Unsteady Low-Speed Windtunnel Test of a Straked Delta Wing, Oscillating in Pitch. Part 3. Plots of the Zeroth and First Harmonic Unsteady Pressure Distributions (Concluded) and Plots of Steady and First Harmonic Unsteady Overall Loads
Abstract
This report contains results of a wind tunnel test of an oscillating straked wing. It provides unsteady airloads and pressure distributions for a range of incidences (-8 to 50 deg.) and amplitudes (1 to 16 deg.). The wind speed was 80 meters/second, which provided reduced frequencies up to 0.50 based on root chord. The zeroth and first harmonic as well as the continuous time history of the pressure and overall loads were measured. Flow visualization was performed for flow of 30 meters/second using a pulsating laser light sheet. In this part, appendix A presents the remainder of the unsteady zeroth and first order harmonic components of the unsteady pressure distribution plots for which the preceding runs were given in appendix B of part II. In appendix B, plots of the steady and the zeroth and first order harmonic components of the unsteady overall loads are presented. These results are presented as functions of angle of attack, frequency and amplitude in various forms for all measured components. Keywords: Unsteady flow, Vortex flow, Delta wings, Strakes, Joint test and evaluation, Netherlands.
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 01, 1988
- Accession Number
- ADA197541
Entities
People
- A. J. Persoon
- A. M. Cunningham Jr.
- A. P. Retel
- C. S. Dogger
- E. G. Geurts
- R. G. Den Boer
- R. J. Zwaan
Organizations
- General Dynamics