Comments on "Angle of Attack and Sideslip from Pressure Measurements on a Fixed Hemispherical Nose"

AIAA Journal ◽  
1963 ◽  
Vol 1 (3) ◽  
pp. 0725a-0725a
Author(s):  
FREDERICK O. SMETANA
Keyword(s):  
Angle Of Attack ◽  
Pressure Measurements

Steady and Unsteady Surface Pressure Distributions Around Rectangular Prisms With Sharp Edges at Reynolds Number Up to 2.5×106

2006 ◽  
Author(s):  
Annick D’Auteuil ◽  
Guy L. Larose
Keyword(s):  
Reynolds Number ◽  
Turbulent Flow ◽  
Surface Pressure ◽  
Angle Of Attack ◽  
Pressure Measurements ◽  
Oncoming Flow ◽  
Pressure Distributions ◽  
Unsteady Surface Pressure ◽  
Sharp Edges ◽  
Flow Reattachment

The commonly-held assumption that the aerodynamics of rectangular prisms with sharp edges are insensitive to Reynolds number is shown to have limitations. Flow reattachment on the top and/or bottom of the prisms can be related to Reynolds number, Re. Steady and unsteady surface pressure measurements were carried out on nine different rectangular prisms for Re from 0.3×106 to 2.5×106 at several angles of attack, in smooth and turbulent flow. It was observed that the reattachment was dependent on parameters such as fineness ratio, edge treatment, angle of attack, turbulence of the oncoming flow and Reynolds number. Permanent reattachment occurred for prisms with fineness ratio of 4 and fluctuating reattachment took place for rectangular prisms with fineness ratio as low as 2.

scholarly journals Bioinspired wind field estimation—part 1: Angle of attack measurements through surface pressure distribution

2018 ◽  
Vol 10 (3) ◽  
pp. 273-284 ◽  
Author(s):  
Nikola Gavrilovic ◽  
Murat Bronz ◽  
Jean-Marc Moschetta ◽  
Emmanuel Benard
Keyword(s):  
Angle Of Attack ◽  
Time Estimation ◽  
Pressure Measurements ◽  
Surface Pressure Distribution ◽  
Additional Equipment ◽  
Field Estimation ◽  
Aerial Vehicle ◽  
Unsteady Interaction ◽  
Wind Vane ◽  
Local Angle

One of the major challenges of Mini-Unmanned Aerial Vehicle flight is the unsteady interaction with turbulent environment while flying in lower levels of atmospheric boundary layer. Following inspiration from nature we expose a new system for angle of attack estimation based on pressure measurements on the wing. Such an equipment can be used for real-time estimation of the angle of attack during flight or even further building of wind velocity vector with additional equipment. Those information can find purpose in control and stabilization of the aircraft due to inequalities seen by the wing or even for various soaring strategies that rely on active control for energy extraction. In that purpose, flying wing aircraft has been used with totally four span-wise locations for local angle of attack estimation. In-flight angle of attack estimation from differential pressure measurements on the wing has been compared with magnetic sensor with wind vane. The results have shown that pressure ports give more reliable estimation of angle of attack when compared to values given by wind vane attached to a specially designed air-boom. Difference in local angle of attack at four span-wise locations has confirmed spatial variation of turbulence in low altitude flight. Moreover, theoretical law of energy dissipation for wind components described by Kaimal spectrum has shown acceptable match with estimated ones.

Horizontal tail local angle-of-attack and total pressure measurements through static pressure ports and Kiel pitot

2019 ◽  
Vol 123 (1268) ◽  
pp. 1476-1491
Author(s):  
R. M. Granzoto ◽  
L. A. Algodoal ◽  
G. J. Zambrano ◽  
G. G. Becker
Keyword(s):  
Total Pressure ◽  
Static Pressure ◽  
Dynamic Pressure ◽  
Angle Of Attack ◽  
Flight Test ◽  
Vertical Position ◽  
Local Dynamic ◽  
Pressure Measurements ◽  
Turbofan Engines ◽  
Local Angle

ABSTRACTAircraft handling qualities may be influenced by wing-tip flow separations and horizontal tail (HT) reduced efficiency caused by loss of local dynamic pressure or local tailplane flow separations in high angle-of-attack manoeuvres. From the flight tester’s perspective, provided that the test aircraft presents sufficient longitudinal control authority to overcome an uncommanded nose-up motion, this characteristic should not be a safety factor. Monitoring and measuring the local airflow in the aircraft’s HT provides information for safe flight-test envelope expansion and data for early aerodynamic knowledge and model validation. This work presents the development, installation and pre-flight calibration using computational fluid dynamics (CFD), flight-test calibration, results and benefits of differential pressure based local angle-of-attack and total pressure measurements through 20 static pressure ports and a Kiel pitot. These sensors were installed in a single-aisle, four-abreast, full fly-by-wire medium-range jet airliner with twin turbofan engines and conventional HT (low vertical position).

Pressure measurements over a hemisphere-cylinder body attached with a forward facing spike

2013 ◽  
Vol 117 (1192) ◽  
pp. 639-646 ◽  
Author(s):  
R. Kalimuthu ◽  
R. C. Mehta ◽  
E. Rathakrishnan
Keyword(s):  
Shock Wave ◽  
Aerodynamic Drag ◽  
Pressure Coefficient ◽  
Angle Of Attack ◽  
Maximum Pressure ◽  
Geometrical Parameters ◽  
Pressure Measurements ◽  
Separation Region ◽  
Pressure Distributions ◽  
Oil Flow

AbstractThe present paper presents oil flow visualisations and pressure measurements over a hemisphere-cylinder body attached with a forward facing spike at Mach 6 and Reynolds number of 1·38 × 108at 0° and 5° angle-of-attack. The oil flow pictures depict the separation region in the vicinity of the spike on the hemisphere-cylinder body. The oil flow visualisations will help to locate the reattachment shock wave on the hemisphere-cylinder body and also understand the flow field behavior on the blunt-nosed spike configuration. The pressure measurements over the hemisphere-cylinder body depend on the shape and the length of the spike. The pressure distributions over the blunt-nosed body show significant influence of the angle-of-attack. The maximum pressure coefficient on the hemisphere-cylinder body is a function of the spike length, shape of the aerodisk and angle-of-attack. The windward and leeward sides pressure variations show dependence of the geometrical parameters of the spike and shape of the spike. The hemisphere and the flat-faced aerodisk cause considerable reduction of pressure leading to decrease of aerodynamic drag compared to the conical spike.

Experimental pressure evaluation near a sail leading edge under real conditions

1994 ◽  
Vol 98 (978) ◽  
pp. 319-322
Author(s):  
G. Lombardi ◽  
A. Tonelli
Keyword(s):  
Present Note ◽  
Angle Of Attack ◽  
Leading Edge ◽  
Pressure Measurements ◽  
Edge Zone ◽  
Experimental Pressure ◽  
Aerodynamic Condition ◽  
The Ideal

AbstractThe aerodynamic condition corresponding to the optimum sail trim has been long debated; in the present note this aerodynamic aspect of the sails is studied by means of pressure measurements near the sail leading-edge. By analysing the pressure acting on the leading edge zone it can be evidenced that, when the sail is “optimally” trimmed, it is actually in the aerodynamic condition corresponding to the ideal angle of attack.

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