1, and the theory is easily

These derivatives will be defined in the context of their role as constant coefficients in There are several purposes for a rudder on an aircraft. Reports and Memoranda No. For a defined "trim" flight condition, changes and oscillations occur in these parameters. computes all stability and control derivatives needed to run several other dynamic response computer programs that compute equations of motion, transfer functions and perform dynamic simulation. To run the modeling software: To use this software run under MATLAB the script called RunFirst.m. Abstract: -In this study, the longitudinal stability derivatives of a transport aircraft have been calculated by modeling the aircraft configuration and flight condition. Inputs for the program are body geometry thickness ratio, acceleration constant, and pitch axis location.

(7) can be rewritten in the convenient form: (10) Rudder Considerations What is a rudder for? 2), wing, and canard parameters (Fig. The principle images of the graphical interface are shown for the main window (Fig.

dynamic stability derivatives applicable to the calculation of the longitudinal static and dynamic stability and control and trimmed flight characteristics of an elastic airplane. for the lateral stability derivatives at subsonic speeds of slender wings, of various planforms, span- length ratios, etc. tudinal stability and control derivatives were adequately determined by the flight test procedure and the MSR analysis method discussed herein. A quick tour of the existing literature reveals that good approx- imations exist for longitudinal modes. The static stability derivatives were then expressed in terms of the perturbation velocities u and w by the approximate rela- tions AV =: u and U0Aa =: w. The change of variables was desirable inasmuch as the values of the stability derivatives for hovering (where CY is undefined) and for forward flight then become directly comparable. Interactive graphs/plots help visualize and better understand the functions. XFLR5 XFLR5 is an analysis tool for airfoils, wings and planes Brought to you by: techwinder Equations of motion are used to analyze these changes and oscillations. do not provide an insight into the participation of and the role played by different parameters (stability derivatives) in dynamics. This is attained by determining if the control authority available for trim is sufficient and if the static stability char-acteristics are adequate. These usually drive the sizing of the rudder. 2 9 2 2" February, 19 5 3 Summary.--A method of calculating stability derivatives for wings osciUating at low frequencies is developed from For the stability derivatives of the blunt cone in hypersonic flow with Mach number 6.85, the numerical results show that when the angle of attack is not very large, both static and dynamic stability derivatives can be predicted in reasonable accuracy which is usually higher than the embedded Newtonian theory. The theoretical calculation of the derivatives has already been given for delta wings with attached flow ~, independent of Mach number, in Ref.