National Advisory Committee for Aeronautics (NACA) - 119 Matching Results

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The effect of accelerating a hypothetical aircraft through the transonic range with controls fixed

Description: Memorandum presenting Mach number histories of the motion experienced by a hypothetical, small, straight-wing aircraft accelerating at various rates through an assumed controls-fixed pitch-down balance change in the transonic range. Two approximate analytical solutions of the longitudinal equations of motion are developed which are based on certain simplifying assumptions indicated by the differential-analyzer results.
Date: April 4, 1950
Creator: Matthews, Howard F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of wing-tank location on the drag and trim of a swept-wing model as measured in flight at transonic speeds

Description: Report presenting results of an exploratory free-flight investigation at zero lift of several rocket-powered drag research models equipped wing wing tanks at a range of Mach numbers. The tanks, which were slender bodies of revolution, were mounted on 34 degrees sweptback, nontapered wings of 2.7 aspect ratio. Results regarding drag and trim change are provided.
Date: April 4, 1950
Creator: Welsh, Clement J. & Morrow, John D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Investigation of the Pressure Distributions and Loads on a Front and Rear Sliding Canopy

Description: "Pressure-distribution measurements and load-coefficient data at low speeds obtained in flight for a conventional front and rear sliding canopy are presented. The load-coefficient data indicate that the highest net aerodynamic load for the front canopy was in the exploding direction and occurred with the front and rear canopies closed. The highest net load for the rear canopy was in the crushing direction with the front canopy open and the rear canopy closed" (p. 1).
Date: April 4, 1950
Creator: Huston, Wilber B. & Skopinski, T. H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A description of the design of highly swept propeller blades

Description: "A description of the two swept propellers investigated in the Langley 8-foot high-speed tunnel is presented, together with the discussions of the numerous assumptions and analyses on which the designs of these propellers are based. The blades are swept considerably along the entire blade radius and, in order to allow for reductions in the maximum stresses, are swept forward inboard and backward outboard. The blades have been designed on the basis of the blade-element method primarily to have s… more
Date: May 4, 1950
Creator: Whitcomb, Richard T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation of a 0.6-Scale Model of Hughes MX-904 Tail Surface at Supersonic Speeds: Tail Attached to a Segment of the Foreshortened Body

Description: "An investigation has been made of a partial-span model of the tail surface designed for use on the Hughes Falcon (MX-904) missile to determine the aerodynamic characteristics of the tail and elevator including elevator hinge moment. Data obtained at Mach numbers of 1.62 and 1.96 in the Langley 9- by 12-inch supersonic blowdown tunnel are presented for the condition where the tail was attached to a segment of the foreshortened body" (p. 1).
Date: May 4, 1950
Creator: Conner, D. William & Guy, Lawrence D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A comparison of the aerodynamic characteristics at transonic speeds of four wing-fuselage configurations as determined from different test techniques

Description: Report presenting a comparison of the high-speed aerodynamic characteristics of a family of four wing-fuselage configurations with four different degrees of sweepback as determined from transonic-bump model tests in the 7- by 10-foot tunnel, sting-supported model tests in the 8-foot tunnel, and the 7-foot by 10-foot tunnel.
Date: October 4, 1950
Creator: Donlan, Charles J.; Myers, Boyd C., II & Mattson, Axel T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Temperature distribution in internally heated walls of heat exchangers composed of noncircular flow passages

Description: "In the walls of heat exchangers composed of noncircular passages, the temperature varies in the circumferential direction because of local variations of the heat-transfer coefficients. A prediction of the magnitude of this variation is necessary in order to determine the region of highest temperature and in order to determine the admissible operating temperatures. A method for the determination of these temperature distributions and of the heat-transfer characteristics of a special type of hea… more
Date: October 4, 1950
Creator: Eckert, E. R. G. & Low, George M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of centrifugal compressor operated as a centripetal refrigeration turbine

Description: Report presenting testing of a centrifugal compressor from a production-type turbojet engine, which was successfully operated as a centripetal refrigeration turbine over a range of rotor speed, inlet pressure, and pressure ratio for full admission. The performance results indicated that partial admission was found to be the most efficient method of turbine control, but throttling at the turbine inlet was easy to apply. When nozzles are used, they should have erosion-resistant surfaces to minimi… more
Date: December 4, 1950
Creator: Rebeske, John J., Jr.; Parisen, Richard B. & Schum, Harold J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A wind-tunnel investigation of the aerodynamic characteristics of a full-scale sweptback propeller and two related straight propellers

Description: Report presenting an investigation of an NACA 10-(1.7)(062)-057-27 two-blade swept propeller was conducted int he 16-foot high-speed tunnel over a range of blade-angle settings. Two related straight propellers were also tested over the same operating range as the swept propeller. Results regarding envelope efficiency, effect of compressibility on maximum efficiency, effect of sweep on power coefficient, constant-power propeller operation, and effect of sweep on propeller-blade loading are provi… more
Date: January 4, 1951
Creator: Evans, Albert J. & Liner, George
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Free-flight-tunnel investigation of the dynamic lateral stability and control characteristics of a tip-to-tip bomber-fighter coupled airplane configuration

Description: Report presenting an investigation in the free-flight tunnel to determine the dynamic lateral stability and control characteristics of a coupled airplane configuration with simplified fighter models attached to the wing tips of a simplified bomber model. The configuration is meant to represent fighter airplanes carried on the wing tips of a bomber airplane to provide fighter protection for the bomber or for in-flight fueling. Results regarding the fighters attached with freedom in roll, with fr… more
Date: April 4, 1951
Creator: Bennett, Charles V. & Cadman, Robert B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Lubrication and cooling studies of cylindrical-roller bearings at high speeds

Description: The results of an experimental investigation of the effect of oil inlet distribution and oil inlet temperature on the inner and outer-race temperatures of 75-millimeter-bore (size 215) cylindrical-roller inner-race-riding cage-type bearings are reported. A radial-load test rig was used over a range of dn values (product of the bearing bore in mm and the shaft speed in r.p.m) from 0.3 x 10(5) to 1.2 x 10(6) and static radial loads from 7 to 1113 pounds.
Date: April 4, 1951
Creator: Macks, E. Fred & Nemeth, Zolton N.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Measurements of downwash and sidewash behind cruciform triangular wings at Mach number 1.4

Description: Report presenting an experimental investigation of the downwash and sidewash flow angles in a transverse plane behind a cruciform-wing and body combination. The wing-body combination had a cruciform arrangement of two identical triangular wings of aspect ratio 2.31 corresponding to a leading-edge sweep angle of 60 degrees placed on a body of fineness ratio of 16. The investigation was conducted at a specified Mach and Reynolds number and a range of angles of bank and attack.
Date: April 4, 1951
Creator: Wetzel, Benton E. & Pfyl, Frank A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Altitude-Wind-Tunnel Investigation of Performance Characteristics of a J47D Prototype (RX1-1) Turbojet Engine With Fixed-Area Exhaust Nozzle

Description: Report presenting an investigation to determine the overall performance of a prototype model of the J47D (RX1-1) turbojet engine with a fixed-area exhaust nozzle. Data was obtained for a range of engine speeds, altitudes, and Mach numbers. Results regarding the effect of those variables and generalization in terms of pumping characteristics are provided.
Date: September 4, 1951
Creator: Saari, M. J. & Wintler, J. T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Calculations on the forces and moments for an oscillating wing-aileron combination in two-dimensional potential flow at sonic speed

Description: From Summary: "The linearized theory for compressible unsteady flow is used, as suggested in recent contributions to the subject, to obtain the velocity potential and the lift and moment for a thin harmonically oscillating, two-dimensional wing-aileron combination moving at sonic speed. The velocity potential is derived by considering the sonic case as the limit of the linearized supersonic theory. From the velocity potential explicit expressions for the lift and moment are developed for vertic… more
Date: September 4, 1951
Creator: Nelson, Herbert C. & Berman, Julian H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimental and theoretical study of the effects of body size on the aerodynamic characteristics of an aspect ratio 3.0 wing-body combination

Description: Report presenting measurements made at a Mach number of 0.25 of the aerodynamic characteristics of a wing with an aspect ratio of 3 combined separately with three geometrically similar bodies of revolution with the same fineness ratio but differing sizes. Results regarding wings, bodies of revolution, wing in the presence of the bodies, wing combined with the bodies of revolution, and effect of wing incidence changes are provided.
Date: October 4, 1951
Creator: Hopkins, Edward J. & Carel, Hubert C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds: Body of revolution

Description: From Summary: "The lift, drag, and pitching moment of a body of revolution are presented for Mach numbers from 0.60 to 0.92 and from 1.20 to 1.70. These data were obtained at test Reynolds numbers of 0.64 million, 1.02 million, and 1.59 million."
Date: October 4, 1951
Creator: Heitmeyer, John C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effects on control effectiveness of systematically varying the size and location of trailing-edge flaps on a 45 degrees sweptback wing at a Mach number of 1.9

Description: Report presenting the effect of control effectiveness of systematically varying the size and location of trailing-edge flaps on a 45 degree sweptback wing at a Mach number of 1.9. The wing model had an aspect ratio of 2.5, a taper ratio of 0.625, and 6-percent-thick hexagonal airfoil sections. Results regarding the rolling-moment and yawing-moment coefficients, lift, rolling-moment, and pitching-moment effectiveness parameters, and flap characteristics are provided.
Date: December 4, 1951
Creator: Jacobsen, Carl R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Pressure distribution at low speed on a 1/4-scale Bell X-5 airplane model

Description: From Summary: "This paper contains the results of measurements at 20 degrees and 60 degrees wing sweep of the low-speed pressure distribution on the wing, wing slat, wing leading-edge fillet, and fuselage of a 1/4-scale model of a preliminary Bell X-5 airplane design. The pressure-distribution measurements were made to obtain specific aerodynamic load information for application to the Bell X-5 airplane. Some of the results, however, are useful for application to swept-wing airplanes in general… more
Date: December 4, 1951
Creator: Kemp, William B., Jr. & Few, Albert G., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary Investigation of Cyclic De-Icing of an Airfoil Using an External Electric Heater

Description: "An investigation was conducted in the NACA Lewis icing research tunnel to determine the characteristics and requirements of cyclic deicing of a 65,2-216 airfoil by use of an external electric heater. The present investigation was limited to an airspeed of 175 miles per hour. Data are presented to show the effects of variations in heat-on and heat-off periods, ambient air temperature, liquid-water content, angle of attack, and. heating distribution on the requirements for cyclic deicing" (p. 1). more
Date: February 4, 1952
Creator: Lewis, James P. & Bowden, Dean T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An active particle diffusion theory of flame quenching for laminar flames

Description: An equation for quenching distance based on the destruction of chain carriers by the surface is derived. The equation expresses the quenching distance in terms of the diffusion coefficients and partial pressures of the chain carriers and gas phase molecules, the efficiency of the surface as a chain breaker, the total pressure of the mixture, and a constant which depends on the geometry of the quenching surface. Quenching distances measured by flashback for propane-air flames are shown to be con… more
Date: March 4, 1952
Creator: Simon, Dorothy M. & Belles, Frank E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of turbines suitable for use in a turbojet engine with high compressor pressure ratio and low compressor-tip speed 1: turbine-design requirements for several engine operating conditions

Description: In order to insure satisfactory turbine performance under five turbojet-engine operating conditions, turbine design requirements were determined for the following operating conditions: take-off, maximum thrust at altitude, altitude cruising at rated rotative speed, altitude cruising with maximum-thrust exhaust nozzle area, and engine acceleration at 80 percent equivalent design rotative speed. If cruising is to be at rated engine speed, both cruising and take-off should be considered in turbine… more
Date: March 4, 1952
Creator: English, Robert E.; Silvern, David H. & Davison, Elmer H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Effect of Blade-Section Camber on the Static Characteristics of Three NACA Propellers

Description: Report discussing static testing on 3 NACA two-blade propellers with design lift coefficients of 0, 0.3, and 0.5. Information about the effect of camber on the static-thrust figure of merit, the effect of camber on the stall-flutter speed, thrust coefficient, and blade flutter is provided.
Date: April 4, 1952
Creator: Wood, John H. & Swihart, John M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of the Low-Speed Static Longitudinal Characteristics of the Republic RF-84F Airplane

Description: From Summary: "Tests in the Ames 40- by 80-foot wind tunnel of the static longitudinal characteristics of the Republic RF-84F were made to determine both the origin and a suitable remedy for a pitch up tendency of the airplane encountered at moderate lift coefficients. The results indicated that the pitch-up at moderate lift coefficients was caused by an abrupt change in downwash at the tail which in turn was traceable presumably to flow conditions associated with the inlet-to-wing leading-edge… more
Date: August 4, 1952
Creator: Hunton, Lynn W.; Griffin, Roy N., Jr. & James, Harry A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of thrust augmentation using water-alcohol injection on a 5200-pound-thrust axial-flow-type turbojet engine at static sea-level conditions

Description: Report presenting an investigation to evaluate the thrust augmentation available with various types of water-alcohol injection system on a 5200-pound-thrust axial-flow-type turbojet engine at sea-level, zero-ram conditions. Results regarding engine performance and operational characteristics are provided.
Date: September 4, 1952
Creator: Boman, David S. & Mallett, William E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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