ROCKET NOZZLE CONTOUR FOR FLOW SEPARATION CONTROL AND SIDE LOAD REDUCTION

摘要

The present invention relates to the full stream rocket nozzles with longitudinal profile substantially corresponding with parabola. It is reduced to obtain flow separation control and side load, it is proposed that more than 50% expansion rate of nozzle throat or parabolic profile transfer of shapes that farther point starts is (i) and center li is angled stringent cone shape. Ne is between 15 ° and 25 °, (ii) slightly it is bent outwardly, indicate the chamfered shape of the positive second dervative with radius r, or the incurvature that (i i i) is slight, that is, the negative second dervative with r, but it is located at the outside of parabolic profile, in a kind of finally situation, three order derivatives of r are consistently equal to zero (0).