Investigation of the Low Speed Flow about a Straked Delta Wing Oscillating in Pitch. Part 1. Windtunnel, Model and Test Program

摘要

A low speed windtunnel test on a straked delta wing, oscillating in pitch, was conducted in the summer of 1986 in a cooperative program between General Dynamics (Fort Worth) and the National Aerospace Laboratory (NLR) of The Netherlands. Measurements of unsteady overall airloads and pressure distributions were performed covering a wide range of incidences (-8 to 50 deg) and amplitudes (1 to 16 deg). Most test cases were carried out at a windspeed of 80 m/s. The zeroth and first harmonic of the pressures and overall loads were measured. Also time recordings were made and stored for later study of higher harmonics, power spectra and cross correlation functions. At 30 m/s visualization of the unsteady flow was performed, using a smoke tube fixed to the model and a pulsating laser light sheet. A limited number of runs with maneuver-like inputs was carried out. At these runs only time recordings of the balance were made. Part I presents the test setup and the procedures used in the test. Also some examples of the results are shown. Part II presents a first analysis of the data, obtained during the experiment.