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Comparison of the performance of a helicopter-type ram-jet engine under various centrifugal loadings

Description: Report presenting an investigation of an 18-foot-radius helicopter rotor powered by tip-mounted ramjet engines in the helicopter test tower. The engine performance is compared with the performance determined in a previous investigation of a 9-foot-radius rotor with the same engines at similar speeds but with twice the centrifugal forces. Results regarding the propulsive characteristics, minimum specific fuel consumption and corresponding propulsive thrust, and operational characteristics are provided.
Date: October 7, 1953
Creator: Radin, Edward J. & Carpenter, Paul J.
Partner: UNT Libraries Government Documents Department

Flight experience with a delta-wing airplane having violent lateral-longitudinal coupling in aileron rolls

Description: From Summary: "During a flight investigation of the lateral stability characteristics of a high-speed delta-wing airplane, violent cross-coupled lateral and longitudinal motions were encountered. The maneuver which produced these motions was an abrupt, rudder-fixed aileron roll performed at a Mach number of 0.75 at about 40,000 feet. The motions were characterized by extreme variations in angle of attack and angle of sideslip which caused the airplane to exceed the normal and transverse acceleration limitations."
Date: October 7, 1955
Creator: Sisk, Thomas R. & Andrews, William H.
Partner: UNT Libraries Government Documents Department

Free-jet tests of a 6.5-inch-diameter ram-jet engine at Mach numbers 1.81 and 2.00

Description: Report presenting testing of a 6.5-inch-diameter ramjet engine with a design Mach number of 2.13 and a short-flame-length combustor. Performance characteristics are provided for a range of Mach numbers and fuel-air ratios. Results regarding thrust, drag tests, static pressure, and combustion efficiencies are provided.
Date: March 7, 1951
Creator: Faget, Maxime A.; Watson, Raymond S. & Bartlett, Walter A., Jr.
Partner: UNT Libraries Government Documents Department

Investigation of Reynolds number effects for a series of cone-cylinder bodies at Mach numbers of 1.62, 1.93, and 2.41

Description: From Summary: "An investigation of the Reynolds number for transition and the skin-friction drag at zero lift of eight cone-cylinder bodies having various fineness ratios has been made at Mach numbers of 1.62, 1.93, and 2.41 over a Reynolds number range from 0.3 x 10(exp 6) to 10 x 10(exp 6). The accuracy of the skin-friction data was not sufficient to permit any general conclusions to be drawn. The Reynolds number for transition was found to be dependent upon both the tunnel stagnation pressure and Mach number."
Date: October 7, 1953
Creator: Grigsby, Carl E. & Ogburn, Edmund L.
Partner: UNT Libraries Government Documents Department

Performance of multiple jet-exit installations

Description: Report presenting an investigation of the performance of clustered jet-exit installations at Mach numbers from 0.60 to 3.05. The data were obtained with tunnel-wall-mounted models with cold-air-jet exhaust. Results indicated that large base-pressure drag coefficients may be encountered in the transonic and low supersonic speed range and that the best configuration in the test was boattailed between the nacelles, had a cylindrical nacelle afterbody, and a divergent nozzle with a design pressure ratio of 15.
Date: July 7, 1958
Creator: Swihart, John M. & Nelson, William J.
Partner: UNT Libraries Government Documents Department

Performance of an impulse-type supersonic-compressor rotor having a mean turning of 114 degrees

Description: Report presenting testing of the performance of a 16-inch tip-diameter rotor designed for impulse operation at the mean radius with a relative Mach number of 1.53 and 114 degrees of turning. Results regarding the rotor with guide vanes, blade-element performance, rotor alone, and modified rotor hub contour are provided.
Date: January 7, 1957
Creator: Goldberg, Theodore J. & Erwin, John R.
Partner: UNT Libraries Government Documents Department

Propeller induced angles of attack and section angles of attack for the NACA 10-(3)(066)-03, 10-(3)(049)-03, 10-(3)(090)-03, 10-(5)(066)-03, and 10-(0)(066)-03 propellers

Description: This paper presents the results of an induced angle-of-attack calculation using a method applicable to a propeller with arbitrary circulation distribution. Tables of induced angles of attack and section angles of attack and curves of wake-survey results are presented for the NACA 10-(3)(066)-03, 10-(3)(049)-03, 10-(3)(090)-03, 10-(5)(066)-03, and 10-(0)(066)-03 propellers. A brief description of the method of calculating propeller induced angles of attack is given.
Date: May 7, 1952
Creator: Igoe, William B. & Davidson, Robert E.
Partner: UNT Libraries Government Documents Department

A low-pressure-loss short afterburner for sea-level thrust augmentation

Description: Report presenting an investigation of the problems associated with the design of a low-pressure-loss, short afterburner for sea-level thrust augmentation in a static, sea-level test stand using the power section of a 5970-pound-thrust, axial-flow turbojet engine. The various portions of the afterburner and procedures used to test it are described. Results regarding diffuser pressure losses, afterburner pressure losses, and afterburner performance are provided.
Date: June 7, 1955
Creator: Ciepluch, Carl C.; Velie, Wallace W. & Burley, Richard R.
Partner: UNT Libraries Government Documents Department

Measurements and predictions of flow conditions on a two-dimensional base separating a Mach number 3.36 jet and a Mach number 1.55 outer stream

Description: Report presenting an investigation in a mixing-zone apparatus to determine the effects of jet flow on two-dimensional base pressure and the development of supersonic channel flow about a two-dimensional base, with and without splitter plates of different thicknesses. Results regarding the starting cycle for outer streams only, the fully established supersonic flow, and the base pressure between the center jet and outer streams are provided.
Date: May 7, 1954
Creator: Coletti, Donald E.
Partner: UNT Libraries Government Documents Department

Lift, drag, and static longitudinal stability characteristics of configurations consisting of three triangular wing panels and a body of equal length at Mach numbers from 3.00 to 6.28

Description: Report presenting lift, drag, and pitching-moment coefficients, lift-drag ratios, and center-of-pressure positions for three highly swept three-wing tailless configurations determined from tests at a range of Mach numbers and angles of attack.
Date: February 7, 1956
Creator: Savin, Raymond C. & Wong, Thomas J.
Partner: UNT Libraries Government Documents Department

Comparison of normal load factors experienced with jet fighter airplanes during combat operations with those of flight tests conducted by the NACA during operational training

Description: Report presenting a comparison of normal load factors measured during combat operations with those measured during an NACA flight program conducted with fully instrumented service airplanes in operational training. Results indicated that for an equal number of maneuvers, normal load factors obtained from the NACA program are greater than those obtained during combat when based on the service-limit load factor.
Date: July 7, 1954
Creator: Hamer, Harold A.; Huss, Carl R. & Mayer, John P.
Partner: UNT Libraries Government Documents Department

Effect of formation position on load factors obtained on F2H airplanes

Description: Report presenting results of a four-plane formation flight with twelve pull-up maneuvers in the form of plots of maximum load factor attained versus airplane position for three combinations of four F2H airplanes. The load factor was generally found to increase toward the end of the formation, and movements of the lead plane that are too sharp might cause excessive loads on the last plane in the formation.
Date: December 7, 1951
Creator: Huss, Carl R. & Hamer, Harold A.
Partner: UNT Libraries Government Documents Department

Design and test of mixed-flow impellers 6: performance and parabolic-bladed impeller with shroud redesigned by rapid approximate method

Description: Report presenting a centrifugal impeller with a modified design procedure to reduce the velocity gradients existing along the hub from inlet to outlet. The modified impeller had better performance characteristics than the original at all speeds tested.
Date: September 7, 1955
Creator: Smith, Kenneth J. & Osborn, Walter M.
Partner: UNT Libraries Government Documents Department

Design and test of mixed-flow impellers 5: design procedure and performance results for two vaned diffusers tested with impeller model MFI-1B

Description: Report presenting the design procedure and experimental test results for a range of impeller speeds for two vaned diffusers of 24 and 40 vanes. Both sets of vanes were designed to give approximately the same prescribed velocity distribution on the vane surfaces and were tested with the same impeller. Results regarding overall performance and the total-pressure-loss coefficient for both vanes are provided.
Date: July 7, 1955
Creator: Hamrick, Joseph T. & Osborn, Walter M.
Partner: UNT Libraries Government Documents Department

Effect of wing camber and twist at Mach numbers from 1.4 to 2.1 on the lift, drag, and longitudinal stability of a rocket-powered model having a 52.5 degree sweptback wing of aspect ratio 3 and inline tail surfaces

Description: Report presenting a free-flight investigation to determine the effect of wing camber and twist at Mach numbers from 1.4 to 2.1 on the lift, drag, and longitudinal stability of a configuration with 52.5 degrees sweptback wing of aspect ratio 3, and inline tail surfaces. Results regarding drag, total normal force and pitching moment, and wash at the horizontal tail are provided.
Date: May 7, 1956
Creator: Gillespie, Warren, Jr.
Partner: UNT Libraries Government Documents Department

Experimental investigation of the damping in roll of cruciform triangular wing-body combinations at Mach numbers from 1.5 to 6.0

Description: Report presenting measurements of the damping in roll of cruciform triangular wings of aspect ratios 0.64, 1.28, and 2.31 at supersonic Mach numbers from 1.5 to 6.0. The models were launched from rifled guns and the time history of the model roll position in free flight was explored. Results regarding the comparison with theory, transonic effects, and comparison with results at other facilities are provided.
Date: April 7, 1954
Creator: Boissevain, Alfred G.
Partner: UNT Libraries Government Documents Department

Aerodynamic characteristics of a 0.04956-scale model of the Convair F-102B airplane at Mach numbers of 1.41, 1.61, and 2.01: COORD No. AF-231

Description: Report discussing testing of a scale model of the Convair F-102B to determine its aerodynamic characteristics at several Mach numbers. Four basic body modifications and two afterbody configurations were evaluated.The body modifications were all found to slightly reduce values of minimum drag, but did not cause a change in the static stability and lift-curve-slope values compared to the F-102A.
Date: February 7, 1956
Creator: Driver, Cornelius & Robinson, Ross B.
Partner: UNT Libraries Government Documents Department

Qualitative measurements of the effective heats of ablation of several materials in supersonic air jets at stagnation temperatures up to 11,000 F

Description: Report presenting testing on the effective heats of ablation of a number of materials using supersonic arc jets at stagnation temperatures ranging from 2000 degrees F to 11,000 degrees F. Materials examined included Teflon, nylon, Lucite, polystyrene, ammonium chloride, sodium carbonate, several phenolic resins, and melamine-fiber glass laminate.
Date: July 7, 1958
Creator: Rashis, Bernard; Witte, William G. & Hopko, Russell N.
Partner: UNT Libraries Government Documents Department

Theoretical study of the tunnel-boundary lift interference due to slotted walls in the presence of the trailing-vortex system of a lifting model

Description: Report presenting some equations that give the interference on the trailing-vortex system of a uniformly loaded finite-span wing in a circular tunnel containing partly open and partly closed walls, with special reference to symmetrical arrangements of the open and closed portions. Methods are given for extending the equations to include tunnel shapes other than circular.
Date: April 7, 1953
Creator: Matthews, Clarence W.
Partner: UNT Libraries Government Documents Department

Pressure distribution at low speed on a model incorporating a W wing with aspect ratio 6, 45 degrees sweep, taper ratio 0.6, and an NACA 65A009 airfoil section

Description: Report presenting results of pressure-distribution measurements at low speed on a wing-fuselage combination with a wing of W plan form with aspect ratio 6, 45 degrees sweep, taper ratio 0.6, and an NACA 65A009 airfoil section placed parallel to the plane of symmetry. Results regarding aerodynamic characteristics, pressure distribution on the wing, pressure distribution on the fuselage, aerodynamic section characteristics, and stall patterns are provided.
Date: August 7, 1952
Creator: Polhamus, Edward C. & Few, Albert G., Jr.
Partner: UNT Libraries Government Documents Department

Preliminary investigation of combustion in flowing gas with various turbulence promoters

Description: Report presenting an investigation of combustion occurring downstream of various turbulence promoters in a 20-inch length of a 1 7/8-inch inside-diameter, water-jacketed tubing using premixed vaporized fuel and air. Among the turbulence promoters investigated were flat plates perforated with 1/8-inch diameter holes, 1/4-inch diameter holes, and a single large hole to give 12.4, 17.2, and 21.5 percent open area respectively.
Date: June 7, 1948
Creator: Haddock, Gordon W. & Childs, J. Howard
Partner: UNT Libraries Government Documents Department

An investigation of three NACA 1-series nose inlets at subsonic and transonic speeds

Description: Report presenting an investigation of three NACA 1-series nose inlets at subsonic and transonic speeds in the 8-foot transonic tunnel. Drag, surface-pressure, and pressure-recovery measurements and schileren photographs were obtained at zero angle of attack through a range of Mach numbers and mass-flow-ratios. Results regarding tunnel boundary interference, surface pressure distribution, external drag, and pressure recovery are provided.
Date: January 7, 1953
Creator: Pendley, Robert E.; Milillo, Joseph R. & Fleming, Frank F.
Partner: UNT Libraries Government Documents Department

Measurements of fluctuating pressures on a 1/4-scale model of the X-1 airplane with a 10-percent-thick wing in the Langley 16-foot transonic tunnel

Description: Report presenting pressure fluctuations measured near the trailing edge of the wing and near the leading edge of the tail of a scale model of the X-1 airplane with a 10-percent-thick wing in the 16-foot transonic tunnel. Results regarding frequency analyses are also provided.
Date: January 7, 1953
Creator: Habel, Louis W. & Steinberg, Seymour
Partner: UNT Libraries Government Documents Department

A flight investigation at transonic speeds of a model having a triangular wing of aspect ratio 2

Description: Report presenting free-falling recoverable model tests conducted at transonic speeds on a model with a triangular wing of aspect ratio 2 and a 45 degree swept tail in the chord plane of the wing. Static- and dynamic-longitudinal-stability data for the complete model, force and moment data for the major components of the model, and load distributions over the fuselage of the model were evaluated at several angles of attack.
Date: September 7, 1955
Creator: White, Maurice D.
Partner: UNT Libraries Government Documents Department