Study on Aircraft Lift Estimation

Yong Feng Shang

doi:10.4028/www.scientific.net/AMR.785-786.1185

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HomeAdvanced Materials ResearchAdvanced Materials Research Vols. 785-786Study on Aircraft Lift Estimation

Study on Aircraft Lift Estimation

Abstract:

This chapter describes how lift can be derived from a known aircraft geometry and conversely, how the selection of aircraft layout influences the generation of lift. As the fuselage shape is predetermined by the payload requirements, the nacelle geometry by the engine size, and the tail surfaces by stability considerations, the wing parameters are the principal variables to be considered in respect to lift aspects. To this end, guidance is given on the selection of wing section profile and platform geometry to provide specified performance requirements. A lift estimation method covering all the aircraft components is also provided. Such methods are suitable for use in the conceptual design phase and provide an introduction to more detailed estimation procedures.

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Periodical:

Advanced Materials Research (Volumes 785-786)

Pages:

1185-1188

DOI:

https://doi.org/10.4028/www.scientific.net/AMR.785-786.1185

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Online since:

September 2013

Authors:

Yong Feng Shang*

Keywords:

Aircraft, Design, Estimation, Lift, Nacelle Shape

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References

[1] VERHCEN N G. An experimental investigation of the vortex flow over the delta and double-delta wing at low speed[R]. Report LR-372, (1983).

Google Scholar

[2] HUMMELD, OELKERHC. Low—speed characteristics for the wing—canard configuration of the international vertex flow experiment[J].J. Aircraft, 1994, 31(4): 868-878.

DOI: 10.2514/3.46573

Google Scholar

[3] Haines P A, Luers J K. Aerodynamic penalties of heavy rain on landing airplanes[J]. Journal of Aircraft, 1983, 20(2): 111-119.

DOI: 10.2514/3.44839

Google Scholar

[4] Brumby R E. Wing surface roughness cause and effect [J]. DC Flight Approach, 1979(32): 2-7.

Google Scholar

[5] Haines P A, Luers J K. Heavy rain penalties for flight simulators[R]. AIAA-1982-0213, (1982).

DOI: 10.2514/6.1982-213

Google Scholar

[6] Youg F L. Experimental investigation of the effects of surface roughness on compressible turbulent boundary layer skin friction and heat transfer[R]. DRL-532, CR-21, (1965).

DOI: 10.21236/ad0621085

Google Scholar