Accession Number : AD0913746
Title : The Effect of Simulated Ablation on the Longitudinal Stability of an 8% Scale Model Re-Entry Vehicle.
Descriptive Note : Master's thesis,
Corporate Author : AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING
Personal Author(s) : Manly, James H.
Report Date : MAR 1971
Pagination or Media Count : 85
Abstract : Wind tunnel tests were conducted to study the effect of simulated ablation on the longitudinal stability of an 8% scale model re-entry vehicle. As suggested in a previous study, commercial emery cloth was used to provide the roughness. When ablated, the model (designated as the FDL-8) pitched up at angles of attack above 16 deg, whereas without ablation instability was delayed until 21 deg. It is known that, when breakdown of leading-edge vortices occurs over a wing, there is a certain loss of lift, drag, and nose-down pitching moment. Using the tuft grid photograph technique and the total head survey technique, it was shown that the presence of the simulated ablation causes premature breakdown of lifting vortices found above the model and thus the early onset of instability.
Descriptors : (*REENTRY VEHICLES, ABLATION), SIMULATION, WIND TUNNEL MODELS, GUIDED MISSILE MODELS, STABILITY, ANGLE OF ATTACK, LEADING EDGES, VORTICES, SIMULATION, LIFT, FORCE(MECHANICS), MOMENTS, DRAG, PHOTOGRAPHY, THESES.
Subject Categories : Guided Missile Dynam, Config & Cntrl Surfaces
Guided Missile Reentry Vehicles
Distribution Statement : APPROVED FOR PUBLIC RELEASE