Pressure Measurements Around a Rotating Cylinder With and Without Crossflow

1993 ◽  
Vol 115 (3) ◽  
pp. 526-528 ◽  
Author(s):  
A. A. Tawfek ◽  
B. V. S. S. S. Prasad ◽  
A. K. Mohanty
Keyword(s):  
Pressure Transducer ◽  
Static Pressure ◽  
Rotating Cylinder ◽  
Differential Pressure ◽  
Pressure Measurements ◽  
Orthogonal Axis ◽  
Differential Pressure Transducer ◽  
Slip Ring

Static pressure measurements around a cylinder rotating about an orthogonal axis with and without superimposed crossflow are carried out by using a capacitance type differential pressure transducer in conjunction with a slip-ring apparatus. A coefficient of pressure (Cp) is defined for the rotating cylinder and typical variations of Cp along its length and periphery are presented.

scholarly journals Correction of static pressure on a research aircraft in accelerated flight using differential pressure measurements

2012 ◽  
Vol 5 (3) ◽  
pp. 3611-3643 ◽  
Author(s):  
A. R. Rodi ◽  
D. C. Leon
Keyword(s):  
Pressure Measurement ◽  
Static Pressure ◽  
Satellite System ◽  
Differential Pressure ◽  
Limiting Factors ◽  
Measurement Unit ◽  
Pressure Measurements ◽  
Factors Affecting ◽  
Wide Range ◽  
Research Aircraft

Abstract. Geometric altitude data from a combined Global Navigation Satellite System (GNSS) and inertial measurement unit (IMU) system on the University of Wyoming King Air research aircraft are used to estimate acceleration effects on static pressure measurement. Using data collected during periods of accelerated flight, comparison of measured pressure with that derived from GNSS/IMU geometric altitude show that errors exceeding 150 Pa can occur which is significant in airspeed and atmospheric air motion determination. A method is developed to predict static pressure errors from analysis of differential pressure measurements from a Rosemount model 858 differential pressure air velocity probe. The method was evaluated with a carefully designed probe towed on connecting tubing behind the aircraft – a "trailing cone" – in steady flight, and shown to have a precision of about ±10 Pa over a wide range of conditions including various altitudes, power settings, and gear and flap extensions. Under accelerated flight conditions, compared to the GNSS/IMU data, this algorithm predicts corrections to a precision of better than ±20 Pa. Some limiting factors affecting the precision of static pressure measurement on a research aircraft are examined.

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