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 Serial/Series Title: NACA Research Memorandums
 Collection: National Advisory Committee for Aeronautics Collection
Chemical and Physical Properties of Hi-Cal-2

Chemical and Physical Properties of Hi-Cal-2

Date: January 1, 1955
Creator: Spakowski, A. E.; Allen, Harrison, Jr. & Caves, Robert M.
Description: As part of the Navy Project Zip to consider various boron-containing materials as possible high-energy fuels, the chemical and physical properties of Hi-Cal-2 prepared by the Callery Chemical Company were evaluated at the NACA Lewis laboratory. Elemental chemical analysis, heat of combustion, vapor pressure and decomposition, freezing point, density, self ignition temperature, flash point, and blow-out velocity were determined for the fuel. Although the precision of measurement of these properties was not equal to that obtained for hydrocarbons, this special release research memorandum was prepared to make the data available as soon as possible.
Contributing Partner: UNT Libraries Government Documents Department
Chemical igniters for starting jet fuel - nitric acid rockets

Chemical igniters for starting jet fuel - nitric acid rockets

Date: October 8, 1957
Creator: Morrell, Gerald & Ladanyi, Dezso J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Chordwise pressures and section moment force and moment coefficients at high subsonic speeds near midspan of a tapered 35 degree sweptback wing with a flap-type control and an attached tab

Chordwise pressures and section moment force and moment coefficients at high subsonic speeds near midspan of a tapered 35 degree sweptback wing with a flap-type control and an attached tab

Date: March 29, 1954
Creator: Hammond, Alexander D & Keffer, Barbara M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Coking of JP-4 fuels in electrically heated metal tubes

Coking of JP-4 fuels in electrically heated metal tubes

Date: November 20, 1956
Creator: Smith, Arthur L; Cook, William P & Hlavin, Vincent F
Description: A limited exploratory investigation of the rate of coking of four JP-4 fuels in electrically heated metal tubes was conducted in order to provide design information for fuel prevaporizers for turbojet-engine combustors. The fuels tested included two production and two minimum-quality JP-4 type fuels. The heating tube was operated at fuel pressures of approximately 500, 400, and 50 pounds per square inch. The operating fuel temperature was varied between approximately 600 degrees and 1200 degrees F.
Contributing Partner: UNT Libraries Government Documents Department
Cold-air investigation of a turbine with nontwisted rotor blades suitable for air cooling

Cold-air investigation of a turbine with nontwisted rotor blades suitable for air cooling

Date: March 18, 1952
Creator: Heaton, Thomas R; Slivka, William R & Westra, Leonard F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Characteristics of perforated diffusers at free-stream Mach number 1.90

Characteristics of perforated diffusers at free-stream Mach number 1.90

Date: May 8, 1950
Creator: Hunczak, Henry R & Kremzier, Emil J
Description: An investigation was conducted at Mach number 1.90 to determine pressure recovery and mass-flow characteristics of series of perforated convergent-divergent supersonic diffusers. Pressure recoveries as high as 96 percent were obtained, but at reduced mass flows through the diffuser. Theoretical considerations of effect of perforation distribution on shock stability in converging section of diffuser are presented and correlated with experimental data. A method of estimating relative importance of pressure recovery and mass flow on internal thrust coefficient basis is given and a comparison of various diffusers investigated is made.
Contributing Partner: UNT Libraries Government Documents Department
Effect of hot-gas bleedback ice prevention on performance of a turbojet engine with fixed-area tail-pipe nozzle

Effect of hot-gas bleedback ice prevention on performance of a turbojet engine with fixed-area tail-pipe nozzle

Date: May 16, 1949
Creator: Dietz, Robert O , Jr & Krebs, Richard P
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of Ice Formations on Section Drag of Swept NACA 63A-009 Airfoil with Partial-Span Leading-Edge Slat for Various Modes of Thermal Ice Protection

Effect of Ice Formations on Section Drag of Swept NACA 63A-009 Airfoil with Partial-Span Leading-Edge Slat for Various Modes of Thermal Ice Protection

Date: March 15, 1954
Creator: VonGlahn, Uwe H. & Gray, Vernon H.
Description: The effects of primary and runback ice formations on the section drag of a 36 deg swept NACA 63A-009 airfoil section with a partial-span leading-edge slat were studied over a range of angles of attack from 2 to 8 deg and airspeeds up to 260 miles per hour for icing conditions with liquid-water contents ranging from 0.39 to 1.23 grams per cubic meter and datum air temperatures from 10 to 25 F. The results with slat retracted showed that glaze-ice formations caused large and rapid increases in section drag coefficient and that the rate of change in section drag coefficient for the swept 63A-009 airfoil was about 2-1 times that for an unswept 651-212 airfoil. Removal of the primary ice formations by cyclic de-icing caused the drag to return almost to the bare-airfoil drag value. A comprehensive study of the slat icing and de-icing characteristics was prevented by limitations of the heating system and wake interference caused by the slat tracks and hot-gas supply duct to the slat. In general, the studies showed that icing on a thin swept airfoil will result in more detrimental aerodynamic characteristics than on a thick unswept airfoil.
Contributing Partner: UNT Libraries Government Documents Department
Effect of ignitor design and ignitor spark-gap environment on ignition in a turbojet combustor

Effect of ignitor design and ignitor spark-gap environment on ignition in a turbojet combustor

Date: April 1, 1954
Creator: Foster, Hampton H & Straight, David M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of immersed surfaces in combustion zone on efficiency and stability of 5-inch diameter ram-jet combustor

Effect of immersed surfaces in combustion zone on efficiency and stability of 5-inch diameter ram-jet combustor

Date: June 21, 1954
Creator: Reynolds, Thaine W & Male, Donald W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of fuels on screaming in 200-pound-thrust liquid-oxygen - fuel rocket engine

Effect of fuels on screaming in 200-pound-thrust liquid-oxygen - fuel rocket engine

Date: June 22, 1956
Creator: Pass, Isaac & Tischler, Adelbert O
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of fuselage circumferential inlet location on diffuser-discharge total-pressure profiles at supersonic speeds

Effect of fuselage circumferential inlet location on diffuser-discharge total-pressure profiles at supersonic speeds

Date: October 29, 1956
Creator: Kremzier, Emil J & Wasserbauer, Joseph F
Description: An experimental investigation of the effect of angle of attack and inlet corrected air flow on diffuser-discharge total-pressure profiles of inlets located in various circumferential positions on a fuselage was conducted at supersonic speeds. Results indicated that the diffuser total-pressure profiles for a bottom inlet were least affected by angle of attack on distortion level was obtained with a side inlet. Variation in distortion for top inlets with angle of attack was confined to the supercritical range of inlet operation.
Contributing Partner: UNT Libraries Government Documents Department
Effect of geometry on secondary flows in blade rows

Effect of geometry on secondary flows in blade rows

Date: October 16, 1952
Creator: Hansen, A G; Costello, G R & Herzig, H Z
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of fuselage fences on the angle-of-attack supersonic performance of a top-inlet - fuselage

Effect of fuselage fences on the angle-of-attack supersonic performance of a top-inlet - fuselage

Date: January 19, 1955
Creator: Kremzier, Emil J & Campbell, Robert C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Characteristics of a canard-type missile configuration with an underslung scoop inlet at Mach numbers from 1.5 to 2.0

Characteristics of a canard-type missile configuration with an underslung scoop inlet at Mach numbers from 1.5 to 2.0

Date: January 30, 1953
Creator: Fradenburgh, Evan A & Campbell, Robert C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Characteristics of a Hot Jet Discharged from a Jet-Propulsion Engine

Characteristics of a Hot Jet Discharged from a Jet-Propulsion Engine

Date: December 27, 1946
Creator: Fleming, William A.
Description: An investigation of a heated jet was conducted in conjunction with tests of an axial-flow jet-propulsion engine in the Cleveland altitude wind tunnel. Pressure and temperature surveys were made across the jet 10 and 15 feet behind the jet-nozzle outlet of the engine. Surveys were obtained at pressure altitudes of 10,000, 20,000, 30,000, and 40,000 feet with test-section velocities from 30 to 110 feet per second and test-section temperatures from 60 F to -50 F. From measurements taken throughout the operable range of engine speeds, tail-pipe outlet temperatures from 500 F to 1250 F and jet velocities from 400 to 2200 feet per second were obtained. The jet-survey data presented extend the work previously done with low-velocity and low-temperature jets to the region of high velocities and high temperatures. The results obtained agree with previously determined experimental data and with predicted theoretical expressions for the dimensionless transverse velocity and temperature profiles across a jet. The spread of both the temperature and the velocity profiles was very nearly linear. Dimensionless plots of temperature and velocity along the axis of a heated jet agree with experimental results of tests with a cold jet.
Contributing Partner: UNT Libraries Government Documents Department
Characteristics of a hydraulic control determined from transient data obtained with a turbojet engine at altitude

Characteristics of a hydraulic control determined from transient data obtained with a turbojet engine at altitude

Date: June 16, 1954
Creator: Vasu, George; Hinde, William L & Craig, R T
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Characteristics of a wedge with various holder configurations for static-pressure measurements in subsonic gas streams

Characteristics of a wedge with various holder configurations for static-pressure measurements in subsonic gas streams

Date: September 5, 1951
Creator: Gettelman, Clarence C & Krause, Lloyd N
Description: The characteristics of a wedge static-pressure sensing element with various holder configurations were determined and compared with the characteristics of the conventional tube. The probes were tested over a range of Mach number from 0.3 to 0.95 and at various pitch and yaw angles. The investigation showed that the spike-mounted wedge sensing element has a pressure coefficient comparable with the conventional subsonic static-pressure probe and the pressure coefficient of the wedge varied less than that of the conventional probe for corresponding change of yaw angle.
Contributing Partner: UNT Libraries Government Documents Department
Characteristics of flow about axially symmetric isentropic spikes for nose inlets at Mach number 3.85

Characteristics of flow about axially symmetric isentropic spikes for nose inlets at Mach number 3.85

Date: August 19, 1954
Creator: Connors, James F & Wollett, Richard R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Cooling of Gas Turbines I - Effects of Addition of Fins to Blade Tips and Rotor, Admission of Cooling Air Through Part of Nozzles, and Change in Thermal Conductivity of Turbine Components

Cooling of Gas Turbines I - Effects of Addition of Fins to Blade Tips and Rotor, Admission of Cooling Air Through Part of Nozzles, and Change in Thermal Conductivity of Turbine Components

Date: February 11, 1947
Creator: Brown, Byron
Description: An analysis was developed for calculating the radial temperature distribution in a gas turbine with only the temperatures of the gas and the cooling air and the surface heat-transfer coefficient known. This analysis was applied to determine the temperatures of a complete wheel of a conventional single-stage impulse exhaust-gas turbine. The temperatures were first calculated for the case of the turbine operating at design conditions of speed, gas flow, etc. and with only the customary cooling arising from exposure of the outer blade flange and one face of the rotor to the air. Calculations were next made for the case of fins applied to the outer blade flange and the rotor. Finally the effects of using part of the nozzles (from 0 to 40 percent) for supplying cooling air and the effects of varying the metal thermal conductivity from 12 to 260 Btu per hour per foot per degree Farenheit on the wheel temperatures were determined. The gas temperatures at the nozzle box used in the calculations ranged from 1600F to 2000F. The results showed that if more than a few hundred degrees of cooling of turbine blades are required other means than indirect cooling with fins on the rotor ...
Contributing Partner: UNT Libraries Government Documents Department
Cooling of Gas Turbines, 6, Computed Temperature Distribution Through Cross Section of Water-Cooled Turbine Blade

Cooling of Gas Turbines, 6, Computed Temperature Distribution Through Cross Section of Water-Cooled Turbine Blade

Date: May 1, 1947
Creator: Livingood, John N. B. & Sams, Eldon W.
Description: A theoretical analysis of the cross-sectional temperature distribution of a water-cooled turbine blade was made using the relaxation method to solve the differential equation derived from the analysis. The analysis was applied to specific turbine blade and the studies icluded investigations of the accuracy of simple methods to determine the temperature distribution along the mean line of the rear part of the blade, of the possible effect of varying the perimetric distribution of the hot gas-to -metal heat transfer coefficient, and of the effect of changing the thermal conductivity of the blade metal for a constant cross sectional area blade with two quarter inch diameter coolant passages.
Contributing Partner: UNT Libraries Government Documents Department
Cooling of Gas Turbines, IV - Calculated Temperature Distribution in the Trailing Part of a Turbine Blade Using Direct Liquid Cooling

Cooling of Gas Turbines, IV - Calculated Temperature Distribution in the Trailing Part of a Turbine Blade Using Direct Liquid Cooling

Date: April 18, 1947
Creator: Brown, W. Byron & Monroe, William R.
Description: A theoretical analysis of the temperature distribution through the trailing portion of a blade near the coolant passages of liquid cooled gas turbines was made. The analysis was applied to obtain the hot spot temperatures at the trailing edge and influence of design variables. The effective gas temperature was varied from 2000 degrees to 5000 degrees F in each investigation.
Contributing Partner: UNT Libraries Government Documents Department
Cooling of gas turbines IX : cooling effects from use of ceramic coatings on water-cooled turbine blades

Cooling of gas turbines IX : cooling effects from use of ceramic coatings on water-cooled turbine blades

Date: October 13, 1948
Creator: Brown, W Byron & Livingood, John N B
Description: The hottest part of a turbine blade is likely to be the trailing portion. When the blades are cooled and when water is used as the coolant, the cooling passages are placed as close as possible to the trailing edge in order to cool this portion. In some cases, however, the trailing portion of the blade is so narrow, for aerodynamic reasons, that water passages cannot be located very near the trailing edge. Because ceramic coatings offer the possibility of protection for the trailing part of such narrow blades, a theoretical study has been made of the cooling effect of a ceramic coating on: (1) the blade-metal temperature when the gas temperature is unchanged, and (2) the gas temperature when the metal temperature is unchanged. Comparison is also made between the changes in the blade or gas temperatures produced by ceramic coatings and the changes produced by moving the cooling passages nearer the trailing edge. This comparison was made to provide a standard for evaluating the gains obtainable with ceramic coatings as compared to those obtainable by constructing the turbine blade in such a manner that water passages could be located very near the trailing edge.
Contributing Partner: UNT Libraries Government Documents Department
Cooling of gas-turbines VII : effectiveness of air cooling of hollow turbine blades with inserts

Cooling of gas-turbines VII : effectiveness of air cooling of hollow turbine blades with inserts

Date: October 20, 1947
Creator: Bressman, Joseph R & Livingood, John N B
Description: None
Contributing Partner: UNT Libraries Government Documents Department