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Decade:
1940-1949
Serial/Series Title:
NACA Advanced Confidential Report
Serial/Series Title:
NACA Wartime Reports
Collection:
Technical Report Archive and Image Library
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.
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
Permallink:digital.library.unt.edu/ark:/67531/metadc61859/
NACA Mach number warning device for use in flight
Date: July 1, 1944
Creator: Goodman, Jerry
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc62414/
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
Permallink:digital.library.unt.edu/ark:/67531/metadc61348/
Charts for estimation of the characteristics of a helicopter rotor in forward flight I : profile drag-lift ratio for untwisted rectangular blades
Date: August 1, 1944
Creator: Gustafson, F B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc61833/
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
Permallink:digital.library.unt.edu/ark:/67531/metadc62530/
Study of Jet-Propulsion System Comprising Blower, Burner, and Nozzle
Date: May 1, 1944
Creator: Hall, Eldon W
Description: A study was made of the performance of a jet-propulsion system composed of an engine-driven blower, a combustion chamber, and a discharge nozzle. A simplified analysis is made of this system for the purpose of showing in concise form the effect of the important design variables and operating conditions on jet thrust, thrust horsepower, and fuel consumption. Curves are presented that permit a rapid evaluation of the performance of this system for a range of operating conditions. The performance for an illustrative case of a power plant of the type under consideration id discussed in detail. It is shown that for a given airplane velocity the jet thrust horsepower depends mainly on the blower power and the amount of fuel burned in the jet; the higher the thrust horsepower is for a given blower power, the higher the fuel consumption per thrust horsepower. Within limits the amount of air pumped has only a secondary effect on the thrust horsepower and efficiency. A lower limit on air flow for a given fuel flow occurs where the combustion-chamber temperature becomes excessive on the basis of the strength of the structure. As the air-flow rate is increased, an upper limit is reached where, ...
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc62460/
A theoretical analysis of the performance of a diesel engine-compressor-turbine combination for aircraft
Date: April 1, 1945
Creator: Hall, Eldon W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc62106/
Correlation of the drag characteristics of a P-51B airplane obtained from high-speed wind-tunnel and flight tests
Date: February 1, 1945
Creator: Hamilton, William T
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc60838/
Determination of the effect of horizontal-tail flexibility on longitudinal control characteristics
Date: February 1, 1945
Creator: Harmon, S M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc61496/
Comparison of fixed-stabilizer, adjustable- stabilizer and all-movable horizontal tails
Date: October 1, 1945
Creator: Harmon, Sidney M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc61649/