BUFFET RESPONSE OF AEROELASTICALLY SCALED TITAN III MISSILE CONFIGURATIONS AT TRANSONIC MACH NUMBERS
Technical rept. 18 Jan-10 Nov 1966
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN
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A wind tunnel investigation was conducted to obtain the structural response of 0.07-scaled aeroelastic models of Titan III missile configurations to buffet airloads at transonic Mach numbers. Test results in the form of bending-moment response in the pitch and yaw planes were obtained for various payload, upper stage, and booster combinations. The tests were conducted in the Mach number range from 0.6 to 1.4 and at angles of attack ranging from 0 to 4 deg. The basic CentaurVoyager configuration experienced flutter in the first pitch and yaw elastic bending modes as Mach number was increased above 0.80. The flutter was eliminated by 1 adding to the payload a cylindrical shroud having the same diameter as the payload and 2 adding to the payload a boattail shroud with a ring of vortex generators upstream of the boattail. The MOL and Apollo configurations exhibited slightly different trends in the bending-moment variations with Mach number, although both configuration families experienced peak loads at Mach numbers near 0.95. Increasing dynamic pressure caused a proportionate increase in the pitch and yaw structural response. Increasing angle of attack, in general, resulted in a reduction in the structural response, although there were deviations from this trend for certain configurations.
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