This work uses computational fluid dynamics to study the flowfield around a hypersonic missile with two lateral jets to provide control in place of control surfaces. The jets exhaust an H2-O2 mixture at Mach number of 2.9 with a jet pressure ratio of roughly 10,500. The jets are staggered axially and circumferentially in such a way to produce pitch and yaw. The flowfield of such a jet configuration is characterized at several angles of attack and the corresponding force coefficients and amplification factors are provided. The freestream air and H2-O2 plume is treated as inert for the majority of the calculations. Special cases are treated with finite rate chemical kinetics and compared to the inert flowfield to ascertain the effects that chemical reactions have on the force coefficients. It was found that the flowfield was only slightly altered from the familiar one jet flowfield when the second jet is active. The flow topology and vortex structures tend to shift towards the second jet but the overall structure remains the same. The normal force amplification factors are close to unity over the range of angle of attack due to the thrust being so high with the two jet configuration having a lower amplification factor compared to firing a single jet. Treating the flowfield as chemically reacting did not affect the force values much: the difference being 0.3% for an angle of attack of 0°.
|Commitee:||Curet, Oscar, Dhanak, Manhar, Gaonkar, Gopal, Su, Tsung-Chow|
|School:||Florida Atlantic University|
|School Location:||United States -- Florida|
|Source:||DAI-B 79/02(E), Dissertation Abstracts International|
|Subjects:||Aerospace engineering, Chemical engineering, Mechanical engineering|
|Keywords:||Chemically reactive, Hypersoinc flow, Lateral jets, Missile aerodynamics, Shock-boundary layer interactions., Thrust & control|
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