Accession Number:

ADA339474

Title:

An Investigation of the Aerodynamic Performance of the Spin-Wing Concept

Descriptive Note:

Interim rept.

Corporate Author:

NAVAL RESEARCH LAB WASHINGTON DC OFF-BOARD COUNTERMEASURES BRANCH

Personal Author(s):

Report Date:

1998-02-27

Pagination or Media Count:

17.0

Abstract:

Unmanned air vehicles UAVs capable of vertical takeoff and landing VTOL are always of interest to the Navy. This paper examines the aerodynamic performance of a unique multi-mode aircraft concept called the spin-wingstop rotor. The spin wing uses its wing and tail as a counter-rotating rotor system for hovering flight. For forward flight, the wing and tail are stopped.

Subject Categories:

  • VSTOL
  • Pilotless Aircraft

Distribution Statement:

APPROVED FOR PUBLIC RELEASE