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absolute coefficient aerodynamic airfoil analysis angle of attack appendix axis characteristics Chief chord Cleveland coefficient due considered constant constant-chord flaps control surfaces control-surface characteristics CORNER cosh derivative determined Director discussed Drag due to flap edge effect equation example Field figure finite thickness flap deflection flight Force full-triangular-tip flap given gives hinge line hinge moment hinge-moment coefficient inner Mach cone integration interest John Langley Aeronautical Laboratory leading leading edge lift limits linearized theory Mach cone Mach lines Mach number maximum method NACA normal outboard flap outer Mach cone parallel Pitch points position pressure distributions problem range of applicability reference region Research rolling rolling-moment shown in figure simple Standard SUPERSONIC FLOW Supersonic Speeds SYMBOLS tables Theoretical triangular wings triangular-tip flaps types of control United various velocity Vice President
Page 1 - The first type, the constantchord partial-span flap, was considered to extend either outboard from the center of the wing or inboard from the wing tip. The second type, the full-triangular-tip flap, was treated only for the case in which the Mach number component normal to the leading edge is supersonic. For each type, expressions were found for the lift, rolling-moment, pitching-moment, and hingemoment characteristics.