Data obtained in study show that canting outward of propulsive nozzles on twin-nozzle booster rocket configuration was effective in reducing base drag over range of nozzle pressure ratios at supersonic speeds; reduction in drag was greatest near design pressure ratio of nozzle.
Measured base pressures on several twin rocket-nozzle configurations at mach numbers of 0.6 to 1.4 with effects due to nozzle canting and stabilizing fins
NASA -- Tech Note
1960
19 pages
Report
English
© Metadata Copyright Elsevier B. V. All rights reserved.
Aeroelastic investigation of three rocket fins at high mach numbers
Engineering Index Backfile | 1965
|