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 Serial/Series Title: NACA Advanced Confidential Report
 Collection: Technical Report Archive and Image Library
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
Effect of tilt of the propeller axis on the longitudinal-stability characteristics of single-engine airplanes

Effect of tilt of the propeller axis on the longitudinal-stability characteristics of single-engine airplanes

Date: January 1, 1944
Creator: Delany, Noel K
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The effect of trailing-edge extension flaps on propeller characteristics

The effect of trailing-edge extension flaps on propeller characteristics

Date: January 1, 1945
Creator: Crigler, John L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The effect of wall interference upon the aerodynamic characteristics of an airfoil spanning a closed-throat circular wind tunnel

The effect of wall interference upon the aerodynamic characteristics of an airfoil spanning a closed-throat circular wind tunnel

Date: January 1, 1946
Creator: Graham, Donald J
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
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 Direction of Propeller Rotation on the Longitudinal Stability of the 1/10-Scale Model of the North American XB-28 Airplane with Flaps Neutral, Special Report

Effects of Direction of Propeller Rotation on the Longitudinal Stability of the 1/10-Scale Model of the North American XB-28 Airplane with Flaps Neutral, Special Report

Date: June 1, 1942
Creator: Delany, Noel K.
Description: The effects of direction of propeller rotation on factors affecting the longitudinal stability of the XB-28 airplane were measured on a 1/10-scale model in the 7- by 10-foot tunnel of the Ames Aeronautical Laboratory. The main effect observed was that caused by regions of high downwash behind the nacelles (power off as well as power on with flaps neutral). The optimum direction of propeller rotation, both propellers rotating up toward the fuselage, shifted this region off the horizontal tail and thus removed its destabilizing effect. Rotating both propellers downward toward the fuselage moved it inboard on the tail and accentuated the effect, while rotating both propellers right hand had an intermediate result. Comparisons are made of the tail effects as measured by force tests with those predicted from the point-by-point downwash and velocity surveys in the region of the tail. These surveys in turn are compared with the results predicted from available theory.
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