Studies of the Flow Pattern at the Base of Missiles with Rocket Exhaust Jets

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Studies of the Flow Pattern at the Base of Missiles with Rocket Exhaust Jets

B. H. Goethert / L. T. Barnes

This report gives a brief summary of the studies which are being conducted in the Engine Test Facility of the Arnold Engineering Development Center (AEDC) of the problem of recirculation at the base of ballistic missiles having liquid rocket exhausts. An introduction to the problem is afforded by considering some of the effects of base recirculation on a missile such as the Atlas ICBM. For this flight the missile was equipped with two booster rockets only. The exhaust of the main rockets can be seen plainly. Also the turbine exhaust, indicated by the cloud to the right of the missile, is clearly visible. Because the exhaust gases of the main rockets and of the turbine are fuel-rich, afterburning can occur when these combustible gases are mixed with atmospheric air. Under certain conditions in flight as well as during captive firings, the low pressure ares at the missile base produced by the external flow action may suck some of the air and some of the exhaust gases backward into the base area and into the engine compartment within the skirt of the missile. If the mixture ratio happens to be suitable and if sufficient stay time is permitted within the skirt region, the combustion gases may ignite, and a burning with resulting high temperatures in the skirt area may occur. Destruction of vital engine components such as fuel lines and control lines may result and, in the case of some actual full-scale tests, may have caused damage or even loss of the missile.