Accession Number:

ADA595716

Title:

Hover and Wind-Tunnel Testing of Shrouded Rotors for Improved Micro Air Vehicle Design

Descriptive Note:

Doctoral thesis

Corporate Author:

MARYLAND UNIV COLLEGE PARK DEPT OF AEROSPACE ENGINEERING

Personal Author(s):

Report Date:

2008-01-01

Pagination or Media Count:

351.0

Abstract:

The shrouded-rotor configuration has emerged as the most popular choice for rotary-wing Micro Air Vehicles MAVs, because of the inherent safety of the design and the potential for significant performance improvements. However, traditional design philosophies based on experience with large-scale ducted propellers may not apply to the low-Reynolds-number 20,000 regime in which MAVs operate. An experimental investigation of the effects of varying the shroud profile shape on the performance of MAV-scale shrouded rotors has therefore been conducted. Hover tests were performed on seventeen models with a nominal rotor diameter of 16 cm 6.3 in and various values of diffuser expansion angle, diffuser length, inlet lip radius and blade tip clearance, at various rotor collective angles. Compared to the baseline open rotor, the shrouded rotors showed increases in thrust by up to 94, at the same power consumption, or reductions in power by up to 62 at the same thrust. These improvements surpass those predicted by momentum theory, due to the additional effect of the shrouds in reducing the non-ideal power losses of the rotor. Increasing the lip radius and decreasing the blade tip clearance caused performance to improve while optimal values of diffuser angle and length were found to be 10 and 50 of the shroud throat diameter, respectively. With the exception of the lip radius, the effects of changing any of the shrouded-rotor parameters on performance became more pronounced as the values of the other parameters were changed to degrade performance. Measurements were also made of the wake velocity profiles and the shroud surface pressure distributions. The uniformity of the wake was improved by the presence of the shrouds and by decreasing the blade tip clearance, resulting in lower induced power losses. For high net shroud thrust, a favorable pressure distribution over the inlet was seen to be more important than in the diffuser.

Subject Categories:

  • Aerodynamics
  • Military Aircraft Operations
  • Marine Engineering

Distribution Statement:

APPROVED FOR PUBLIC RELEASE