Design and Development
The 1-29 was constructed using a modified SGS 1-23G fuselage. New wings were built for the aircraft to determine if better laminar flow could be achieved on a metal wing.
The wings were all-metal and of constant chord. The wing ribs were identical and created from a single master die to ensure uniformity. The wing features a thick, deep spar to reduce wing flexing and "oil-canning" that might interrupt laminar flow. The wing was assembled using flush rivets and has balanced top and bottom dive brakes.
The aircraft first flew in 1958 and flight testing was reported by Schweizer Aircraft as on-going though 1959.
The 1-29 program did yield positive results. The standard production model SGS 1-23H-15 with the same fuselage and wingspan as the 1-29 and a NACA 43012A airfoil, produced a best glide ratio of 29:1. With its laminar flow wing and NACA 63-618 airfoil the 1-29 recorded a 34:1 glide ratio, an improvement of 15%.
The 1-29 design was never certified and the sole aircraft that was built is an experimental aircraft in the "racing, exhibition" class and registered as N3898A.
Read more about this topic: Schweizer SGS 1-29
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