Description
At supersonic speeds the values of C sub m sub o predicted and measured by the N.A.E. were found to disagree with the values measured by the N.A.C.A. In an attempt to discover a possible explanation for this discrepancy a detailed investigation was made in the area of interest and at a Mach number of 1.57. The effect of tunnel flow angularity was assessed by testing the model in both the inverted and upright positons while the effect of flow through the rather long and narrow intake ducts of the model was determined by testing the model with and without fairings over the intakes. In addition the effect of duct flow on the drag was determined at zero lift.
