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Wind-Tunnel Investigation at Low Speed of Sideslipping, Rolling, Yawing, and Pitching Characteristics for a Model of a 45 Degree Swept-Wing Fighter-Type Airplane

Description: Report presenting an investigation in the stability tunnel at low speed to determine the rolling characteristics at combined angles of attack and sideslip for a model of a fighter-type airplane with a 45 degree sweptback wing. Testing was performed with the original vertical tail and a vertical tail with a 27 percent larger exposed area. Results regarding the static longitudinal stability, directional stability, and effect of the different tails are presented.
Date: September 1, 1955
Creator: Jaquet, Byron M. & Fletcher, H. S.
Item Type: Refine your search to only Report
open access

Investigation of a high-pressure-ratio eight-stage axial-flow research compressor with two transonic inlet stages 6: over-all performance, rotating stall, and blade vibration at low and intermediate compressor speeds

Description: Report presenting an investigation to determine the overall performance of the modified eight-stage axial-flow compressor with new fourth-stage stator blades as part of a study of the problems encountered in a high-pressure-ratio axial-flow compressor with transonic inlet stages. The performance of the compressor was determined over a range of weight flows at equivalent speeds from 30 to 100 percent of design speed.
Date: November 1, 1955
Creator: Standahar, Raymond M.; Hanson, Morgan P. & Geye, Richard P.
Item Type: Refine your search to only Report
open access

Longitudinal Aerodynamic Characteristics at Transonic Speeds of a Complete Model With an Unswept Wing and a Sweptback Horizontal Tail at Two Vertical Locations

Description: Memorandum presenting an investigation to determine the static longitudinal stability contribution of a horizontal tail at two vertical locations behind a 4-percent-thick unswept-wing-fuselage combination at transonic speeds. The model used in tests is comprised of an unswept wing located in the midwing position on a body of revolution and a sweptback horizontal tail mounted on a vertical tail.
Date: September 1, 1955
Creator: Hieser, Gerald & Kudlacik, Louis
Item Type: Refine your search to only Report
open access

Spark ignition of flowing gases 5: application of fuel-air-ratio and initial-temperature data to ignition theory

Description: Report presenting a study to show the effect of fuel-air ratio and initial temperature on spark-ignition energy and to apply the results to a previously developed theory of ignition. Results regarding initial-temperature effect and fuel-air-ratio effect are provided.
Date: November 1, 1955
Creator: Swett, Clyde C., Jr.
Item Type: Refine your search to only Report
open access

Hydrodynamic Pressure Distribution Obtained With a Streamline Body Equipped With Chine Strips

Description: Memorandum presenting an investigation to determine the nature of the pressure distribution and the order of magnitude of the pressures on a streamline body moving on a water surface. The body of revolution was equipped with chine strips and had a fineness ratio of 9. The results from the investigation indicate that there is a characteristic pattern of hydrodynamic pressure distribution for streamline bodies equipped with chine strips and moving on a water surface.
Date: September 1, 1955
Creator: Weinflash, Bernard
Item Type: Refine your search to only Report
open access

Comparative Dispersion Data From Ground-Launched 2.25-Inch Rockets Equipped With Cruciform and Monoplane Fins

Description: Report presenting testing of about 150 rounds of 2.25-inch subcaliber aircraft rockets equipped with standard cruiform fins and twisted monoplane fins. No significant difference in dispersion was observed for the different configurations of fins on the rockets. Results regarding the stability of the different types of rockets, and general characteristics of the flight paths are provided.
Date: November 1, 1955
Creator: Purser, Paul E.
Item Type: Refine your search to only Report
open access

Effect of Reduced Stator-Blade Trailing-Edge Thickness on Over-All Performance of a Transonic Turbine

Description: "A transonic turbine with a stator trailing-edge thickness reduced from 0.030 to 0.010 inch has been investigated experimentally. The performance results indicated an increase in efficiency of 0.6 of a point at design operation, and as much as 2.4 points at off-design conditions, as a result of reducing the trailing-edge thickness. This improvement could only be partially accounted for by the theoretical change in mixing loss for the two stator-blade rows, and it was felt that the improvement w… more
Date: November 1, 1955
Creator: Whitney, Warren J.; Stewart, Warner L. & Wong, Robert Y.
Item Type: Refine your search to only Report
open access

Pressure recovery at supersonic speeds through annular duct inlets situated in a region of appreciable boundary layer 1: addition of energy to the boundary layer

Description: Report presenting a model with a nozzle upstream of an annular duct inlet for the purpose of ejecting high-velocity air into the boundary layer of the flow along the forebody tested between Mach numbers of 1.36 and 2.01. Results wind-tunnel data, equivalent pressure recovery, and scale effects are provided.
Date: April 1, 1948
Creator: Davis, Wallace F. & Brajnikoff, George B.
Item Type: Refine your search to only Report
open access

Investigation of Flow Conditions and the Nature of the Wall-Constriction Effect Near and at Choking by Means of the Hydraulic Analogy

Description: Report presenting an investigation of the closed wind-tunnel phenomenon of choking and the wall-constriction effects in the subsonic Mach number range where supersonic Mach numbers appear using the hydraulic analogy. Application of the results to wind tunnel testing, the subsonic choking phenomena, and effects of the walls are described.
Date: September 1, 1948
Creator: Matthews, Clarence W. & Wright, Ray H.
Item Type: Refine your search to only Report
open access

Aerodynamic characteristics at high speeds of a two-blade NACA 10-(3)(062)-045 propeller and of a two-blade NACA 10-(3)(08)-045 propeller

Description: From Introduction: "The aerodynamic characteristics of a series of 10-foot-diameter propellers are being investigated in the Langley 16-foot high-speed tunnel in a comprehensive propeller research program. Using high-critical-speed NACA 16-series airfoil sections (reference 1), these propellers are designed to have Betz minimum induced-energy loss loading (reference 2) for a blade angle of 45^o at the 0.7 radius, when used as a four-blade propeller operating at an advance ratio of approximately… more
Date: October 1, 1948
Creator: Solomon, William
Item Type: Refine your search to only Report
open access

Analysis of V-g records from the Grumman F8F-2 airplane

Description: From Introduction: "In the present paper, which supplements reference 1, V-g records obtained from F8F-2 airplanes in 1949 are analyzed statistically to determine the frequency of experiencing large values of normal load factor and airspeed. These results are compared with the results from the F8F-1 airplane."
Date: July 1, 1952
Creator: Thornton, James O.
Item Type: Refine your search to only Report
open access

An Investigation at Transonic Speeds of the Aerodynamic Characteristics of an Air Inlet Installed in the Root of a 45 Degree Sweptback Wing

Description: Report presenting an investigation in the transonic blowdown tunnel from Mach numbers 0.80 to 1.41 to determine the increments in lift and drag due to installation of a triangular-shaped air inlet in the root of a 45 degree sweptback wing and to determine the internal flow characteristics of the inlet. Results regarding pressure measurements of the inlet model, force measurements of basic and inlet models, and effect of boundary-layer bypass scoop and fuselage nose configuration on characterist… more
Date: October 1, 1952
Creator: Howell, Robert R. & Keith, Arvid L., Jr.
Item Type: Refine your search to only Report
open access

Stability and Control Flight Tests of a 0.13-Scale Model of the Consolidated-Vultee XFY-1 Airplane in Take-Offs, Landings, and Hovering Flight: TED No. NACA DE 368

Description: Report presenting an investigation to determine the dynamic stability and control characteristics of a scale flying model of the Consolidated-Vultee XFY-1 vertically rising airplane. It includes the results of flight tests to determine the stability and control characteristics of the model in hovering, take-offs, and landings.
Date: October 1, 1952
Creator: Lovell, Powell M., Jr.; Smith, Charles C., Jr. & Kirby, Robert H.
Item Type: Refine your search to only Report
open access

Some effects of body cross-sectional shape, including sunken-canopy design, on drag as shown by rocket-powered-model tests at Mach numbers from 0.8 to 1.5

Description: Report presenting free-flight tests made with four fin-stabilized bodies of fineness ratio 8.91 to determine the effect of body cross-sectional shape on body drag at a range of Mach and Reynolds numbers. Results regarding the curve of drag coefficients, drag on the nose and body, and body pressure drag are provided.
Date: July 1, 1952
Creator: Stoney, William E., Jr. & Putland, Leonard W.
Item Type: Refine your search to only Report
open access

Preliminary investigation of the altitude performance of pentaborane and a pentaborane : JP-4 blend in an experimental 9.5-inch-diameter tubular combustor

Description: From Summary: "A preliminary investigation was conducted to determine the altitude performance of pentaborane and a blend fuel of 64.2 percent pentaborane in JP-4 fuel in a tubular combustor of a current production type turbojet engine. Deposits on the liner barrel and dome were virtually nonexistent. The combustion efficiency of 90 to 94 percent for pentaborane and approximately 90 percent for the blend. Outlet temperature profiles were marginal; however, the developed combustor provided lower… more
Date: April 1, 1957
Creator: Kaufman, Warner B. & Branstetter, J. Robert
Item Type: Refine your search to only Report
open access

Wind-tunnel investigation of the aerodynamic characteristics in pitch of wing-fuselage combinations at high subsonic speeds: Aspect-ratio series

Description: Report presenting an investigation in the 7- by 10-foot tunnel to determine the effect of aspect ratio on the aerodynamic characteristics in pitch of wing-fuselage combinations with 45 degrees sweepback at the quarter-chord line and 0.6 taper ratio at high subsonic speeds. Results regarding the lift characteristics, pitching-moment characteristics, drag characteristics, and lift-drag ratios are provided.
Date: April 1, 1952
Creator: Kuhn, Richard E. & Wiggins, James W.
Item Type: Refine your search to only Report
open access

Thermal shock resistance and high-temperature strength of a molybdenum disilicide - aluminum oxide ceramic

Description: From Summary: "A ceramic consisting nominally of 75 percent molybdenum disilicide and 25 percent alumium oxide was investigated to determine its thermal shock characteristics and high-temperature strength properties. In a rim-quench thermal shock evaluation, the material was found to be superior to pure molybdenum disilicide. In a simulated altitude blow-out test, the material withstood an average of 2.5 cycles when quenched from 1800 degrees Fahrenheit."
Date: October 1, 1953
Creator: Maxwell, W. A. & Smith, R. W.
Item Type: Refine your search to only Report
open access

Horizontal-Tail Load Measurements at Transonic Speeds of the Bell X-1 Research Airplane

Description: Report presenting a flight investigation to determine horizontal-tail loads at transonic speeds of the Bell X-1. The tests were made through the transonic region and at high lift coefficients. Results regarding the time histories, tail load data, aerodynamic-center positions, and potential load discrepancy explanations are presented.
Date: September 1, 1953
Creator: Rogers, John T.
Item Type: Refine your search to only Report
open access

Some Experimental Effects of Afterbody Shape on the Zero-Lift Drag of Bodies for Mach Numbers Between 0.8 and 1.3

Description: Report presenting zero-lift drag data for a series of fin-stabilized bodies differing only in afterbody shape. Three series of afterbodies with varying ratios of base radium to maximum radius were combined with a fineness-ratio-7.13 parabolic nose. Results regarding the total drag, drag breakdown, comparison of experimental and theoretical afterbody pressure drag, and afterbody design criteria are provided.
Date: October 1, 1953
Creator: Stoney, William E., Jr.
Item Type: Refine your search to only Report
open access

Downwash Behind a Triangular Wing of Aspect Ratio 3 - Transonic Bump Method

Description: Report presenting an investigation of the lift, drag, pitching-moment, and downwash characteristics of a triangular wing of aspect ratio 3 with an NACA 63A006 section. Downwash was measured by using an all-movable horizontal tail at five locations. Results regarding basic wing characteristics and stability contribution of the tail are also provided.
Date: December 1, 1953
Creator: Axelson, John A.
Item Type: Refine your search to only Report
open access

Investigation of the Low-Speed Aerodynamic Characteristics of a Variable-Sweep Airplane Model With a Twisted and Cambered Wing

Description: Report presenting an investigation to determine the low-speed characteristics of a variable-sweep airplane model with a twisted and cambered wing. The wing was designed to have a uniform load distribution at a Mach number 1.10 and a lift coefficient of 0.25 and 50 degrees sweep. Results regarding lift characteristics, drag characteristics, lift-drag ratio, pitching-moment characteristics, dynamic pressure and downwash at the tail, effect of flaps, and lateral stability characteristics are provi… more
Date: February 1, 1952
Creator: Kemp, William B., Jr.; Becht, Robert E. & Few, Albert G., Jr.
Item Type: Refine your search to only Report
open access

Aerodynamic characteristics at supersonic speeds of a series of wing-body combinations having cambered wings with an aspect ratio of 3.5 and a taper ratio of 0.2: Effects of sweep angle and thickness ratio on the static lateral stability characteristics at M = 2.01

Description: Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel at Mach number 2.01 to determine the effects of sweep angle and thickness ratio on the static lateral stability characteristics of a series of wings with taper ratio 0.2 and aspect ratio 3.5. The results are presented with little analysis.
Date: August 1, 1952
Creator: Hamilton, Clyde V.
Item Type: Refine your search to only Report
open access

Considerations in the adaptation of low-cost fuels to gas-turbine-powered commercial aircraft

Description: "In recent months interest has increased in the possible use of distillate and residual fuel oils as fuels for commercial gas-turbine aircraft. However, the use of such fuels entails the solution of many problems pertaining to fuel physical properties and combustion characteristics. This report reviews some of these problems and discusses the status of current knowledge in relation to their solution" (p. 1).
Date: October 1, 1953
Creator: Barnett, Henry C. & McCafferty, Richard J.
Item Type: Refine your search to only Report
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