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  Partner: UNT Libraries Government Documents Department
 Decade: 1940-1949
 Serial/Series Title: NACA Advanced Confidential Report
 Collection: National Advisory Committee for Aeronautics Collection
The development and application of high-critical-speed nose inlets

The development and application of high-critical-speed nose inlets

Date: July 1, 1945
Creator: Wright, John B
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
On the flow of a compressible fluid by the hodography method I : unification and extension of present-day results

On the flow of a compressible fluid by the hodography method I : unification and extension of present-day results

Date: March 1, 1944
Creator: Kaplan, Carl
Description: None
Contributing Partner: UNT Libraries Government Documents Department
On the flow of a compressible fluid by the hodography method II : fundamental set of particular flow solutions of the Chaplygin differential equation

On the flow of a compressible fluid by the hodography method II : fundamental set of particular flow solutions of the Chaplygin differential equation

Date: November 1, 1944
Creator: Kaplan, Carl
Description: None
Contributing Partner: UNT Libraries Government Documents Department
NACA Mach number indicator for use in high-speed tunnels

NACA Mach number indicator for use in high-speed tunnels

Date: July 1, 1943
Creator: Smith, Norman F
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
The propeller and cooling-air-flow characteristics of a twin-engine airplane model equipped with NACA D(sub S)-type cowlings and with propellers of NACA 16-series airfoil sections

The propeller and cooling-air-flow characteristics of a twin-engine airplane model equipped with NACA D(sub S)-type cowlings and with propellers of NACA 16-series airfoil sections

Date: September 1, 1944
Creator: Pepper, Edward
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Profile-drag coefficients of conventional and low-drag airfoils as obtained in flight

Profile-drag coefficients of conventional and low-drag airfoils as obtained in flight

Date: May 1, 1944
Creator: Zalovcik, J. A.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Performance of an exhaust-gas "blowdown" turbine on a nine-cylinder radial engine

Performance of an exhaust-gas "blowdown" turbine on a nine-cylinder radial engine

Date: December 1, 1944
Creator: Desmon, Leland G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Determination of general relations for the behavior of turbulent boundary layers

Determination of general relations for the behavior of turbulent boundary layers

Date: July 1, 1943
Creator: Tetervin, Neal
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A Concise Theoretical Method for Profile-Drag Calculation; Advance Report

A Concise Theoretical Method for Profile-Drag Calculation; Advance Report

Date: February 1, 1944
Creator: Nitzberg, Gerald E.
Description: In this report a method is presented for the calculation of the profile drag of airfoil sections. The method requlres only a knowledge of the theoretical velocity distribution and can be applied readily once this dlstribution is ascertained. Comparison of calculated and experimental drag characteristics for several airfoils shows a satisfactory agreement. Sample calculatlons are included.
Contributing Partner: UNT Libraries Government Documents Department
Notes on the effect of surface distortions on the drag and critical Mach number of airfoils

Notes on the effect of surface distortions on the drag and critical Mach number of airfoils

Date: September 1, 1943
Creator: Allen, J.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Investigation of flow in an axially symmetrical heated jet of air

Investigation of flow in an axially symmetrical heated jet of air

Date: December 1, 1943
Creator: Corrsin, Stanley
Description: The work done under this contract falls essentially into two parts: the first part was the design and construction of the equipment and the running of preliminary tests on the 3-inch jet, carried out by Mr. Carl Thiele in 1940; the second part consisting in the measurement in the 1-inch jet flow in an axially symmetrical heated jet of air. (author).
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
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
Correlation of Wright Aeronautical Corporation cooling data on the R-3350-14 intermediate engine and comparison with data from the Langley 16-foot high-speed tunnel

Correlation of Wright Aeronautical Corporation cooling data on the R-3350-14 intermediate engine and comparison with data from the Langley 16-foot high-speed tunnel

Date: July 1, 1946
Creator: Pinkel, Benjamin & Rubert, Kennedy F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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
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
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
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
Wind-tunnel data on the aerodynamic characteristics of airplane control surfaces

Wind-tunnel data on the aerodynamic characteristics of airplane control surfaces

Date: December 1, 1943
Creator: Sears, Richard I
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-Tunnel Investigation of Shielded Horn Balances and Tabs on a 0.7-Scale Model of XF6F Vertical Tail Surface

Wind-Tunnel Investigation of Shielded Horn Balances and Tabs on a 0.7-Scale Model of XF6F Vertical Tail Surface

Date: March 1, 1944
Creator: Lowry, John G.; Maloney, James A. & Garner, I Elizabeth
Description: Results of subject tests indicate the difficulty of obtaining closely balanced rudder surfaces for most tail assemblies with shielded horns and maintaining a near zero rate-of-change of hinge-moment coefficient without an additional balancing device. A comparison is made between shielded and unshielded horn test results. Pressure distribution and tuft tests of flow over different shaped horns showed higher critical speed for medium-taper nosed horn. The trim tab nose shape had little effect on tab test results.
Contributing Partner: UNT Libraries Government Documents Department
An analysis of jet-propulsion systems making direct use of the working substance of a thermodynamic cycle

An analysis of jet-propulsion systems making direct use of the working substance of a thermodynamic cycle

Date: February 1, 1945
Creator: Rubert, Kennedy F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Comparison of calculated and experimental propeller characteristics for four-, six-, and eight-blade single-rotating propellers

Comparison of calculated and experimental propeller characteristics for four-, six-, and eight-blade single-rotating propellers

Date: February 1, 1944
Creator: Crigler, John L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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