Abstract:
Methods of predicting shock pressure recovery and external drag at all mass flows have been developed for conical centre-body intakes at supersonic speeds. Comparison with wind-tunnel measurements shows that the method for predicting the shock pressure recovery gives the correct variation for the shock losses as the shock configuration changes with mass-flow ratio. Agreement near full mass flow is not so good when the losses other than shock losses are probably changing rapidly and the shock configuration remains unchanged. Results of drag tests show that reasonable agreement with theory is obtained for the rise in drag which occurs when the intake is spilling and for the drag at full mass flow. Curves are included to assist in the calculation of the drag rise and the associated reduction in pressure recovery.
