tailieunhanh - Aeronautical Engineer Data Book Episode 14

Tham khảo tài liệu 'aeronautical engineer data book episode 14', kỹ thuật - công nghệ, cơ khí - chế tạo máy phục vụ nhu cầu học tập, nghiên cứu và làm việc hiệu quả | LP N Yr L Nr Rolling moment due to roll rate Yawing moment due to roll rate Sideforce due to yaw rate Rolling moment due to yaw rate Yawing moment due to yaw rate i wing contribution i wing contribution i fin contribution i wing contribution ii fin contribution i wing contribution ii fin contribution 1 If . s 2 - s. Jo a d 1 rfr dCD 2 - 2S C y Vpa F 1 fs 2 s y a V - L. . p F b - Lv fin b if snCDycyy2dy Ss J 0 y 77 ỈF _ F -KT lYp b b N fi Roll damping wing effects dominate but fin and tailplane contribute Many contributions but often negligible Yaw damping for large aspect ratio rectangular wing wing contribution is approximately CD 6 251 252 Aeronautical Engineer s Data Book Table Longitudinal aerodynamic control derivatives Small perturbation derivatives referred to aircraft wind axes Derivative Description Expression Comments X Axial force due to elevator - 2 krCLia2 Usually insignificantly small Z Normal force due to elevator - sF a2 S 1 M Pitching moment due to elevator - V 2 Principal measure of pitch control power Appendix 4 Compressible flow tables Table Subsonic flow isentropic flow y 7 5 Notation M Local flow Mach number P Po Ratio of static pressure to total pressure p p Ratio of local flow density to stagnation density T To Ratio of static temperature to total temperature p 1 - M2 Compressibility factor V a Local velocity speed of sound at sonic point q Po Dynamic pressure total pressure A A Local flow area flow area at sonic point M P Po P Po T To p q Po A A V a - .