This report, which is a natural sequel to Ref.3, presents the results obtained from a series of wind tunnel tests on an axi-symmetric body. These tests were conducted in a subsonic tunnel at a nominal Reynolds number of 580000 and measured the distribution of pressure on the body when set at a range of incidences from -2 degrees to 5 degrees. Using the measured pressure coefficients, load distribution, normal force, pitching moment and centre of pressure results were obtained. Comparison and correction of the measured data was obtained through the use of the panel method SPARV. The opportunity was taken to compare the RING SOURCE method, which was designed to deal with the potential flow around bodies of revolution, with inviscid SPARV. Starting in 1946 as the College of Aeronautics, the Cranfield Institute of Technology was granted university status in 1969. In 1993 it changed its name to Cranfield University.