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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Advanced Confidential Report
 Collection: National Advisory Committee for Aeronautics Collection
Flight investigation of boundary-layer and profile-drag characteristics of smooth wing sections of a P-47D airplane

Flight investigation of boundary-layer and profile-drag characteristics of smooth wing sections of a P-47D airplane

Date: October 1, 1945
Creator: Zalovcik, J. A.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Knock-limited power outputs from a CFR engine using internal coolants II : six aliphatic amines

Knock-limited power outputs from a CFR engine using internal coolants II : six aliphatic amines

Date: October 1, 1945
Creator: Evvard, John C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Supersonic-tunnel tests of projectiles in Germany and Italy

Supersonic-tunnel tests of projectiles in Germany and Italy

Date: October 1, 1945
Creator: Ferri, Antonio
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Bibliography and review of information relating to the hydrodynamics of seaplanes

Bibliography and review of information relating to the hydrodynamics of seaplanes

Date: September 1, 1945
Creator: Bidwell, Jerold M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of wing modifications on the longitudinal stability of a tailless all-wing airplane model

Effect of wing modifications on the longitudinal stability of a tailless all-wing airplane model

Date: September 1, 1945
Creator: Ankenbruck, Herman O
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Charts for helicopter-performance estimation

Charts for helicopter-performance estimation

Date: August 1, 1945
Creator: Talkin, Herbert W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A simple method for estimating terminal velocity including effect of compressibility on drag

A simple method for estimating terminal velocity including effect of compressibility on drag

Date: August 1, 1945
Creator: Bielat, Ralph P
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Blade design data for axial-flow fans and compressors

Blade design data for axial-flow fans and compressors

Date: July 1, 1945
Creator: Bogdonoff, Harriet E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The development and application of high-critical-speed nose inlets

The development and application of high-critical-speed nose inlets

Date: July 1, 1945
Creator: Wright, John B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of leakage past aileron nose on aerodynamic characteristics of plain and internally balanced ailerons on NACA 66(215)-216, a = 1.0 airfoil

Effect of leakage past aileron nose on aerodynamic characteristics of plain and internally balanced ailerons on NACA 66(215)-216, a = 1.0 airfoil

Date: July 1, 1945
Creator: Bird, J D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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 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
Comparison of Pitching Moments Produced by Plain Flaps and by Spoilers and Some Aerodynamic Characteristics of an NACA 23012 Airfoil with Various Types of Aileron

Comparison of Pitching Moments Produced by Plain Flaps and by Spoilers and Some Aerodynamic Characteristics of an NACA 23012 Airfoil with Various Types of Aileron

Date: April 1, 1945
Creator: Purser, Paul E. & Mckinney, Elizabeth G.
Description: Sectional characteristics of airfoil having retractable slotted flap with plain, slot-lip, or retractable ailerons are presented for a large range of aileron deflections. The analysis indicated that pitching moments produced by spoilers were less positive than those produced by plain flaps of equal effectiveness, also that pitching moments created by the spoiler increased less with the Mach number than similar moments produced by plain flaps. Positive values of pitching moment decreased as devices were located nearer airfoil leading edge.
Contributing Partner: UNT Libraries Government Documents Department
Efficiency tests of a single-stage impulse turbine having an 11.0-inch pitch-line diameter wheel with air as the driving fluid

Efficiency tests of a single-stage impulse turbine having an 11.0-inch pitch-line diameter wheel with air as the driving fluid

Date: April 1, 1945
Creator: Carman, L Robert
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flight investigation of boundary-layer transition and profile drag of an experimental low-drag wing installed on a figher-type airplane

Flight investigation of boundary-layer transition and profile drag of an experimental low-drag wing installed on a figher-type airplane

Date: April 1, 1945
Creator: Zalovcik, J. A. & Skoog, R. B.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flight investigation of boundary-layer transition and profile drag of an experimental low-drag wing installed on a fighter-type airplane

Flight investigation of boundary-layer transition and profile drag of an experimental low-drag wing installed on a fighter-type airplane

Date: April 1, 1945
Creator: Skoog, Richard B
Description: None
Contributing Partner: UNT Libraries Government Documents Department