Selecting the airplane's general arrangement is a complex issue. This chapter deals with finding the optimum allocation of a given useful load volume inside a generic combination of a fuselage and a wing. Although an all‐wing airplane is often considered the ultimate ideal, it is not necessarily better than the traditional body and wing concept. For instance, a preferred integrated configuration may combine a body and a wing each containing about 50% of the total volume required for payload and fuel. For a very large airliner, such an integrated concept may be superior to the traditional tube and wing.

    Results of an analytical approach are illustrated with a parametric survey for a transport aircraft with 2,000 cubic meter useful volume. This leads to the conclusion that all‐wing aircraft achieve a high lift to drag ratio only under flight conditions that may not be favorable to a practical design. The analysis is applied to several integrated concepts studied by airplane manufacturers and research institutions. Configurations compared are a discrete wing and body, an all‐wing airplane, a blended wing and body, a hybrid flying wing and a very large span loader. The chapter concludes with a discussion of the feasibility of flying wing design.


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    Title :

    From Tube and Wing to Flying Wing


    Contributors:

    Published in:

    Publication date :

    2013-06-21


    Size :

    35 pages




    Type of media :

    Article/Chapter (Book)


    Type of material :

    Electronic Resource


    Language :

    English




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