Aerodynamic stability and drag characteristics of the MSFC pressure fed booster configurations at Mach numbers from 0.9 to5.0

摘要

Experimental aerodynamic investigations were conducted in the NASA/MSFC 14 x 14 Inch Trisonic Wind Tunnel during January 1972 on 0.003366 and 0.00419 scale models of the MSFC space shuttle pressure fed booster configurations. The configurations tested were a 40 deg cone/cylinder/13 deg flare with and without fins, a 40 deg cone/cylinder/13 deg flare/9 deg flare with and without fins, a 35 deg cone/cylinder with and without fins, a 35 deg cone/cylinder/7 deg flare and a 35 deg cone/cylinder with straight extension. Six component aerodynamic force and moment data were recorded over a Mach number range of 0.9 to 5.0. Model angle of attack range was -10 to 10 deg and 20 to 80 at 0 deg sideslip. Model sideslip range was -10 to 10 deg at nominal angles of attack of 0, 30 and 51 deg