Several Methods for Aerodynamic Reduction of Static-Pressure Sensing Errors for Aircraft at Subsonic, Near-Sonic, and Low Supersonic Speeds

摘要

Tests were conducted in transonic wind tunnels to investigate and verify experimentally methods for aerodynamically reducing errors due to sensor position, bow-wave passage, and angle of attack. The results indicated that aerodynamic devices of simple design may be employed to reduce errors in sensing static pressures to less than 0.5 percent at Mach numbers from about 0.40 to 1.15. (Author)