Unsteady Low-Speed Windtunnel Test of a Straked Delta Wing, Oscillating in Pitch. Part 4. Plots of Time Histories of Pressures and Overall Loads
Abstract
Results of a wind tunnel test of an oscillating straked wing. The report 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 part IV, the plots of time history data for both pressures and overall air loads for continuous oscillating model are presented for conditions in which non- linearities and higher harmonics are expected. Appendix A includes the pressure plots in a 'carpet' format which shows the distributions at every 45 deg of phase angle in a manner similar to the unsteady flow visualization photos. The distributions are shown similarly for all four pressure sections. A survey of the test conditions and their runnumbers is given in table 10 of part I. Appendix B includes plots of overall air loads vs. incidence for continuous oscillating model. A survey of the runnumbers of these plots is given in table 11 of part I. Keywords: Unsteady flow; Vortex flow; Wind tunnel test.
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 01, 1988
- Accession Number
- ADA198682
Entities
People
- A. J. Persoon
- A. M. Cunningham Jr.
- C. S. Dogger
- E. G. Geurts
- R. G. Den Boer
Organizations
- General Dynamics