A design method of a nose aerodynamic compensation pitot-static tube is proposed according to the aircraft design requirement for the pitot-static tube to be placed at the head of the aircraft. The aircraft nose position error is obtained by numerical calculation and then an aerodynamic compensation pitot-static tube configuration is given. Numerical calculations are conducted on the pitot-static tube in order to study its aerodynamic compensation characteristics. Calculation results are verified by comparing them with experimental data. Compensation curves of the pitot-static tube and the best static pressure port location in the compensation region are obtained. On this basis, the compatibility of the compensation pitot-static tube with the aircraft nose is analyzed so as to determine the length of the pitot-static tube. Finally, an integrated calculation of the compensation pitot-static tube and the aircraft nose is presented. The results show that the pitot-static tube is able to provide the desired compensation for aircraft nose position error. Research results of this paper can validate the feasibility of the design approach and method, and the aerodynamic compensation pitot-static tube of this design can satisfy the design requirement. These findings can provide references for aircraft nose aerodynamic compensation pitot-static tube design.
ZHENG Liu, CHEN Zhimin
. Design of an Aircraft Nose Aerodynamic Compensation Pitot-static Tube[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2011
, 32(7)
: 1189
-1194
.
DOI: CNKI:11-1929/V.20110225.1654.000
[1] Garcy W. Measurement of aircraft speed and altitude. NASA Reference Publication 1046, 1980.
[2] Letko W. Investigation of the fuselage interference on a pitot-static tube extending forward from the nose of the fuselage. NACA-TN-1496, 1947.
[3] White F M. Viscous fluid flow[M]. New York: McGraw-Hill, 1991: 500-562.
[4] Schreier S. Compressible flow[M]. New York: Wiley, 1982: 133-200.
[5] Ames Research Staff. Equations, tables, and charts for compressible flow. NACA Report 1135, 1953.
[6] Ritchie 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.
[7] Lao S, Bao Y. Computation of transonic aerodynamically compensating pitot tube[J]. Journal of Aircraft, 1988, 25(6): 544-547.
[8] Swafford T W, Bomba J, Daiber M P. Computational evaluation of compensated pitot-static probes using the Euler equations. AIAA-1995-1839, 1995.
[9] 武文康, 屠兴. 气动补偿空速管的研究与发展[J]. 气动试验与测量控制, 1993, 7(4): 11-16. Wu Wenkang, Tu Xing. The research and development of the aerodynamic compensated pitot-static tube[J]. Aerodynamic Experiment and Measurement & Control, 1993, 7(4): 11-16. (in Chinese)
[10] 汤黄华. 机头空速管位置误差值的计算[J]. 洪都科技, 1991(4): 1-11. Tang Huanghua. Calculation of nose pitot tube position error[J]. Hongdu Science and Technology, 1991(4): 1-11. (in Chinese)
[11] 汤黄华. 补偿空速管与飞机的匹配性设计[J]. 洪都科技, 1998(4): 16-23. Tang Huanghua. Compatibility design of pitot tube compensating with aircraft[J]. Hongdu Science and Technology, 1998(4): 16-23. (in Chinese)
[12] Latif A, Masud J, Sheikh S R, et al. Robust design of an aerodynamic compensation pitot-static tube for supersonic aircraft[J]. Journal of Aircraft, 2007, 44(1): 163-169.
[13] Masud J, Qazi O A, Sheikh S R, et al. Adjustment of aerodynamic compensation characteristics of a pitot tube by rear-body shape manipulation. AIAA-2008-254, 2008.
[14] Masud J, Afgan I. Performance characteristics of flush angle-of-attack measurement system integrated on a pitot tube. AIAA-2009-1077, 2009.
[15] Shih T H, Liou W W, Shabbir A, et al. A new k-ε eddy viscosity model for high Reynolds number turbulent flows[J]. Comput Fluids, 1995, 24(3): 227-238.
[16] MIL-P-26292C(3)NOT 2, Pitot and static pressure systems, installation and inspection of (no s/s document)[S]. 1998.
CJA