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 Serial/Series Title: NACA Advanced Confidential Report
 Collection: Technical Report Archive and Image Library
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
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
Effects of Compressibility on the Maximum Lift Characteristics and Spanwise Load Distribution of a 12-Foot-Span Fighter-Type Wing of NACA 230-Series Airfoil Sections

Effects of Compressibility on the Maximum Lift Characteristics and Spanwise Load Distribution of a 12-Foot-Span Fighter-Type Wing of NACA 230-Series Airfoil Sections

Date: November 1, 1945
Creator: West, F E
Description: Lift characteristics and pressure distribution for a NACA 230 wing were investigated for an angle of attack range of from -10 to +24 degrees and Mach range of from 0.2 to 0.7. Maximum lift coefficient increased up to a Mach number of 0.3, decreased rapidly to a Mach number of 0.55, and then decreased moderately. At high speeds, maximum lift coefficient was reached at from 10 to 12 degrees beyond the stalling angle. In high-speed stalls, resultant load underwent a moderate shift outward.
Contributing Partner: UNT Libraries Government Documents Department
Effects of mean-line loading on the aerodynamic characteristics of some low-drag airfoils

Effects of mean-line loading on the aerodynamic characteristics of some low-drag airfoils

Date: September 1, 1943
Creator: Turner, Harold R , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The effects of roughness at high Reynolds numbers on the lift and drag characteristics of three thick airfoils

The effects of roughness at high Reynolds numbers on the lift and drag characteristics of three thick airfoils

Date: August 1, 1944
Creator: Turner, Harold R , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effects of specific types of surface roughness on boundary-layer transition

Effects of specific types of surface roughness on boundary-layer transition

Date: February 1, 1946
Creator: Loftin, L. K., Jr.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effects of specific types of surface roughness on boundary-layer transition

Effects of specific types of surface roughness on boundary-layer transition

Date: February 1, 1946
Creator: Loftin, Laurence K
Description: None
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
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
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
Engine and inspection tests of methyl tert-butyl ether as a component of aviation fuel

Engine and inspection tests of methyl tert-butyl ether as a component of aviation fuel

Date: August 1, 1944
Creator: Jones, Anthony W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Estimation of pressure distributions at subcritical speeds for turrets located on a wing

Estimation of pressure distributions at subcritical speeds for turrets located on a wing

Date: July 1, 1944
Creator: Daniels, Everett J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Estimation of pressures on cockpit canopies, gun turrets, blisters, and similar protuberances

Estimation of pressures on cockpit canopies, gun turrets, blisters, and similar protuberances

Date: May 1, 1944
Creator: Wright, Ray H
Description: None
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
An Experimental Investigation of NACA Submerged-Duct Entrances

An Experimental Investigation of NACA Submerged-Duct Entrances

Date: October 1, 1945
Creator: Frick, Charles W.; Davis, Wallace F.; Randall, Lauros M. & Mossman, Emmet A.
Description: The results of a preliminary investigation of submerged duct entrances are presented. It is shown that an entrance of this type possess desirable critical speed and pressure recovery characteristics when used on a fuselage or nacelle in a region of low incremental velocity and thin boundary layer. The data obtained indicate that submerged entrances are most suitable for use with internal-flow systems which diffuse the air only a small amount: for example, those used with jet motors which have axial-flow compressors. Where complete diffusion of the air is required, fuselage-nose or wing leading edge inlets may prove to be superior. The results of the investigation have been prepared in such a form as to permit their use by a designer and the application of these data to a specific design is discussed.
Contributing Partner: UNT Libraries Government Documents Department
An Experimental Investigation of Several Low-Drag Wing-Nacelle Combinations with Internal Air Flow

An Experimental Investigation of Several Low-Drag Wing-Nacelle Combinations with Internal Air Flow

Date: March 1, 1945
Creator: Allen, H. Julian; Frick, Charles W. & Erickson, Myles D.
Description: The results of an experimental investigation of several low-drag wing-nacelle combinations, incorporating internal air-flow systems, are presented. The external-drag increments due to these nacelles are between one-half and two-thirds of those of conventional nacelle forms. This improvement is accomplished with only minor effects on the lift and moment characteristics of the wing. The procedure employed to determine the external shape of such low-drag nacelles is considered in detail. The design of an efficient internal-flow system with or without a blower or throttle, presents no serious problems. The energy losses in the expansion before the engine and the contraction thereafter can be kept small. It is believed that these nacelles have a wide application in housing engine pusher-propeller units and, with some alteration, jet-propulsion devices. It is probable that the low external drags may not be realized if such nacelles are used with a tractor propeller because of the high level of turbulence in the propeller slipstream.
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
Experimental study of the coating found on scuffed cast-iron piston rings during operation in nitrided-steel cylinders

Experimental study of the coating found on scuffed cast-iron piston rings during operation in nitrided-steel cylinders

Date: November 1, 1944
Creator: Vierthaler, Walter A
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
Experiments on drag of revolving disks, cylinders and streamline rods at high speeds

Experiments on drag of revolving disks, cylinders and streamline rods at high speeds

Date: June 1, 1944
Creator: Regier, Arthur
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Extension of Useful Operating Range of Axial-Flow Compressors by Use of Adjustable Stator Blades

Extension of Useful Operating Range of Axial-Flow Compressors by Use of Adjustable Stator Blades

Date: January 1, 1948
Creator: Sinnette, John T & Voss, William J
Description: A theory has been developed for resetting the blade angles of an axial-flow compressor in order to improve the performance at speeds and flows other than the design and thus extend the useful operating range of the compressor. The theory is readily applicable to the resetting of both rotor and stator blades or to the resetting of only the stator blades and is based on adjustment of the blade angles to obtain lift coefficients at which the blades will operate efficiently. Calculations were made for resetting the stator blades of the NACA eight-stage axial-flow compressor for 75 percent of design speed and a series of load coefficients ranging from 0.28 to 0.70 with rotor blades left at the design setting. The NACA compressor was investigated with three different blade settings: (1) the design blade setting, (2) the stator blades reset for 75 percent of design speed and a load coefficient of 0.48, and (3) the stator blades reset for 75 percent of design speed and a load coefficient of 0.65.
Contributing Partner: UNT Libraries Government Documents Department
Field of Flow About a Jet and Effect of Jets on Stability of Jet-Propelled Airplanes

Field of Flow About a Jet and Effect of Jets on Stability of Jet-Propelled Airplanes

Date: April 1, 1946
Creator: Ribner, Herbert S.
Description: A theoretical investigation was conducted on jet-induced flow deviation. Analysis is given of flow inclination induced outside cold and hot jets and jet deflection caused by angle of attack. Applications to computation of effects of jet on longitudinal stability and trim are explained. Effect of jet temperature on flow inclination was found small when thrust coefficient is used as criterion for similitude. The average jet-induced downwash over tail plane was obtained geometrically.
Contributing Partner: UNT Libraries Government Documents Department
Flight investigation at high speeds of profile drag of wing of a P-47D airplane having production surfaces covered with camouflage paint

Flight investigation at high speeds of profile drag of wing of a P-47D airplane having production surfaces covered with camouflage paint

Date: March 1, 1946
Creator: Zalovcik, J. A. & Daum, F. L.
Description: None
Contributing Partner: UNT Libraries Government Documents Department