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Aerodynamic Heating and Boundary-layer Transition on a 1/10-power nose shape in free flight at Mach numbers up to 6.7 and Free-stream Reynolds numbers up tp 16 x 10(exp 6)

Description: Report presenting testing of a modified 1/10-power nose shape in free flight at Mach numbers up to 6.7. Measured heating rates were presented and compared with calculated values. Results regarding transition and comparison with previous investigations are provided.
Date: June 17, 1957
Creator: Garland, Benjamine J.; Swanson, Andrew G. & Speegle, Katherine C.

Aerodynamic Performance of Several Techniques for Spike-Position Control of a Blunt-Lip Nose Inlet Having Internal Contraction; Mach Numbers of 0.63 and 1.5 to 2.0

Description: Memorandum presenting a study to determine locations of pressure sensors for controlling the spike position of a blunt-lip, axisymmetric inlet with internal contraction. The inlet performance was determined at Mach numbers of 0.63 and 1.5 to 2.0 for airflow schedules corresponding to those of a given turbojet engine over a wide range of ambient temperatures. The use of the ratio of a throat static pressure to either a local total or the spike-tip total pressure provided a signal that could set nearly maximum pressure recoveries at Mach numbers of 1.7 to 2.0 and within 6 percent of maximum recovery at Mach 1.5.
Date: September 17, 1957
Creator: Anderson, Arthur A. & Weinstein, Maynard I.

Altitude performance of pentaborane - JP-4 fuel blends in a modified J47 combustor

Description: From Introduction: "Experimental investigations of the combustion characteristics of diborane, pentaborane, and pentaborane-hydrocarbon blends in modified turbojet combustors have been conducted at this laboratory at the request of the Bureau of Aeronautics, Department of the Navy, as part of Project Zip. Results of these single-combustor tests are presented in references 2 to 5."
Date: April 17, 1957
Creator: Branstetter, J. Robert & Kaufman, Warner B.

Altitude-wind-tunnel investigation of several afterburner configurations having moderately high burner-inlet velocities

Description: From Introduction: "The screech investigation, reported in reference 1, included a large number of afterburner configurations. Several of these configurations are presented herein to show the effects of afterburner-inlet gas whirl pattern, flame-holder design, and fuel distribution on performance as determined by combustion efficiency, augmented thrust ratio, and special fuel consumption."
Date: November 17, 1954
Creator: Schulze, F. W.; Bloomer, H. E. & Miller, R. R.

Analysis of a nuclear-powered liquid-metal ducted-fan cycle

Description: From Introduction: "The results are presented for flight Mach numbers of 0.9 to 1.5 at an altitude of 50,000 feet. The effect of flight altitude on optimum engine design-point airplane performance is also shown."
Date: December 17, 1952
Creator: Rom, F. E. & Wachtl, W. W.

Analysis of a Nuclear-Powered Liquid-Metal Ducted-Fan Cycle

Description: From Introduction: "The results are presented for flight Mach numbers of 0.9 to 1.5 at an altitude of 50,000 feet. The effect of flight altitude on optimum engine design-point airplane performance is also shown."
Date: December 17, 1952
Creator: Rom, F. E. & Wachtl, W. W.

Analysis of experimental sea-level transient data and analog method of obtaining altitude response for turbine-propeller engine with relay-type speed control

Description: From Introduction: "This report shows correlation between actual transient data obtained from the engine and solutions to a simulated system set up on an analog computer. Data are presented for response of engine speed to changes in set speed when the power plant was being controlled by a relay-type electronic governor that acted to maintain set speed by varying propeller pitch. Correlation obtained for sea-level conditions between actual time data and analog solutions is discussed."
Date: May 17, 1951
Creator: Vasu, George & Pack, George J.

Analytical Investigation of Ram-Jet-Engine Performance in Flight Mach Number Range From 3 to 7

Description: "An analytical investigation was made of the performance of isolated ram-jet engines in the flight Mach number range from 3 to 7 for two types of diffuser, a high-efficiency diffuser, and a normal-shock diffuser. The fuel was assumed to be a hydrocarbon similar to gasoline. The conclusions reached are: (1) a design altitude of about 100,000 feet is desirable for a high-efficiency high Mach number ram jet on the basis of engine construction and performance; and (2) although greater thrust could be obtained with other fuels, gasoline provides sufficient energy release for maximum engine efficiency in the flight Mach number range investigated. The maximum engine efficiency calculated was 0.47, which occurred at a Mach number of 5. At a Mach number of 7, the maximum propulsive-thrust coefficient was 0.57" (p. 1).
Date: October 17, 1951
Creator: Evans, Philip J., Jr.

Analytical Investigation of Turbines With Adjustable Stator Blades and Effect of These Turbines on Jet-Engine Performance

Description: From Introduction: "A comparison is also made of the actual performance of two contemporary jet engines with estimated performance, assuming the engines were equipped with adjustable-angle stators and adjustable exhaust nozzles. Charts are presented that aid in estimating the performance of adjustable-stator turbines."
Date: July 17, 1950
Creator: Silvern, David H. & Slivka, William R.

An Analytical Study of the Comparative Performance of Four Air-Induction Systems for Turbojet-Powered Airplanes Designed to Operate at Mach Numbers Up to 1.5

Description: Memorandum presenting a study made to ascertain some of the operational characteristics of four types of air-induction systems for a turbojet-powered airplane intended to operate at a range of Mach numbers at an altitude of 35,332 feet. The investigation included air-induction systems with and wthout ramps to produce oblique shock waves, with fixed and variable inlet areas, and with divergent diffusers.
Date: June 17, 1952
Creator: Blackaby, James R.

An analytical study of the effects of increasing fin chord on the lift and longitudinal stability characteristics of constant-span fin-body combinations of fineness ratio 14

Description: Report presenting an analysis to determine the effect of increasing the fin-chord length while holding the span constant on the lift and longitudinal static stability of fin-body combinations. Rectangular and triangular fins with spans of 2 and 3 body diameters in combination with a fineness-ratio-14 ogive-cylinder body were tested.
Date: January 17, 1957
Creator: English, Roland D.

Arrangement of Bodies of Revolution in Supersonic Flow to Reduce Wave Drag

Description: The wave drag of a combination of slender bodies of revolution at zero angle of attack is studied with a view to determining the arrangements for which the total drag is a minimum.Linearized theory is used to calculate the pressure distribution in the field surrounding the bodies. The interference drag coefficient is computed for different arrangements. The special cases of two bodies and of a three-body combination with bilateral symmetry are considered. The bodies treated are of the form determined by Sears and Haack as having minimum wave drag for prescribed volume and length. They also have equal fineness ratios. Numerical calculations of the drag coefficient of interference are carried out and curves are drawn which show the relative positions at which minimum drag occurs. A three-body configuration is found for which the total wave drag is about 35 percent less than the sum of the individual wave drags of the three bodies.
Date: December 17, 1951
Creator: Friedman, Morris D.

Combustion efficiency of homogeneous fuel-air mixtures in a 5-inch ram-jet-type combustor

Description: Report presenting combustion-efficiency data for a 5-inch-diameter combustor employing a straight V-gutter flame holder and a simple cone flame holder. The data covers a range of inlet static pressures, temperatures, and velocities for four fuels. The majority of the data indicated that the combustion efficiency was relatively insensitive to fuel-air ratio over the range of fuel-air ratios investigated.
Date: November 17, 1952
Creator: Reynolds, Thaine W. & Ingebo, Robert D.

Comparison of drag, pressure recovery, and surface pressure of a scoop-type inlet and an NACA submerged inlet at transonic speeds

Description: Report presenting an investigation of a solid half body modified to mount a scoop inlet and a submerged inlet while maintaining the same entrance geometry, afterbody, and diffuser for both inlets. Comparative pressure-recovery, pressure-distribution, and drag data were obtained for the two inlet types.
Date: December 17, 1951
Creator: Frank, Joseph L. & Taylor, Robert A.

Comparison of locked-rotor and windmilling drag characteristics of an axial-flow-compressor type turbojet engine

Description: The internal drag of an axial-flow turbojet engine with the rotor locked in place to prevent windmilling and with the engine windmilling was obtained over a range of simulated Mach numbers. The corrected internal drag of the engine with the locked rotor was 210 pounds or only 46 percent of the windmilling drag at a flight Mach number of 0.8.
Date: January 17, 1952
Creator: Vincent, K. R.; Huntley, S. C. & Wilsted, H. D.

Comparison of outside-surface heat-transfer coefficients for cascades of turbine blades

Description: A comparison of available results from heat-transfer investigations on cascades of turbine blades is presented using the Nusselt equation. The conventional correlation procedure is modified by defining the Reynolds number by the average of the velocities and the pressures around the blades. The correlation of the results from impulse blades was improved by using the Reynolds number defined by the average velocity and pressure. The final comparison indicated that several variables, which possibly influence heat transfer, should be investigated.
Date: July 17, 1950
Creator: Hubbartt, James E.

Comparison of Performance and Component Frontal Areas of Hypothetical Two-Spool and One-Spool Turbojet Engines

Description: For constant-mechanical-speed operation, the two-spool thrust values are as great as or greater than the one-spool thrust values over the entire flight range considered, while the specific fuel consumption for the two engines agrees within 1 percent. The maximum difference in thrust occurs at Mach 2.8 in the stratosphere, where the two-spool thrust advantage is about 9 percent for operation with the after burning.
Date: January 17, 1956
Creator: Dugan, James F., Jr.

Comparison of zero-lift drags determined by flight tests at transonic speeds of symmetrically mounted nacelles in various chordwise positions at the wing tip of a 45 degrees sweptback wing and body combination

Description: Report presenting the effect on drag of varying the chordwise position of a nacelle at the wing tip of a 45 degree sweptback wing and body combination as determined through transonic flight tests at zero lift. The drag of the configuration with nacelles in the rear chordwise positions was equal to or less than the drag of the configuration without nacelles over most of the speed range.
Date: September 17, 1951
Creator: Pepper, William B., Jr. & Hoffman, Sherwood