configuration as Determined From Flight Test for a Mach Number Range of 1.1. To 1.8

Stability of two rocket-propelled models having aspect-ratio-5 unswept tails on a long body for the Mach number range of 1.7 to 2.4


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