Abstract <p>The study investigates a non-intrusive static surface pressure measurement technique for a Blended Wing Body (BWB) model in low-speed wind tunnel testing using internal pressure channels. This approach eliminates external pressure taps, reducing aerodynamic disturbances and preserving model integrity. Pressure data were obtained using a multi-tube manometer, capturing surface pressure variations across spanwise and chordwise locations. The experimental results were compared with computational fluid dynamics (CFD) simulations, showing good agreement in regions of smooth flow, while minor discrepancies near flow separation zones were attributed to surface imperfections and unsteady effects. The internal pressure channels effectively transmitted pressure data with minimal losses, ensuring reliable measurements. Factors such as tube length, channel diameter, and response time were analyzed for their impact on accuracy, confirming the method’s feasibility for low-speed aerodynamic studies. The findings demonstrate that this technique provides a practical and effective alternative for surface pressure measurement without protrusions, making it suitable for applications where aerodynamic fidelity is critical. Key considerations for optimizing internal channel design and post-processing are discussed to enhance measurement accuracy. This study highlights the potential of internal pressure channels for improving aerodynamic testing methods in low-speed wind tunnel experiments.</p>