Development and validation of an enhanced semi-empirical method for estimation of aerodynamic characteristics of light,propeller-driven airplanes

Abstract

This study is intended to introduce an enhanced semi-empirical method for estimation of longitudinal and lateral-directional stability and control derivatives in the preliminary design phase of light airplanes. Specialised for light, single or twin propeller-driven airplanes, available state-of-the-art analytical procedures and design data compendia are combined and modified in a unique compatible method, and automated in NAMAYEH software. In the present study, modified procedures and the software structure are presented. Afterwards, the proposed method is applied to a four-place, low wing, single-engine, propeller-driven general aviation airplane. In order to validate the proposed method, the estimated aerodynamic characteristics are compared with the wind tunnel test data as well as DATCOM and VLM-based method estimations. The results indicate that the proposed method is able to predict the aerodynamic characteristics in an acceptable range of accuracy from zero-lift to stall conditions in all configurations.

Keywords

Semi-empirical methods propeller-driven airplanes preliminary design phase stability and control derivatives aerodynamic characteristics

Get full access to this article

View all access options for this article.

References

Chudoba B. Stability and control of conventional and unconventional aircraft configurations: A generic approach. BoD–Books on Demand, 2001.

Blake WB. Prediction of fighter aircraft dynamic derivatives using Digital Datcom. In: AlAA 3rd applied aerodynamics conference, Colorado Springs, CO, 14–16 October 1985, paper no. AIAA-85-407.

Kay J, Mason WH, Durham W, et al. Control authority issues in aircraft conceptual design: Critical conditions, estimation methodology, spreadsheet assessment, trim and bibliography. Report, Virginia Polytechnic Institute and State University, USA, 1993.

Razgonyaev V and Mason WH. An evaluation of aerodynamic prediction methods applied to the XB-70 for use in high speed aircraft stability and control system design. In: 33rd aerospace sciences meeting & exhibit, Reno, NV, USA, 9–12 January 1995, paper no. AlAA 95-0759.

Wagner T and Valasek J. Comparison of computational methods for stability and control analysis. In: 43rd AIAA aerospace sciences meeting and exhibit, Reno, NV, USA, 10–13 January 2005, paper no. AIAA 2005-140.

Ghoreyshi M, Badcock KJ and Woodgate M. Integration of multi-fidelity methods for generating an aerodynamic model for flight simulation. In: 46th AIAA aerospace sciences meeting and exhibit, Reno, NV, USA, 7–10 January 2008, paper no. AIAA 2008-197.

Shafer TC, Lynch CE, Viken SA, et al. Comparison of computational approaches for rapid aerodynamic assessment of small UAVs. In: 52nd aerospace sciences meeting, AIAA SciTech, National Harbor, MD, USA, 13–17 January 2014, paper no. AIAA 2014-0039.

Anton N, Botez RM and Popescu D. New methodologies for aircraft stability derivatives determination from its geometrical data. In: Proceedings of the AIAA atmospheric flight mechanics conference, Chicago, IL, USA, 10–13 August 2009, paper no. AIAA 2009-6046.

Anton

Botez

Popescu

. New methodology and code for Hawker 800XP aircraft stability derivatives calculations from geometrical data. Aeronaut J 2010, pp. 114–114.

10.

Anton

Botez

Popescu

. Stability derivatives for a delta-wing X-31 aircraft validated using wind tunnel test data. Proc IMechE, Part G: J Aerospace Engineering 2011; 225: 403–416.

11.

Kostić

Stefanović

Kostić

. Aerodynamic analysis of a light aircraft at different design stages. FME Trans 2014; 42: 94–105.

12.

Smith MS. Analysis of wind tunnel oscillatory data of the X-31A aircraft. Report, The George Washington University, Joint Institute for Advancement of Flight Sciences, Langley Research Center, USA, 1999.

13.

Da Ronch A, Badcock KJ, McFarlane C, et al. Benchmarking CEASIOM software to predict flight control and flying qualities of the B-747. In: 27th congress of the international council of the aeronautical sciences, Nice, France, September 2010.

14.

Siddiqui

Kassem

Al-Gami

. Using USAF DATCOM to predict nonlinear aerodynamics of structurally impaired aircraft. Int Rev Aerosp Eng 2010; 3.2: 125–133.

15.

Ghoreyshi

Cummings

. From spreadsheets to simulation-based aircraft conceptual design. Appl Phys Res 2014; 21: 64–80.

16.

Gabor OŞ, Koreaschi A, Botez RM, et al. Analysis of the aerodynamic performance of a morphing wing-tip demonstrator using a novel nonlinear vortex lattice method. In: 34th AIAA applied aerodynamics conference, Washington DC, USA, 13–17 June 2016, paper no. AIAA 2016-4036.

17.

Ul Haque

Asrar

Omar

et al.

Comparison of digital DATCOM and wind tunnel data of a winged hybrid airship’s generic model. Appl Mech Mater 2014; 31: 629–629.

18.

Wolowicz CH and Yancey RB. Longitudinal aerodynamic characteristics of light, twin-engine, propeller-driven airplanes. Report, NASA Technical Note, Report no. NASA TN D-6800, June 1972.

19.

Wolowicz CH and Yancey RB. Lateral-directional aerodynamic characteristics of light, twin-engine, propeller driven airplanes. Report, NASA Technical Note, Report no. NASA TN D-6946, October1972.

20.

Hoak DE and Finck RD. The USAF Stability and Control DATCOM. Report, Air Force Wright Aeronautical Laboratories, Report no. TR-83-3048, 1978.

21.

Anon. Light and general aviation aerodynamics, Volumes 1–4. Report, Engineering Sciences Data Unit, London, 1981.