Design, Fabrication, Testing, And Data Analysis Of Adam II Concept (Propulsive Wing). Part II. Shakedown Testing In Vad 7-Ft X 10-Ft Low Speed Wind Tunnel

Item

Title
Design, Fabrication, Testing, And Data Analysis Of Adam II Concept (Propulsive Wing). Part II. Shakedown Testing In Vad 7-Ft X 10-Ft Low Speed Wind Tunnel
Date
1968
Index Abstract
Not Available
Photo Quality
Not Needed
Report Number
AFFDL TR 68-31 Part 2
Creator
Meyer, Robert D.
English, Robert B.
Davidson, Jim K.
Corporate Author
LTV Aerospace Corp Dallas Tx Vought Aeronautics Div
Laboratory
Air Force Flight Dynamics Laboratory
Extent
54
Identifier
AD0832604
Access Rights
Export Controls
Distribution Classification
1
Contract
AF 33(615)-3293
DoD Project
1366
DoD Task
136617
DTIC Record Exists
No
Distribution Change Authority Correspondence
AFFDL LTR
Distribution Conflict
No
Special Scanning Requirements
Lots of fold out pages
Abstract
An analysis is presented of the data obtained from a short series of tests to "shakedown" a powered model of the ADAM II V/STOL concept. Correlating data from tests of a related semispan model are also included. Results show that the longitudinal stability of the present configuration in the cruise mode has a greater nariation with angle of attack and power than conventional airplanes. The data indicated that, for this test, possible lower surface flap separation and detached nose fan exit flow caused nonlinearities in pitching moment. These can be eliminated by redesign at critical points to provide good stability. The location of the horizontal tails in the wing tip vortex results in an upwash derivative (negative d(espilon)/d(alpha)) that results in a high level of horizontal tail contribution to stability. Although the basic low aspect ration horizontal tails were highly loaded and operating wih disturbed flow conditions much of the time, there was no indication of tail stall. Horizontal tail control effectiveness appears to be adequate at the present stability levels. The model was less stable directionally than longitudinally in the sense that a greater forward movement in c. g. location is required for neutral stability. In this test, directional stability was independent of angle of attack and power effects, and lateral stability was at all times positive and varied with angle of attack and power effects.
Report Availability
Full text available
Date Issued
1968-05
Provenance
Lockheed Martin Missiles & Fire Control
Type
report
Format
1 online resource
Media
AFFDLTR68-031part02.pdf