Hostname: page-component-84b7d79bbc-c654p Total loading time: 0 Render date: 2024-07-28T21:03:26.096Z Has data issue: false hasContentIssue false
  • English
  • Français

New methodology and code for Hawker 800XP aircraft stability derivatives calculation from geometrical data

Published online by Cambridge University Press:  03 February 2016

N. Anton ,
R. M. Botez  and
D. Popescu
R. M. Botez
Affiliation:
ruxandra@gpa.etsmtl.ca
D. Popescu
Affiliation:
École de technologie supérieure, Laboratory of Research in Active Controls, Aeroservoelasticity and Avionics, Montréal, Canada
Get access Rights & Permissions [Opens in a new window]

Abstract

The new FDerivatives code was conceived and developed for calculating static and dynamic stability derivatives of an aircraft in the subsonic regime, based on its geometrical data. The code is robust and it uses geometries and flight conditions to calculate the aircraft’s stability derivatives. FDerivatives contains new algorithms and methods that have been added to DATCOM’s classical method, presented in a USAF Stability and Control DATCOM reference. The new code was written using MATLAB and has a complex structure which contains a graphical interface to facilitate the work of potential users. Results obtained with the new code were evaluated and validated with flight test data provided by CAE Inc. for the Hawker 800XP business aircraft.

Type
Research Article
Information
The Aeronautical Journal , Volume 114 , Issue 1156 , June 2010 , pp. 367 - 376
Copyright
Copyright © Royal Aeronautical Society 2010 

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

1. The USAF Stability and Control Digital DATCOM – AFFDL–TR–79–3032.Google Scholar
2. http://www.pdas.com/datcom.htm.Google Scholar
3. Blake, W.B. and Etan, D.K., A cambered body method for missile DATCOM, 23rd AIAA Applied Aerodynamics Conference (6-9 June 2005), p 11, Toronto, Ontario, Canada.Google Scholar
4. Williams, J.E. and Vukelich, S.R. The USAF Stability and control digital DATCOM, Volume I. Users Manual, p 317, AFFDL-TR-79-3032, St. Louis, Missouri, USA: McDonnell Douglas Astronautics Company, St. Louis Division, Wright-Patterson Air Force Base, 1979.Google Scholar
5. Williams, J.E. and Vukelich, S.R., The USAF Stability and Control Digital DATCOM, Volume II. Implementation of DATCOM Method, AFFDL-TR-79-3032. 155. St. Louis, Missouri: McDonnell Douglas Astronautics Company, St. Louis Division, Wright-Patterson Air Force Base, 1979.Google Scholar
6. Roskam, J., Methods for Estimating Stability and Control Derivatives for Conventional Subsonic Airplane, Lawrence, Kansas, USA, 1973.Google Scholar
7. Roskam, J., Airplane Flight Dynamics and Automatic Flight Controls, DARcorporation, Lawrence, Kansas, USA, 1995.Google Scholar
8. Roskam, J. and Lan, C.T.E., Airplane Aerodynamics and Performances, DARcorporation, Lawrence, Kansas, USA, 1997.Google Scholar
9. http://www.darcorp.com Google Scholar
10. Champigny, P. and Denis, P., The ONERA aero prediction code “MISSILE”, ONERA–TP–04–112, France, 2004.Google Scholar
11. Popescu, D., Nouvelle implémentation de la procédure DATCOM pour le calcul des coefficients aérodynamiques et des dérivées de stabilité dans le domaine subsonique de vol, Master Thesis, ETS Montréal, 2009.Google Scholar
12. Roskam, J., Airplane design Part VI: Preliminary Calculation of Aerodynamic, Thrust and Power Characteristics, DARcorporation, Lawrence, Kansas, USA, 2000.Google Scholar
13. Sivells, J.C. and Neely, R.H., Method for calculating wing characteristics by lifting-line theory using nonlinear section lift data, NACA–TN–1269, Washington, UK, April 1947.Google Scholar
14. Phillips, W.F. and Alley, N.R., Predicting maximum lift coefficient for twisted wings using lifting-line theory, AIAA J Aircr, May-June 2007, 44, (3).Google Scholar
15. Multhopp, H., Aerodynamics of the fuselage, NACA–TM–1036, Washington, USA, December 1942.Google Scholar
16. Etkin, B. and Reid, L.D., Dynamics of Flight, Stability and Control, 3rd ed, John Wiley & Sons, 1996, 2, p 25.Google Scholar
17. Abbot, I.H. and Von Doenhoff, A.E., Theory of wing sections, Dover Publication, New York, USA, 1959.Google Scholar
18. Nelly, R.H. and Bollech, T.V., Experimental and calculated characteristics of several NACA 44–series wings with aspect ratios of 8, 10, and 12 and taper ratios of 2.5 and 3.5, NACA–TN–1270, Washington, UK, May 1947.Google Scholar
19. Letko, W. and Riley, D.R., Effect of an unswept wing on the contribution of unswept-tail configurations to the low-speed static- and rolling-stability derivatives of a midwing airplane model, NACA TN 2175, Washington, USA, August 1950, pp 25–26.Google Scholar