<p>Sonic boom plays a key role in aerodynamic/aero-acoustic design of supersonic commercial aircraft. Development of sonic boom wind tunnel test techniques would aid the validation of sonic boom design and deepen the knowledge of near-field sonic boom pressure distributions. Aiming at supersonic wind tunnel sonic boom test, a near-field sonic boom pressure measurement system based on multi-point pressure measurement rail is designed, which is suitable for the intermittent wind tunnel. Moreover, high-accuracy spatial off-body pressure measurement techniques and test data processing methods are proposed. Wind tunnel test for SEEB-ALR sonic boom standard model at operating condition of Mach 1.5 is first performed, which verifies the effectiveness and reliability of the current pressure measurement technique, and provides significant technique support for the sonic boom wind tunnel tests of supersonic commercial aircraft. Based on the validated sonic boom test techniques, near-field sonic boom characteristics of a typical boom supersonic commercial aircraft model and a low-boom optimized aircraft model at Mach number of 2.0 are investigated, which confirms the correctness of the low-boom design.</p>