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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Restricted Bulletin
 Collection: Technical Report Archive and Image Library
An approximate method of shear-lag analysis for beams loaded at right angles to the plane of symmetry of the cross section

An approximate method of shear-lag analysis for beams loaded at right angles to the plane of symmetry of the cross section

Date: September 1, 1943
Creator: Brilmyer, Harold J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A study of the effects of radii of gyration and altitude on aileron effectiveness at high speed

A study of the effects of radii of gyration and altitude on aileron effectiveness at high speed

Date: April 1, 1943
Creator: Fehlner, Leo F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Use of Internal Coolant as a Means of Permitting Increase in Engine Take-Off Power

Use of Internal Coolant as a Means of Permitting Increase in Engine Take-Off Power

Date: January 1, 1944
Creator: Rothrock, Addison M
Description: Engine tests, together with estimates made at Langley Memorial Aeronautical Laboratory, indicate that a 25-percent increase in take-off power can be obtained with present-day aircraft engines without increasing either the knock limit of the fuel or the external cooling requirements of the engine. This increase in power with present fuels and present external cooling is made possible through the use of an internal coolant inducted through the inlet manifold. Estimates on aircraft indicate that this 25-percent increase in power will permit an approximate usable increase of 8.5 percent in the take-off load of existing military airplanes. This increase in load is equivalent to an increase in the weight of gasoline normally carried of between 30 and 65 percent.
Contributing Partner: UNT Libraries Government Documents Department
Calculations of intake-air cooling resulting from water injection and of water recovery from exhaust gas

Calculations of intake-air cooling resulting from water injection and of water recovery from exhaust gas

Date: August 1, 1944
Creator: Rotherock, Addison M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Preliminary tank experiments with a hydrofoil on a planing-tail seaplane hull

Preliminary tank experiments with a hydrofoil on a planing-tail seaplane hull

Date: March 1, 1944
Creator: Wadlin, Kenneth L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Cylinder-head cooling by means of a shield in the exhaust passage

Cylinder-head cooling by means of a shield in the exhaust passage

Date: June 1, 1944
Creator: Mulcahy, B A & Wilsted, H D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Determination from flight tests of thrust coefficients for 10 full-scale airplanes in the gliding condition with engine idling

Determination from flight tests of thrust coefficients for 10 full-scale airplanes in the gliding condition with engine idling

Date: June 1, 1945
Creator: Talmage, Donald B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An automatically variable control linkage and its effect on the lateral-control characteristics of a high-speed fighter airplane

An automatically variable control linkage and its effect on the lateral-control characteristics of a high-speed fighter airplane

Date: May 1, 1944
Creator: Gillis, Clarence L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Some Notes on the Determination of the Stick-Free Neutral Point from Wind-Tunnel Data

Some Notes on the Determination of the Stick-Free Neutral Point from Wind-Tunnel Data

Date: February 1, 1944
Creator: Schuldenfrei, Marvin
Description: Two graphical methods are presented for determining the stick-free neutral point, and they are extensions of the methods commonly used to determine the stick-free neutral point. A mathematical formula for computing the stick-free neutral point is also given. These methods may be applied to determine approximately the increase in tail size necessary to shift the neutral point (stick fixed or free) to any desired location on an airplane having inadequate longitudinal stability.
Contributing Partner: UNT Libraries Government Documents Department
An estimation of the internal-cooling requirements of an aircraft-engine cylinder when using oxygen boost

An estimation of the internal-cooling requirements of an aircraft-engine cylinder when using oxygen boost

Date: November 1, 1944
Creator: Moeckel, W E
Description: None
Contributing Partner: UNT Libraries Government Documents Department