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Method for Estimating Pitching-Moment Interference of Wing-Body Combinations at Supersonic Speed

Description: Report presenting an investigation into the effects of interference at supersonic speeds on the aerodynamic properties of wing-body combinations to determine the pitching moments. The correlation points of various wing-body shapes are provided and suggestions for modifications are made.
Date: April 17, 1952
Creator: Kaattari, George E.; Nielsen, Jack Norman & Pitts, William C.
Partner: UNT Libraries Government Documents Department
open access

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.
Partner: UNT Libraries Government Documents Department
open access

Airfoil profiles for minimum pressure drag at supersonic velocities: Application of shock-expansion theory, including consideration of hypersonic range

Description: From Summary: "A comparison of optimum profiles determined by the shock-expansion method of this report with corresponding profiles determined by the linearized-theory method of a previous report shows only small differences in shape at Mach numbers up to infinity even though the linearized theory at high supersonic Mach numbers breaks down completely insofar as the drag of the profile is concerned. Curves are presented which show that for thin airfoils the use of a trailing-edge thickness cons… more
Date: September 17, 1952
Creator: Chapman, Dean R.
Partner: UNT Libraries Government Documents Department
open access

The dynamic-response characteristics of a 35 degree swept-wing airplane as determined from flight measurements

Description: From Summary: "The longitudinal and lateral-directional dynamic-response characteristics of a 35 degree swept-wing fighter-type airplane determined from flight measurements are presented and compared with predictions based on theoretical studies and wind-tunnel data. Flights were made at an altitude of 35,000 feet covering the Mach number range of 0.50 to 1.04. A limited amount of lateral-directional data were also obtained at 10,000 feet. The flight consisted essentially of recording transient… more
Date: September 17, 1952
Creator: Triplett, William C.; Brown, Stuart C. & Smith, G. Allan
Partner: UNT Libraries Government Documents Department
open access

Effect of Various Blade Modifications in Performance of a 16-Stage Axial-flow Compressor. 4 - Effect on Over-all Performance Characteristics of Decreasing Twelfth through Fifteenth Stage Stator-blade Angles 3 deg and Increasing Stator Angles in the Inlet Stages

Description: "The performance of a 16-stage axial-flow compressor, in which two modifications of unloaded inlet stages were combined with loaded exit stages, has been determined. In the first modification the exit stages were loaded by decreasing the twelfth through fifteenth stage stator angles 3 deg. as compared with the blade angles in the original compressor, and the inlet stages were unloaded by increasing the blade angles the following amounts: guide vanes and first-stage stator, 6 deg; second- and th… more
Date: March 17, 1952
Creator: Hatch, James E. & Medeiros, Arthur A.
Partner: UNT Libraries Government Documents Department
open access

As Investigation at Mach Numbers of 1.41 and 2.01 of the Aerodynamic Characteristics of an 0.025-scale Model of the MX-1712

Description: "An investigation of the aerodynamic characteristics of an 0.025-scale model of the MX-1712 configuration has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel. The tests were performed at Mach numbers of 1.41 and 2.01 at a Reynolds number of approximately 2.6 x 10(exp 6) based on the wing mean aerodynamic chord. The MX-1712 is a proposed swept-wing, jet-powered supersonic bomber aircraft. The wing is of aspect ratio 3.5, taper ratio 0.2, and thickness ratio 5.5 percent (str… more
Date: October 17, 1952
Creator: Smith, Norman F. & Hasel, Lowell E.
Partner: UNT Libraries Government Documents Department
open access

Theoretical Investigation of the Stability at Negative Static Margins of a Supersonic Missile With an Autopilot Sensitive to Pitch Angle and Pitching Velocity

Description: Memorandum presenting stability charts covering a range of small positive and negative static margins for a supersonic missile with an autopilot sensitive to angle of pitch and rate of pitch. The results in the form of stability boundaries and lines of constant damping ratio and period show that time lags have an adverse effect on stability, but this can be counteracted by using ample gain in the rate-of-pitch feedback loop. Methods of simplifying the characteristic stability equation are discu… more
Date: March 17, 1952
Creator: Cole, Henry A., Jr. & Abramovitz, Marvin
Partner: UNT Libraries Government Documents Department
open access

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.
Partner: UNT Libraries Government Documents Department
open access

Investigation of Turbines for Driving Supersonic Compressors: 1: Design and Performance of First Configuration

Description: Report presenting the design and performance of a turbine to drive a supersonic compressor in order to determine the problems that would be encountered in turbines required to drive high-speed, high-weight-flow compressors. A model of the turbine was built and operated over a range of speed and total-pressure ratios. Results regarding performance, the effects of rotor choking, and possible modifications to the design are provided.
Date: June 17, 1952
Creator: Stewart, Warner L.; Schum, Harold J. & Whitney, Warren J.
Partner: UNT Libraries Government Documents Department
open access

Effects of wing elasticity on the aerodynamic characteristics of a 45 degree sweptback-wing-fuselage combination measured in the Langley 8-foot transonic tunnel

Description: Report presenting testing of a wing-fuselage configuration with a wing of 45 degrees sweepback of the 0.25-chord line, aspect ratio of 4, taper ratio of 0.6, and NACA 65A006 airfoil sections in aluminum and steel at a range of Mach numbers and angles of attack to determine effects of wing elasticity. Results regarding the relative effects of bending and torsion, wing-tip twist, aerodynamic characteristics, and some theoretical considerations are provided.
Date: September 17, 1952
Creator: Osborne, Robert S. & Mugler, John P., Jr.
Partner: UNT Libraries Government Documents Department
open access

Investigation at high and low subsonic Mach numbers of two symmetrical 6-percent-thick airfoil sections designed to have high maximum lift coefficients at low speeds

Description: Report presenting an investigation at high and low subsonic Mach numbers of two symmetrical 6-percent-thick airfoil sections derived to have high maximum lift at low speeds. The high-speed portion of the investigation included lift, drag, and pitching moment measurements.
Date: October 17, 1952
Creator: Paradiso, Nicholas J.
Partner: UNT Libraries Government Documents Department
open access

Investigation of ram-jet afterburning as a means of varying effective exhaust nozzle area

Description: Report presenting a discussion of the flow mechanism in an afterburner extension to a ramjet engine. An experimental evaluation of the operation of 16-inch ramjet equipped with an afterburner at Mach number 1.8 and 2.0 in the supersonic wind tunnel. The experimental data confirmed the proposed method of afterburner operation.
Date: November 17, 1952
Creator: Perchonok, Eugene & Wilcox, Fred A.
Partner: UNT Libraries Government Documents Department
open access

An Experimental Investigation of the Base Pressure Characteristics of Nonlifting Bodies of Revolution at Mach Numbers From 2.73 to 4.98

Description: Report presenting an investigation in the supersonic wind tunnel to determine some of the base pressure characteristics of related bodies of revolution at zero angle of attack. The basic body shape was a 10-caliber tangent ogive nose with a cylindrical afterbody, while other shapes tested had either a blunt-nosed profile or a boat-tailed afterbody. Results regarding the variation of pressure over the base, variation of base pressure with Reynolds number, effect of nose and afterbody shape, vari… more
Date: September 17, 1952
Creator: Reller, John O., Jr. & Hamaker, Frank M.
Partner: UNT Libraries Government Documents Department
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Observations of Unsteady Flow Phenomena for an Inclined Body Fitted with Stabilizing Fins

Description: Memorandum presenting an investigation of the variations with Mach number and angle of attack of the dynamic rolling-moment characteristics of a slender body of revolution in combination with a cruciform tail in the 6- by 6-foot supersonic wind tunnel. Oscillograph records of the instantaneous rolling moment of the model were obtained for Mach numbers of 0.90, 1.20, 1.40, 1.53, 1.60, and 1.70 at a constant free-stream Reynolds number. Results regarding dynamic rolling moments and visual flow st… more
Date: January 17, 1952
Creator: Mead, Merrill H.
Partner: UNT Libraries Government Documents Department
open access

Investigation of internal film cooling of exhaust nozzle of a 1000-pound-thrust liquid-ammonia liquid-oxygen rocket

Description: Report presenting an investigation of internal film cooling of the exhaust nozzle of a 1000-pound-thrust liquid ammonia liquid-oxygen rocket engine. With water as a coolant, approximately 16 percent of the total propellant and coolant flow was required to film-cool the entire nozzle and with anhydrous liquid ammonia, approximately 19 percent of the total flow was required. Results regarding the coolant results and performance results are provided.
Date: June 17, 1952
Creator: Abramson, Andrew E.
Partner: UNT Libraries Government Documents Department
open access

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.
Partner: UNT Libraries Government Documents Department
open access

Free-spinning-tunnel investigation of a 1/30-scale model of the Grumman XS2F-1 airplane: TED No. NACA DE 366

Description: Report presenting an investigation of a 1/30-scale model of the Grumman XS2F-1 airplane in the 20-foot free-spinning tunnel to determine the erect spin and recovery characteristics of the model in the design flight condition and with the center of gravity at 30 percent of the mean aerodynamic chord. Results regarding the erect spins, inverted spins, spin-recovery parachutes, influence of power, control forces, landing condition, and recommended recovery technique are provided.
Date: September 17, 1952
Creator: Healy, Frederick M.
Partner: UNT Libraries Government Documents Department
open access

Force Tests of Three Thin Wings of Moderately Low Aspect Ratio at High Subsonic Mach Numbers

Description: Report presenting an investigation in the high-speed tunnel to determine the effect of leading-edge shape and section profile on the aerodynamic characteristics of two thin wings of aspect ratio 4. Lift, drag, and pitching-moment data are presented for a range of angles of attack and Mach numbers. Information about a third wing with an aspect ratio of 3, a taper ratio of 0.4, and a 4.5-percent-thick modified-hexagonal section are also provided.
Date: October 17, 1952
Creator: Jordan, Gareth H.
Partner: UNT Libraries Government Documents Department
open access

A Meter for Timing the Flow of Very Small Volumes of a Gas

Description: "A flowmeter has been developed which combines a volume-time measurement of the flow, regulation of the rate, and a determination or presetting of the pressure head producing the flow. This meter is capable of accurately metering and controlling very small rates of gas flow within a closed system such as those required in a small capillary tube gas viscosimeter" (p. 1).
Date: October 17, 1952
Creator: Westmoreland, J. C.
Partner: UNT Libraries Government Documents Department
open access

Flight Determination of the Longitudinal Stability of a 1/10-Scale Rocket-Powered Model of the Northrop MX-775A Missile at Low Lift Coefficients and Mach Numbers From 0.89 to 1.34

Description: Report presenting a flight investigation to determine the longitudinal stability of a scale model of the Northrop MX-775A missile at low lift coefficients through a range of Mach numbers. Results regarding the trimmed flight and model pitching are provided.
Date: September 17, 1952
Creator: Gillespie, Warren, Jr. & Arbic, Richard G.
Partner: UNT Libraries Government Documents Department
open access

Pressure drop in coolant passages of two air-cooled turbine-blade configurations

Description: Report presenting pressure and temperature changes in the cooling air flowing through air-cooled gas-turbine blades, which have been measured experimentally in a static cascade on a 10-tube blade for isothermal and nonisothermal flows, and on a 13-fine blade for isothermal flows. Values of pressure and temperature were obtained for a range of cooling-air flows over a range of Reynolds numbers, Mach numbers, and heat-transfer rates.
Date: June 17, 1952
Creator: Brown, W. Byron & Slone, Henry O.
Partner: UNT Libraries Government Documents Department
open access

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.
Partner: UNT Libraries Government Documents Department
open access

Experimental investigation of a conservatively designed turbine at four rotor-blade solidities

Description: Report presenting a program to determine limiting values of the aerodynamic parameters used in turbine design, which includes a study of several turbine designs suitable for application in current aircraft power plants. In this first report, the performance of a single-stage turbine of conservative design was studied for the purpose of establishing a basis for the comparison of turbine performance of less conservative designs.
Date: July 17, 1952
Creator: Heller, Jack A.; Whitney, Rose L. & Cavicchi, Richard H.
Partner: UNT Libraries Government Documents Department
open access

Some factors affecting fabrication and high-temperature strength of molybdenum disilicide

Description: Report presenting an investigation of the properties of molybdenum disilicide in which a fine-grain material and a large-grain material were produced using different methods. Results regarding the fine-particle sintered material, coarse-grain, hot-pressed material, a comparison of the two materials, and the effect of oxygen on sintering and mechanical properties are provided.
Date: April 17, 1952
Creator: Maxwell, W. A.
Partner: UNT Libraries Government Documents Department
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