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  Partner: UNT Libraries Government Documents Department
 Year: 1944
 Serial/Series Title: NACA Restricted Bulletin
 Collection: Technical Report Archive and Image Library
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
Relative effects of cylinder-head and inlet-mixture temperatures upon knock limits of fuels

Relative effects of cylinder-head and inlet-mixture temperatures upon knock limits of fuels

Date: October 1, 1944
Creator: Hensley, Reece V
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Some effects of propeller operation on the distribution of the load on the vertical tail surface of a typical pursuit airplane

Some effects of propeller operation on the distribution of the load on the vertical tail surface of a typical pursuit airplane

Date: March 1, 1944
Creator: Dingeldein, Richard C
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
Some strength tests of stiffened curved sheets loaded in shear

Some strength tests of stiffened curved sheets loaded in shear

Date: April 1, 1944
Creator: Chiarito, Patrick T
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Spinning of large airplanes

Spinning of large airplanes

Date: October 1, 1944
Creator: Seidman, Oscar
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tests of 10 inch 24S-T aluminum-alloy shear panels with 1-1/2 inch holes II : panels having holes with notched edges

Tests of 10 inch 24S-T aluminum-alloy shear panels with 1-1/2 inch holes II : panels having holes with notched edges

Date: April 1, 1944
Creator: Levin, L Ross
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tests of beams having webs with large circular lightening holes

Tests of beams having webs with large circular lightening holes

Date: February 1, 1944
Creator: Levin, L Ross
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tests of hydraulically expanded rivets

Tests of hydraulically expanded rivets

Date: March 1, 1944
Creator: Schuette, Evan H
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