Numerical analysis of aerodynamic compensation pitot-static tube

Author:

Žunić Tanja,Dovatov Biljana,Nenadić Ilija

Abstract

Numerical analysis of a flow filed around the aerodynamic compensation pitot-static tube that is used on a domestic ORAO J22 aircraft is presented in this paper. The analysis was performed for three different Mach numbers of the free stream velocity for two configurations of the pitot-static tube. The comparison of the pressure coefficient (Cp) distribution for both of the configurations is given.

Publisher

Centre for Evaluation in Education and Science (CEON/CEES)

Reference8 articles.

1. GARCY,W.: Measurement of aircraft speed, NASA Reference Publication 1046, 1980;

2. RICHIE,V.S.: Several methods for aerodynamic reduction of static pressure sensing errors for aircraft at subsonic, near-sonic, and low supersonic speeds, NASA TR R-18, 1959;

3. LETKO,W.: Investigation of the fuselage interference on a pitot-static tube extending forward from the nose of the fuselage, NASA-TN-1496, 1947;

4. O'BRYAN,T.C., DANFORTH,E.C.B., JOHNSTON,J.F.: Error in airspeed measurement due to the static-pressure field ahead of an airplane at transonic speeds, National Advisory Committee for Aeronautics R-1239, 1955;

5. LATIF,A., MASUD,J., SHEIKIH,S.R., PERVEZ,K., QAZI,O.A., QURESHI,H.: Novel aerodynamic compensation pitot-static tube for application in subsonic and supersonic flight regimes, 44th AIAA Aerospace Sciences Meeting and Exhibit, 2006;

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