In the aerodynamic design of vehicles for supersonic flight it is essential that the limits of the important aerodynamic variables lift, drag, moment and centre of pressure as functions of the design parameters be known. Frequently an ‘in the large’ analysis of this nature may be initiated using the most elementary considerations with the proper choice of the independent parameters and the proper representation of the aerodynamic variables. The main consideration in this paper is the representation of lift for a fairly general family of wing‐body configurations in a stationary linearized supersonic flow. Further generalization to other wing plan forms and body shapes and the representation of other aerodynamic variables will be evident but not considered in detail.
(1950), "The I.Ae.S. Annual Summer Meeting: Official summaries of the papers read during the sessions held on July 12 and 13 in the Institute's new Western Headquarters Building, 7660 Beverley Boulevard, Los Angeles", Aircraft Engineering and Aerospace Technology, Vol. 22 No. 8, pp. 244-245. https://doi.org/10.1108/eb031936Download as .RIS
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