METHOD FOR OBTAINING AERODYNAMIC DATA ON HYPERSONIC CONFIGURATIONS WITH SCRAMJET EXHAUST FLOW SIMULATION

摘要

This report describes a hypersonic wind tunnel test method for obtaining credible aerodynamic data on a complete hypersonic vehicle (generic X-24c) with scramjet exhaust flow simulation. The general problems of simulating the scramjet exhaust as well as accounting for scramjet inlet flow and vehicle forces are analyzed and candidate test methods are described and compared. The method selected as most useful makes use of a thrust-minus-drag flow-through balance with a completely metric model. Inlet flow is diverted by a fairing. The incremental effect of the fairing is determined in the testing of two reference models. The net thrust of the scramjet module is an input to be determined in large-scale module tests with scram¬jet combustion, force accounting is described and examples of force com¬ponent levels are predicted. Compatibility of the test method with candi¬date wind tunnel facilities is described and a preliminary model mechanical arrangement drawing is presented. The balance design and performance requirements are described in a detailed specification. Calibration pro¬cedures, model instrumentation, and a test plan for the model are outlined.