National Advisory Committee for Aeronautics (NACA) - 41 Matching Results

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Flight investigation from high subsonic to supersonic speeds to determine the zero-lift drag of a transonic research vehicle having wings of 45 degree sweepback, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil sections

Description: Report presenting rocket-powered flight tests from high subsonic to supersonic speeds and at high Reynolds numbers to determine the zero-lift drag of a transonic wing-body and body-alone configuration. The configuration tested featured a wing of 45 degree sweepback, aspect ratio 4, taper ratio 0.6, and an NACA 65A006 airfoil section, and a body of fineness ratio of 10 and a frontal area equal to 6.06 percent of the wing-plan-form area.
Date: October 27, 1949
Creator: Katz, Ellis
Partner: UNT Libraries Government Documents Department

Hovering and Low-Speed Performance and Control Characteristics of the Kaman Helicopter Rotor System as Determined on the Langley Helicopter Tower. TED No. NACA DE 205

Description: From Summary: "An investigation has been conducted with the Langley helicopter tower to obtain basic performance and control characteristics of the Raman rotor system. Blade-pitch control is obtained in this configuration by utilizing an auxiliary flap to twist the blades. Rotor thrust and power required were measured for the hovering condition and over a range of wind velocities from 0 to 30 miles per hour. The control characteristics and the transient response of the rotor to various control movements were also measured."
Date: September 27, 1949
Creator: Carpenter, Paul J. & Paulnock, Russell S.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of horizontal tails. 5: 45 degree swept-back plan form of aspect ratio 2

Description: Report presenting the results of a wind-tunnel investigation of the low-speed aerodynamic characteristics of a 45 degree sweptback horizontal-tail model of aspect ratio 2 and a comparison of these results with results for a model of the same aspect ratio with an unswept hinge line. Results regarding the lift and hinge-moment parameters, static longitudinal stability, effect of Reynolds number, effect of standard roughness, effect of removing elevator nose seal, and visualization of the air flow are provided.
Date: September 27, 1949
Creator: Dods, Jules B., Jr.
Partner: UNT Libraries Government Documents Department

Dynamics of a turbojet engine considered as a quasi-static system

Description: From Summary: "A determination of the dynamic characteristics of a typical turbojet engine with a centrifugal compressor, a sonic-flow turbine-nozzle diaphragm, and fixed area exhaust nozzle is presented. A generalized equation for transient behavior of the engine was developed; this equation was then verified by calculations using compressor and turbine performance charts extrapolated from equilibrium operating data and by experimental data obtained from an engine operated under transients in fuel flow."
Date: July 27, 1949
Creator: Otto, Edward W. & Taylor, Burt L., III
Partner: UNT Libraries Government Documents Department

Effects of Mach number and sweep on the damping-in-roll characteristics of wings of aspect ratio 4

Description: An investigation of the damping-in-roll characteristics of three wings with an aspect ratio of 4, a taper ratio of 0.6, three sweep angles at the quarter chord line, and the NACA 65A006 section as determined through a range of Mach numbers and angles of attack.
Date: June 27, 1949
Creator: Kuhn, Richard E. & Myers, Boyd C., II
Partner: UNT Libraries Government Documents Department

Take-off Stability Characteristics of a 1/13-scale Model of the Consolidated Vultee Skate 7 Seaplane (TED No. NACA DE 338)

Description: The take-off stability characteristics of a Consolidated Vultee Aircraft Corporation Skate 7 seaplane were determined in the Langley tank no. 2. Trim limits of stability, trim tracks, and elevator limits of stability are presented.
Date: April 27, 1949
Creator: McKann, Robert; Coffee, Claude W. & Abrabian, Donald D.
Partner: UNT Libraries Government Documents Department

Experimental pressure distributions over wing tips at Mach number 1.9 I :wing tip with subsonic leading edge

Description: An investigation was conducted at a Mach number of 1.91 to determine spanwise pressure distribution over a wing tip in a region influenced by a sharp subsonic leading edge swept back at 70 degrees. Except for pressure distribution on the top surface in the immediate vicinity of the subsonic leading edge, the maximum difference between linearized theory and experimental data was 2 1/2 percent (of free-stream dynamic pressure) for angles of attack up to 4 degrees and 7 percent for angles of attack up to 8 degrees. Pressures on the top surface nearest the subsonic edge indicated local expansions beyond values predicted by linearized theory.
Date: January 27, 1949
Creator: Jagger, James M. & Mirels, Harold
Partner: UNT Libraries Government Documents Department

Lateral-Control Investigation on a 37 Degree Sweptback Wing of Aspect Ratio 6 at a Reynolds Number of 6,800,000

Description: Memorandum presenting the low-speed lateral-control characteristics of a 37 degree sweptback semispan wing of aspect ratio 6 and NACA 64-series airfoil sections in the 19-foot pressure tunnel. The investigation included the measurement of the hinge-moment characteristics of an aileron and the rolling-effectiveness characteristics of the aileron and two configurations of spoilers.
Date: January 27, 1949
Creator: Graham, Robert R. & Koven, William
Partner: UNT Libraries Government Documents Department

On the flying qualities of helicopters

Description: Report presenting the flying qualities problems of current helicopters, including instability with angle of attack in forward flight, control sensitivity in hovering, and control forces following control movement in maneuvers. Some possible solutions to these issues are presented.
Date: January 27, 1949
Creator: Reeder, John P. & Gustafson, F. B.
Partner: UNT Libraries Government Documents Department

Method of estimating the minimum size of a tail or wing-tip parachute for emergency spin recovery of an airplane

Description: Report presenting a method for estimating the size of a tail or wing-tip parachute required for satisfactory emergency recovery of airplanes during spin demonstrations. A comparison of the parachute sizes estimated by the method versus information obtained during experimentation indicated satisfactory agreement. Information about the calculations for a conventional and a tailless airplane is provided.
Date: October 27, 1948
Creator: Malvestuto, Frank S., Jr.
Partner: UNT Libraries Government Documents Department

Method of Estimating the Minimum Size of a Tail or Wing-Tip Parachute for Emergency Spin Recovery of an Airplane

Description: Paper presents a method for estimating the size of a tail or wing-tip parachute required for satisfactory emergency recovery of airplanes during spin demonstrations. The method was developed from an analysis of the results of investigations conducted in the 20-foot free-spinning tunnel with dynamically scaled models of 23 airplanes. Results regarding the conventional airplane, tailless aircraft, and estimation of shock load developed by the opening of the spin-recovery parachute.
Date: October 27, 1948
Creator: Malvestuto, Frank S., Jr.
Partner: UNT Libraries Government Documents Department

Theoretical Comparison of Several Methods of Thrust Augmentation for Turbojet Engines

Description: "A theoretical investigation has been made of various methods of thrust augmentation for turbojet engines. The method investigated were tail-pipe burning, water injection at the compressor inlet, a combination of tail-pipe burning and water injection, bleedoff in conjunction with water injection at the compressor inlet, and rocket assist. The effect of ratio of augmented-to-normal total liquid consumption, flight conditions, and design compressor pressure ratio on the augmentation produced by each method were determined" (p. 1).
Date: October 27, 1948
Creator: Hall, Eldon W. & Wilcox, E. Clinton
Partner: UNT Libraries Government Documents Department

Theoretical comparison of several methods of thrust augmentation for turbojet engines

Description: "A theoretical investigation of tail-pipe burning, water injection at the compressor inlet, combination tail-pipe burning plus water injection, bleedoff, and rocket-assist methods thrust augmentation for turbojet engines was made for an engine representative of those in current use. The effect of augmented liquid ratio on augmented thrust ratio and the effects of altitude and flight Mach number on the performance of various methods were determined. The additional take-off weight involved by the use of the different thrust augmentation methods, as well as the effect of the various thrust augmentation methods on the range of a representative aircraft was also investigated" (p. 727).
Date: October 27, 1948
Creator: Hall, Eldon W. & Wilcox, E. Clinton
Partner: UNT Libraries Government Documents Department

High-Speed Aerodynamic Characteristics of a Lateral-Control Model 1: NACA 0012-64 Section with 20-Percent-Chord Plain Aileron and 0 Degree and 45 Degrees Sweepback

Description: Memorandum describing wind-tunnel tests made to determine the aerodynamic characteristics of a 20-percent-chord plain aileron on a semispan wing with the NACA 0012-64 section. The report includes the results of tests of the wing unswept and swept back 45 degrees and with the aileron deflected from 0 to 10 degrees.
Date: September 27, 1948
Creator: Anderson, Joseph L. & Krumm, Walter J.
Partner: UNT Libraries Government Documents Department

An Investigation of the McDonnell XP-85 Airplane in the Ames 40- by 80-foot Wind Tunnel. Force and Moment Tests

Description: Wind-tunnel tests of the McDonnell XP-85 airplane were conducted to determine its longitudinal, lateral, and directional stability and the characteristics of the aileron, the ruddervator, the leading-edge droop nose flap, and the stall control vanes. The directional stability of the airplane with numerous skyhook modifications and with a ventral fin was also investigated. The results of the tests showed that the effectiveness of the droop nose flaps and the stall control vanes was negligible with regard to either the maximum lift or longitudinal stability of the airplane. Contrary to any previous small-scale results, extension of the skyhook caused a 75-percent reduction in the directional stability of the airplane for both low and high values of lift coefficient. The simplest solution to the problem short of a major redesign of the skyhook appears to be the adoption of a ventral fin.
Date: September 27, 1948
Creator: Hunton, Lynn W. & James, Harry A.
Partner: UNT Libraries Government Documents Department

Method for stress analysis of a swept propeller

Description: Report presenting the methods used to estimate and reduce the stresses in a swept propeller to be tested in the 8-foot high-speed tunnel. Specific information regarding the method for determination of stresses, method for reduction of moments, and relative magnitude of factors is provided.
Date: September 27, 1948
Creator: Whitcomb, Richard T.
Partner: UNT Libraries Government Documents Department

Calculated Condenser Performance for a Mercury-Turbine Power Plant for Aircraft

Description: As part of an investigation af the application of nuclear energy to various types of power plants for aircraft, calculations have been made to determine the effect of several operating conditions on the performance of condensers for mercury-turbine power plants. The analysis covered 8 range of turbine-outlet pressures from 1 to 200 pounds per square inch absolute, turbine-inlet pressures from 300 to 700 pounds per square inch absolute,and a range of condenser cooling-air pressure drops, airplane flight speeds, and altitudes. The maximum load-carrying capacity (available for the nuclear reactor, working fluid, and cargo) of a mercury-turbine powered aircraft would be about half the gross weight of the airplane at a flight speed of 509 miles per hour and an altitude of 30,000 feet. This maximum is obtained with specific condenser frontal areas of 0.0063 square foot per net thrust horsepower with the condenser in a nacelle and 0.0060 square foot per net thrust horsepower with the condenser submerged in the wings (no external condenser drag) for a turbine-inlet pressure of 500 pounds per square inch absolute, a turbine-outlet pressure of 10 pounds per square inch absolute, and 8 turbine-inlet temperature of 1600 F.
Date: August 27, 1948
Creator: Doyle, Ronald B.
Partner: UNT Libraries Government Documents Department

A comparison of flight measurements with calculations of the loss in rolling effectiveness due to wing twist

Description: From Summary: "A flight investigation was conducted with a fighter-type airplane to determine the loss in rolling effectiveness due to wing twist, and the results are compared with the loss in rolling effectiveness calculated by use of a simplified method. The computed rolling velocities showed good agreement with experimentally determined rolling velocities throughout the Mach number range covered by the flights. Extrapolation of the flight data indicated a Mach number for reversal which agreed well with that obtained from calculations."
Date: August 27, 1948
Creator: Cooney, T. V. & Wollner, Bertram C.
Partner: UNT Libraries Government Documents Department

Free-flight investigation of the rolling effectiveness of several delta wing : aileron configurations at transonic and supersonic speeds

Description: Report presenting testing of several delta wing-aileron configurations as part of a general investigation of their rolling effectiveness characteristics at transonic and supersonic speeds. Results regarding wing-aileron rolling effectiveness and drag are provided.
Date: August 27, 1948
Creator: Sandahl, Carl A.
Partner: UNT Libraries Government Documents Department

Low-Speed Investigation of a Small Triangular Wing of Aspect Ratio 2.0 1 The Effect of Combination With a Body Revolution and Height Above a Ground Plane

Description: Memorandum presenting low-speed wind-tunnel test conducted of a triangular wing of aspect ratio 2.0 with a symmetrical double-wedge section with a maximum thickness of 5 percent of the chord at 20 percent of the chord. The wing was also tested in the presence of a ground plane. Results regarding isolated wing and wing-body combinations, split-flap effectiveness, and ground effect are provided.
Date: August 27, 1948
Creator: Rose, Leonard M.
Partner: UNT Libraries Government Documents Department

Investigation of effects of movable exhaust-nozzle plug on operational performance of 20-inch ram jet

Description: Report presenting the effects of a movable exhaust-nozzle plug on the operational performance of a 20-inch ramjet in the altitude wind tunnel. Results were obtained at various exhaust-nozzle-plug positions over a range of fuel-air ratios, combustion-chamber-inlet velocities and static pressures, and ambient-air static pressures.
Date: July 27, 1948
Creator: Sterbentz, William H. & Wilcox, Fred A.
Partner: UNT Libraries Government Documents Department

Theoretical characteristics of two-dimensional supersonic control surfaces

Description: Report presenting aerodynamic characteristics of uncambered symmetrical parabolic and double-wedge airfoils with leading-edge and trailing-edge flaps using the Busemann second-order-approximation theory. Characteristics presented include aileron effectiveness factor, rate of change of hinge-moment coefficient with aileron deflection, rate of change of the pitching-moment coefficient, and the location of the center of pressure of the airfoil-aileron combination.
Date: July 27, 1948
Creator: Morrissette, Robert R. & Oborny, Lester F.
Partner: UNT Libraries Government Documents Department

Aerodynamic characteristics of several NACA airfoil sections at seven Reynolds numbers from 0.7 x 10(exp 6) to 9.0 x 10(exp 6)

Description: Report presenting an investigation of the two-dimensional aerodynamic characteristics of several NACA airfoil sections at four Reynolds numbers. Results regarding the minimum drag, maximum lift, lift-curve slope, and angle of zero lift and pitching moment are provided.
Date: May 27, 1948
Creator: Loftin, Laurence K., Jr. & Poteat, M. Irene
Partner: UNT Libraries Government Documents Department

An exploratory investigation of the relative merits of split and chord-extension flaps on a 45 degrees swept-back wing

Description: Report presenting a wind-tunnel investigation to explore the merits of split and chord-extension flaps on a 45 degree sweptback wing. Testing occurred at low speed on a semispan model equipped with split flaps of 60 and 90-percent span and a full-span chord-extension flap. Results regarding split flaps, chord-extension flap, and resultant lift coefficients after balancing pitching-moment coefficients are provided.
Date: May 27, 1948
Creator: Hopkins, Edward J.
Partner: UNT Libraries Government Documents Department