You limited your search to:

 Serial/Series Title: NACA Advanced Confidential Report
 Collection: Technical Report Archive and Image Library
Effect of a trailing-edge extension on the characteristics of a propeller section

Effect of a trailing-edge extension on the characteristics of a propeller section

Date: September 1, 1944
Creator: Stickle, George W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of Compressibility on Pressure Distribution over an Airfoil with a Slotted Frise Aileron

Effect of Compressibility on Pressure Distribution over an Airfoil with a Slotted Frise Aileron

Date: July 1, 1944
Creator: Luoma, Avro A
Description: Pressure distribution measurements were made over an airfoil with slotted Frise aileron up to 0.76 Mach at various angles of attack and aileron defections. Section characteristics were determined from these pressure data. Results indicated loss of aileron rolling power for deflections ranging from -12 Degrees to -19 Degrees. High stick forces for non-differential deflections incurred at high speed, which were due to overbalancing tendency of up-moving aileron, may precipitate serious control difficulties. Detailed results are presented graphically.
Contributing Partner: UNT Libraries Government Documents Department
Effect of Compressibility on the Pressure and Forces Acting on a Modified NACA 65,3-019 Airfoil Having a 0.20-Chord Flap

Effect of Compressibility on the Pressure and Forces Acting on a Modified NACA 65,3-019 Airfoil Having a 0.20-Chord Flap

Date: January 1, 1946
Creator: Lindsey, W F
Description: An investigation has been conducted in the Langley rectangular high-speed tunnel to determine the effect of compressibility on the pressure distribution for a modified NACA 65,3-019 airfoil having a 0.20-chord flap. The investigation was made for an angle-of-attack range extending from -2 to 12 deg at .20 flap deflections from 0 to -12 deg. Test data were obtained for Mach numbers from 0.28 to approximately 0.74. The results show that the effectiveness of the trailing-edge-type control surface rapidly decreased and approached zero as the Mach number increased above the critical value.
Contributing Partner: UNT Libraries Government Documents Department
Effect of Helicopter Performance of Modifications in Profile-Drag Characteristics of Rotor-Blade Airfoil Sections

Effect of Helicopter Performance of Modifications in Profile-Drag Characteristics of Rotor-Blade Airfoil Sections

Date: August 1, 1944
Creator: Gustafson, F.B.
Description: Rough conventional, smooth conventional, and laminar-flow or low-drag sections were tested. The items covered are rotor thrust for fixed power in hovering, range and endurance at cruising speed, and power required at high-forward speed. Calculations indicated that a smooth conventional section gives marked performance gains. Smaller gains are obtainable by using a low-drag section. At high speeds or loads the low-drag section is inferior to the smooth conventional section.
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
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
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 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