MIL-S-i252D
(Note: When an airfoil section other than a NACA section is used, the airfoil section shall be compared with the most nearly equivalent NACA uction, or data similar to that available for NACA sections shall be presented.)
Incidence, normal |
---- |
Sweep of leading edge, degrees |
---- |
Dihedral, degrees |
---- |
Adjustment each side of neutral... |
---- |
Aspects ratio |
---- |
Vertical:
Airfoil section designation and thickness ......----
(Note: When an airfoil section other than a NACA section iS used, the· airfoil section shall be compared with the most nearly equivalent NACA aeetions, or data similar to that available for N,\CA sections shall be presented.)
Sweep of leading edge, degrees ---- Aspect ratio ---- Tab dimensions ---- Tab location ---- The amount of the aerodynamic and static
balance shall be specified, in percent, and
the coefficient of dynamic balance given .....----
Height over highest fixed part of aircraft (wing,
tail, or propeller disk) :
Reference line level (reference is to ----
Wings not folded ---- Wings folded --'---
Maximum during folding operation ----
Three-point, · or on beaching gear, or handling truck:
Wings not folded ---
Wings folded --- Maximum during folding operation ----
Height over highest part of tail, reference line level ----
Height in hoisting attitude, from top of hoisting sling to lowest part of aircraft (wheels in lowD est position for landplanes. .and .amphibians ;
on beach handling gear where used) ----
Length, maximum:
Reference line level ---- Three point, or on beach handling gear or
truck, propeller stationary, lower blade ver-
tical -.----
Length from hoisting sling to farthest aft part of tail, reference line level, rudder neutral, ele- vator down ----
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