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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Advanced Confidential Report
 Collection: National Advisory Committee for Aeronautics Collection
Effect of the lift coefficient on propeller flutter

Effect of the lift coefficient on propeller flutter

Date: July 1, 1945
Creator: Regier, Arthur A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An additional investigation of the high-speed lateral-control characteristics of spoilers

An additional investigation of the high-speed lateral-control characteristics of spoilers

Date: June 1, 1945
Creator: Summers, James
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Completed Tabulation in the United States of Tests of 24 Airfoils at High Mach Numbers (Derived from Interrupted Work at Guidonia, Italy in the 1.31- by 1.74-Foot High-Speed Tunnel)

Completed Tabulation in the United States of Tests of 24 Airfoils at High Mach Numbers (Derived from Interrupted Work at Guidonia, Italy in the 1.31- by 1.74-Foot High-Speed Tunnel)

Date: June 1, 1945
Creator: Ferri, Antonio
Description: Two-dimensional data were obtained in Mach range of from 0.40 to 0.94 and Reynolds Number range of (3.4 - 4.2) X 10 Degrees. Results indicate that thickness ratio is dominating shape parameter at high Mach numbers and that aerodynamic advantages are attainable by using thinnest possible sections. Effects of jet boundaries, Reynolds Number, and Data presented are free from jet-boundary and humidity effects.
Contributing Partner: UNT Libraries Government Documents Department
The Effect of Inlet Pressure and Temperature on the Efficiency of a Single Stage Impulse Turbine Having an 11.0-Inch Pitch-Line Diameter Wheel

The Effect of Inlet Pressure and Temperature on the Efficiency of a Single Stage Impulse Turbine Having an 11.0-Inch Pitch-Line Diameter Wheel

Date: June 1, 1945
Creator: Gabriel, David S.; Carmen, Robert L. & Trautwein, Elmer E
Description: Efficiency tests have been conducted on a single-stage impulse engine having an 11-inch pitch-line diameter wheel with inserted buckets and a fabricated nozzle diaphragm. The tests were made to determine the effect of inlet pressure, Inlet temperature, speed, and pressure ratio on the turbine efficiency. An analysis is presented that relates the effect of inlet pressure and temperature to the Reynolds number of the flow. The agreement between the analysis and the experimental data indicates that the changes in turbine efficiency with Inlet pressure and temperature may be principally a Reynolds number effect.
Contributing Partner: UNT Libraries Government Documents Department
Effects on low-speed spray characteristics of various modifications to a powered model of the Boeing XPBB-1 flying boat

Effects on low-speed spray characteristics of various modifications to a powered model of the Boeing XPBB-1 flying boat

Date: June 1, 1945
Creator: Mas, Newton A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Performance of compressor-turbine jet-propulsion systems

Performance of compressor-turbine jet-propulsion systems

Date: June 1, 1945
Creator: Palmer, Carl B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A correlation of the effects of compression ratio and inlet-air temperature on the knock limits of aviation fuels in a CFR engine I

A correlation of the effects of compression ratio and inlet-air temperature on the knock limits of aviation fuels in a CFR engine I

Date: May 1, 1945
Creator: Branstetter, J Robert
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flight investigation of the variation of drag coefficient with Mach number for the Bell P-39N-1 airplane

Flight investigation of the variation of drag coefficient with Mach number for the Bell P-39N-1 airplane

Date: May 1, 1945
Creator: Clousing, Lawrence A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flight tests of dive-recovery flaps on an XP-51 airplane

Flight tests of dive-recovery flaps on an XP-51 airplane

Date: May 1, 1945
Creator: Williams, Walter G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Preliminary Investigation of Supersonic Diffusers

Preliminary Investigation of Supersonic Diffusers

Date: May 1, 1945
Creator: Kantrowitz, Arthur & Donaldson, Coleman Dup
Description: None
Contributing Partner: UNT Libraries Government Documents Department