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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Restricted Bulletin
 Collection: Technical Report Archive and Image Library
Theoretical and experimental dynamic loads for a prismatic float having an angle of dead rise of 22-1/2 degrees

Theoretical and experimental dynamic loads for a prismatic float having an angle of dead rise of 22-1/2 degrees

Date: July 1, 1945
Creator: Mayo, Wilbur L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Thermodynamic design of double-panel, air-heated windshields for ice prevention

Thermodynamic design of double-panel, air-heated windshields for ice prevention

Date: June 1, 1943
Creator: Kushnick, Jerome L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The use of geared spring tabs for elevator control

The use of geared spring tabs for elevator control

Date: February 1, 1945
Creator: Phillips, William 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
Use of stagnation temperature in calculating rate of heat transfer in aircraft heat exchangers

Use of stagnation temperature in calculating rate of heat transfer in aircraft heat exchangers

Date: October 1, 1943
Creator: Wood, George P
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Use of variable-ratio geared tabs to improve stick-force characteristics in turning flight

Use of variable-ratio geared tabs to improve stick-force characteristics in turning flight

Date: October 1, 1945
Creator: Kleckner, Harold F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Use of water injection to decrease gasoline consumption in an aircraft engine cruising at high power

Use of water injection to decrease gasoline consumption in an aircraft engine cruising at high power

Date: August 1, 1944
Creator: White, H Jack
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Variation of hydrodynamic impact loads with flight-path angle for a prismatic float at 3 degree trim and with a 22 1/2 degree angle of dead rise

Variation of hydrodynamic impact loads with flight-path angle for a prismatic float at 3 degree trim and with a 22 1/2 degree angle of dead rise

Date: February 1, 1945
Creator: Batterson, Sidney A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Variation of hydrodynamic impact loads with flight-path angle for a prismatic float at 6 degrees and 9 degrees trim and a 22-1/2 degree angle of dead rise

Variation of hydrodynamic impact loads with flight-path angle for a prismatic float at 6 degrees and 9 degrees trim and a 22-1/2 degree angle of dead rise

Date: February 1, 1946
Creator: Stewart, Thelma
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Variation of hydrodynamic impact loads with flight-path angle for a prismatic float at 12 degree trim and with a 22-1/2 degree angle of dead rise

Variation of hydrodynamic impact loads with flight-path angle for a prismatic float at 12 degree trim and with a 22-1/2 degree angle of dead rise

Date: February 1, 1946
Creator: Batterson, Sidney A
Description: None
Contributing Partner: UNT Libraries Government Documents Department