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 Collection: National Advisory Committee for Aeronautics Collection
Rocket-model investigation to determine the hinge-moment and normal-force properties of a full-span, constant-chord, partially balanced trailing-edge control on a 60 degree clipped delta wing between Mach numbers of 0.50 and 1.26

Rocket-model investigation to determine the hinge-moment and normal-force properties of a full-span, constant-chord, partially balanced trailing-edge control on a 60 degree clipped delta wing between Mach numbers of 0.50 and 1.26

Date: October 30, 1953
Creator: Martz, C William & Goslee, John W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Comper "Streak" single seat airplane (British) : a low-wing cantilever monoplane

The Comper "Streak" single seat airplane (British) : a low-wing cantilever monoplane

Date: July 1, 1934
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An investigation of a thermal ice-prevention system for a C-46 cargo airplane VI : dry-air performance of thermal system at several twin- and single-engine operating conditions at various altitudes

An investigation of a thermal ice-prevention system for a C-46 cargo airplane VI : dry-air performance of thermal system at several twin- and single-engine operating conditions at various altitudes

Date: May 1, 1945
Creator: Kees, Harold L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An investigation of a thermal ice-prevention system for a C-46 cargo airplane V : effect of thermal system on airplane cruise performance

An investigation of a thermal ice-prevention system for a C-46 cargo airplane V : effect of thermal system on airplane cruise performance

Date: January 13, 1945
Creator: Selna, James
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A study of the use of various high-lift devices on the horizontal tail of a canard airplane model as a means of increasing the allowable center-of-gravity travel

A study of the use of various high-lift devices on the horizontal tail of a canard airplane model as a means of increasing the allowable center-of-gravity travel

Date: January 21, 1953
Creator: Johnson, Joseph L , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
On the flow of a compressible fluid by the hodography method I : unification and extension of present-day results

On the flow of a compressible fluid by the hodography method I : unification and extension of present-day results

Date: March 1, 1944
Creator: Kaplan, Carl
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Saunders "Cutty Sark" commercial seaplane (British) : a high-wing monoplane flying boat

The Saunders "Cutty Sark" commercial seaplane (British) : a high-wing monoplane flying boat

Date: November 1, 1929
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation of the effects of spoilers on the characteristics of a low-drag airfoil equipped with a 0.25-chord slotted flap

Wind-tunnel investigation of the effects of spoilers on the characteristics of a low-drag airfoil equipped with a 0.25-chord slotted flap

Date: July 23, 1945
Creator: Holtzclaw, Ralph W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
On a new method for calculating the potential flow past a body of revolution

On a new method for calculating the potential flow past a body of revolution

Date: July 1, 1942
Creator: Kaplan, Carl
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Unsteady Lift of a Finite Wing

The Unsteady Lift of a Finite Wing

Date: January 1, 1939
Creator: Jones, Robert T
Description: Unsteady lift function for wings of finite aspect ratio have been calculated by approximate methods involving corrections of the aerodynamic inertia and of the angle of the infinite wing. The starting lift of the finite wing is found to be only slightly less than that of the infinite wing; whereas the final lift may be considerably less. The calculations indicate that the distribution of lift near the start is similar to the final distribution. Both the indicia and the oscillating lift functions are given. Approximate operational equivalents of the functions have been devised to facilitate the calculation of lift under various conditions of motion.
Contributing Partner: UNT Libraries Government Documents Department