FIELD: aeronautical engineering; designing subsonic flying vehicles.
SUBSTANCE: proposed aircraft has fuselage, wing, tail unit, power plant and functional systems. Aircraft is arranged as single spatial system on base of straight wing at zero sweep by rear spar with single base profile modified in span in such way that root section ensures maximum of magnitudes Mk* and Mzo at moderate magnitudes Cymax; tip section satisfies maximum Cymax and fuselage varying in length of section. Section of forward fuselage as far as zone of attachment of wing is made in form of oval at horizontal located of larger axis; section of rear fuselage after zone of attachment of wing is made in form of circle. Total cross-sectional area changes in length and distribution of areas in length differs from area of body of revolution of minimum distribution by no more than 15%.
EFFECT: increased internal volume of flying vehicle spaces; reduced resistance; enhanced comfort for passengers.
5 dwg
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Authors
Dates
2005-01-20—Published
2003-02-03—Filed