Performance Optimization of a Cruise Missile Using Dynamic-Stall Induced Lift Augmentation.
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.
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 01, 1987
- Accession Number
- ADA190497
Entities
People
- William J. Dardis Iii
Organizations
- Air Force Institute of Technology