Accession Number : ADA190497
Title : Performance Optimization of a Cruise Missile Using Dynamic-Stall Induced Lift Augmentation.
Descriptive Note : Master's thesis,
Corporate Author : AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING
Personal Author(s) : Dardis, William J , III
PDF Url : ADA190497
Report Date : Sep 1987
Pagination or Media Count : 153
Abstract : An investigation was conducted to study the possible performance benefits of using the augmented lift produced by dynamic stall-type airfoil motions to a cruise-missile-type aircraft in terms of range, climb capability, and susceptibility to threat. A baseline cruise-missile-type aircraft is defined and compared to three modified versions with augmented lift capability. The wings for the three dynamic-lift vehicles are sized to produce the same maximum lift coefficient, while operating dynamically, as the maximum usable lift aircraft. By resizing the wing through chord reduction, increases in straight-and-level range of 20 to 25% are found along with improvements in climb, pull over terrain, and pull up from a dive, capability. Moderate improvements in performance are found for the same aspect ratio vehicle. The vehicle resized by span reduction consistently under-performed all vehicles except in some examples of pull out to level flight. Two typical cruise missile-type missions were chosen and the trajectories of the four vehicles were modeled. minimum time above a reference altitude was determined for the two missions as a representative measure of suseptability to threat. Keywords: Dynamic stall.
Descriptors : *CRUISE MISSILES, *LIFT, AIRCRAFT, ALTITUDE, ASPECT RATIO, AUGMENTATION, CLIMBING, COEFFICIENTS, DYNAMICS, GUIDED MISSILE TARGETS, LEVEL FLIGHT, OPTIMIZATION, REDUCTION, STALLING, TERRAIN, THESES, THREATS, TRAJECTORIES, VEHICLES, WINGS
Subject Categories : Guided Missile Dynam, Config & Cntrl Surfaces
Distribution Statement : APPROVED FOR PUBLIC RELEASE