You limited your search to:

 Serial/Series Title: NACA Advanced Confidential Report
 Collection: Technical Report Archive and Image Library
Wind-tunnel investigation of a high-critical-speed fuselage scoop including the effects of boundary layer

Wind-tunnel investigation of a high-critical-speed fuselage scoop including the effects of boundary layer

Date: February 1, 1945
Creator: Baals, Donald D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The NACA impact basin and water landing tests of a float model at various velocities and weights

The NACA impact basin and water landing tests of a float model at various velocities and weights

Date: August 1, 1944
Creator: Batterson, Sidney A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The knock-limited performance of several miscellaneous fuels blended with a base fuel I

The knock-limited performance of several miscellaneous fuels blended with a base fuel I

Date: July 1, 1944
Creator: Bellman, Donald R
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
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
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
Wind-tunnel tests of a blunt-nose aileron with beveled trailing edge on an NACA 66(215)-216 airfoil with several modifications of aileron nose and adjacent airfoil contour

Wind-tunnel tests of a blunt-nose aileron with beveled trailing edge on an NACA 66(215)-216 airfoil with several modifications of aileron nose and adjacent airfoil contour

Date: February 1, 1945
Creator: Bird, J D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel tests of ailerons at various speeds II : ailerons of 0.20 airfoil chord and true contour with 0.60 aileron-chord sealed internal balance on the NACA 66,2-216 airfoil

Wind-tunnel tests of ailerons at various speeds II : ailerons of 0.20 airfoil chord and true contour with 0.60 aileron-chord sealed internal balance on the NACA 66,2-216 airfoil

Date: June 1, 1943
Creator: Bird, J D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental study of the coating formed on nitrided-steel piston rings during operation in nitrided-steel cylinders

Experimental study of the coating formed on nitrided-steel piston rings during operation in nitrided-steel cylinders

Date: March 1, 1944
Creator: Boegli, Charles 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
Wind-Tunnel Investigation of a Low-Drag Airfoil Section with a Double Slotted Flap

Wind-Tunnel Investigation of a Low-Drag Airfoil Section with a Double Slotted Flap

Date: September 1, 1943
Creator: Bogdonoff, Seymour M.
Description: Tests were made of an 0.309-chord double-slotted flap on an NACA 65, 3-118, a equals 1.0 airfoil section to determine drag, lift, and pitching-moment characteristics for a range of flap deflections. Results indicate that combination of a low-drag airfoil and a double-slotted flap, of which the two parts moved as a single unit, gave higher maximum lift coefficients than have been obtained with plain, split, or slotted flaps on low-drag airfoils. Pitching moments were comparable to those obtained with other high-lift devices on conventional airfoils for similar lift coefficients.
Contributing Partner: UNT Libraries Government Documents Department
Occurrence of iron oxides on cast-iron engine surfaces after operation

Occurrence of iron oxides on cast-iron engine surfaces after operation

Date: February 1, 1946
Creator: Borckway, L O
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The determination of span load distribution at high speeds by use of high-speed wind-tunnel section data

The determination of span load distribution at high speeds by use of high-speed wind-tunnel section data

Date: February 1, 1944
Creator: Boshar, John
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
An electron and x-ray diffraction investigation of surface changes on nitrided-steel piston rings during engine operation in nitrided-steel cylinders barrels

An electron and x-ray diffraction investigation of surface changes on nitrided-steel piston rings during engine operation in nitrided-steel cylinders barrels

Date: March 1, 1945
Creator: Brockway, L O
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An electron-diffraction examination of cast-iron piston rings from single-cylinder aircraft engine tests

An electron-diffraction examination of cast-iron piston rings from single-cylinder aircraft engine tests

Date: February 1, 1945
Creator: Brockway, L O
Description: None
Contributing Partner: UNT Libraries Government Documents Department
NACA Investigation of a Jet-Propulsion System Applicable to Flight

NACA Investigation of a Jet-Propulsion System Applicable to Flight

Date: April 1, 1944
Creator: Brown, Clinton E.
Description: Following a brief history of the NACA investigation of jet-propulsion, a discussion is given of the general investigation and analyses leading to the construction of the jet-propulsion ground-test mock-up. The results of burning experiments and of test measurements designed to allow quantitative flight-performance predictions of the system are presented and correlated with calculations. These calculations are then used to determine the performance of the system on the ground and in the air at various speeds and altitudes under various burning conditions. The application of the system to an experimental airplane is described and some performance predictions for this airplane are made. It was found that the main fire could be restricted to an intense, small, and short annular blue flame burning steadily and under control in the intended combustion space. With these readily obtainable combustion conditions, the combustion chamber the nozzle walls and the surrounding structure could be maintained at normal temperatures. The system investigated was found to be capable of burning one-half the intake air up the fuel rates of 3 pounds per second. Calculations were shown to agree well with experiment. It was concluded that the basic features of the jet-propulsion system investigation in the ground-test mock-up were ...
Contributing Partner: UNT Libraries Government Documents Department
Experimental constriction effects in high-speed wind tunnels

Experimental constriction effects in high-speed wind tunnels

Date: December 1, 1944
Creator: Byrne, Robert W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Two-dimensional wind-tunnel investigation of 0.20-airfoil-chord plain ailerons of different contour on an NACA 65(sub 1)-210 airfoil section

Two-dimensional wind-tunnel investigation of 0.20-airfoil-chord plain ailerons of different contour on an NACA 65(sub 1)-210 airfoil section

Date: December 1, 1945
Creator: Cahill, Jones F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental verification of a simplified vee-tail theory and analysis of available data on complete models with vee tails

Experimental verification of a simplified vee-tail theory and analysis of available data on complete models with vee tails

Date: January 1, 1945
Creator: Campbell, John P
Description: None
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
Effects of compressibility on maximum lift coefficients for six propeller airfoils

Effects of compressibility on maximum lift coefficients for six propeller airfoils

Date: January 1, 1945
Creator: Cleary, Harold E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Variation of peak pitching-moment coefficients for six airfoils as affected by compressibility

Variation of peak pitching-moment coefficients for six airfoils as affected by compressibility

Date: October 1, 1944
Creator: Cleary, Harold E
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