Static Response of a Hemispherical-Headed Yawmeter at High Subsonic and Transonic Speeds
نویسنده
چکیده
SUMMARY Details are given of the static calibration of a hemispherrcal-headed drfferentral pressure yawmeter, 0.6 to 1.2; rn the Mach number range from the xnstrument has a central pitot pressure hole and two pairs of holes m perpendroular planes for flow directron measurement. The results show that ths sensitivity to yaw (for angles up to 8') as determined from pressure differences between opposing holes, varres smoothly with Mach number at transonlc speeds; the sensitivity is little affected by a cross-flos normal to the line jouung the holes. LIST OF CONTEXTS 1 Introduction 2 Details of yawmeter and test equipment 2.1 Yawmeter 2.2 Wind tunnel and installation of yawmeter z Details of tests Methods of analysas 5 Results and discussion 5.1 Pitot pressure 5.2 Yawmeter sensitivity and zero error 5.3 Individual hole pressures and sensitivities 5.4 Effect of a change in &ape of the support 6 Conclusions hst of symbols References LIST OF ILLUSTRATIONS Yawmeter (including faults) Arrangement of yawmeter in tunnel (plan view) Variation of pressure at patot hole with yaw at various Mach numbers Variation of pressure difference with yaw at various Each numbers for the holes B and D in the yawing plane Variation with Mach number of rate of change of ratio of pressure difference to free stream stagnation preesurs with component of yaw m hole plane Variation with Mach number of rate of change of ratio of pressure difference to free etrnam dynamic pressure wrth component of yaw in hole plane Variation with Mach number of rate of change of ratio of pressure difference to free stream static pressure with component of yaw,in hole plane Zero errors for the two pairs of holes Variation of pressure with yaw, for hole B on positive yaw side of head Variation of pressure with yaw, for hole D on negative yaw side of head Variation of pressure with yaw, for hole B on negative yaw side of head Variation of pressure with yaw, for hole D on positive yaw side of head Variation with Mach number of rate of change with component of yaw in hole plane of pressure coefficient at individual yawmeter holes Results of probe traverses. Variation of ratio of static and stagnation pressures with position along a line 4.35 inches from the yawmeter axis Effect of falring on pressures for holes in plane perpendicular to yawing plane Effect of fairlng on pressures for hole in yawing …
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