Abstract:
The reduction of sonic boom noise level is one of the most important problems that must be resolved to get the commercial success in the future. For the sonic boom noise prediction and control of supersonic flight vehicle, the sonic boom noise level prediction methods based on supersonic linear theory and waveform parameter method were developed. The prediction results agreed well with the experiment results of the lm1021, thus the reliability of the prediction methods were validated. The low sonic boom configuration optimizations were researched. The sonic boom level of a basic configuration of supersonic business jet was computed, and the cause of sonic boom formation was analyzed. Based on the results and the analysis, the fuselage and wing planform were optimized separately to decrease the noise level of sonic boom. Compared with the basic configuration, the sonic boom level of optimized configuration decreased distinctively. The overpressure decreased 41%, and the A-weighted noise level decreased 7.55 dB. The aerodynamic characteristics of optimized configuration were computed by computational fluid dynamics(CFD). Compared with the basic configuration, the drag decreased significantly at the cruise condition, while the moment almost unchanged.