National Advisory Committee for Aeronautics (NACA) - 53 Matching Results

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Effect of High-Lift Devices on the Low-Speed Static Lateral and Yawing Stability Characteristics of an Untapered 45 Degrees Sweptback Wing

Description: Memorandum presenting a wind-tunnel investigation made in the stability tunnel to determine the effects of lift flaps on the static lateral stability derivatives and the yawing derivatives of an untapered 45 degree sweptback wing at low speeds. Results regarding straight flow and yawing characteristics are provided.
Date: September 30, 1948
Creator: Lichtenstein, Jacob H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Full-Scale Investigation of an Equilateral Triangular Wing Having 10-Percent-Thick Biconvex Airfoil Sections

Description: Report discussing an investigation of the low-speed characteristics of a wing with a triangular plan form, 60 degrees of sweepback at the leading edge, and 10-percent-thick biconvex airfoil sections. The purpose of the investigation was to determine the effects of semispan and full-span leading-edge and trailing-edge flaps on the longitudinal aerodynamic characteristics of the wing and the effects of a vertical fin on the lateral stability characteristics.
Date: September 30, 1948
Creator: Whittle, Edward F., Jr. & Lovell, J. Calvin
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of Performance of Single-Stage Axial-Flow Compressor Using NACA 5509-34 Blade Section

Description: Memorandum presenting an investigation conducted to study the performance of a single-stage axial-flow compressor using blades with an NACA 5509-34 airfoil section. Static- and total-pressure, total-temperature, and flow-angle surveys were taken in the compressor inlet and outlet and between blade rows to study the overall performance and individual blade-row performance.
Date: September 30, 1948
Creator: Mankuta, Harry & Guentert, Donald C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Performance investigation of can-type combustor 2: water injection at various stations in combustor

Description: Report presenting an investigation to determine the maximum quantity of water that could be injected either into or ahead of a single can-type combustor without reducing the attainable combustor-outlet temperature below the value required for engine operation and without the appearance of liquid water at the combustor outlet. Water was injected from spray nozzles at four different stations along the combustor.
Date: September 30, 1948
Creator: Cook, William P. & Zettle, Eugene V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation at Low Speeds of the Pitching Derivatives of Untapered Swept Wings

Description: Report presenting a wing-tunnel investigation in straight and pitching flow to determine the effects of independently varying aspect ratio and angle of sweep on the longitudinal rotary stability characteristics of a series of ten untapered wings. The investigation showed that an interdependent relationship existed between the effects of aspect ratio and sweep. Results regarding pitching moment due to pitching velocity and lift due to pitching velocity are provided.
Date: September 29, 1948
Creator: MacLachlan, Robert & Fisher, Lewis R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of Mach Number on Performance of an Axial-Flow Compressor Rotor-Blade Row

Description: Report presenting an investigation to study the influence of high relative inlet Mach number on the performance of a highly loaded blade row. Twenty-nine rotor blades were installed in a compressor rotor and static and total pressure, total temperature, and flow-angle surveys were taken upstream and downstream of the row.
Date: September 28, 1948
Creator: Dugan, Paul D.; Mahoney, John J. & Benser, William A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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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 wi… more
Date: September 27, 1948
Creator: Hunton, Lynn W. & James, Harry A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation at supersonic speed (M = 1.53) of the pressure distribution over a 63 degrees swept airfoil of biconvex section at several angles of attack

Description: Report presenting the results of an investigation at supersonic speed of the distribution of pressure over the surface of a swept airfoil of biconvex section at various angles of attack. The measurements are compared with supersonic lifting-surface theory, which generally indicated good agreement except over the regions of the airfoil influenced by the subsonic trailing edge and the tips. Results regarding the pressure distribution, boundary-layer studies, and normal force and pitching moment a… more
Date: September 24, 1948
Creator: Katzen, Elliott D.; Frick, Charles W. & Boyd, John W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Low-speed pressure distributions over the drooped-nose flap of a 42 degrees sweptback wing with circular-arc airfoil sections at a Reynolds number of 5.3 x 10(exp 6)

Description: Report presenting an investigation of the pressure distributions over the drooped-nose flap of a 42 degree sweptback wing with circular-arc airfoil sections and half-span trailing-edge split flaps in the 19-foot pressure tunnel. The effects of the deflection and span of the drooped-nose flap and effects of split trailing-edge flaps on the pressures over the drooped-nose flap were determined.
Date: September 23, 1948
Creator: Spooner, Stanley H. & Woods, Robert L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Theoretical Stability Derivatives of Thin Sweptback Wings Tapered to a Point with Sweptback or Sweptforward Trailing Edges for a Limited Range of Supersonic Speeds

Description: "The stability derivatives valid for a limited range of supersonic speeds are presented for a series of sweptback wings tapered to a point with sweptback or sweptforward trailing edges. These wings were derived by modifying the trailing edge of a basic triangular wing so that it coincided with lines drawn from the wing tips to the wing axis of symmetry. The stability derivatives were formulated by using the pressure distributions previously obtained for the basic triangular wing for angle of at… more
Date: September 23, 1948
Creator: Malvestuto, Frank S., Jr. & Margolis, Kenneth
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimental data concerning the effect of high heat-input rates on the pressure drop through radiator tubes

Description: From Summary: "The pressure drops through electrically heated Inconel tubes with length-diameter ratios of 29.25, 58.50, 87.75, and 117.00 have been measured at entrance Mach numbers from approximately 0.12 to the value at which choking occurred. The heat-input rate was varied from zero to the highest values allowable without damaging the tubes. Experimental data and a number of computed variables are presented in tabular form."
Date: September 22, 1948
Creator: Habel, Louis W. & Gallagher, James J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Notes on the Application of Airfoil Studies to Helicopter Rotor Design

Description: Report presenting a discussion of a number of the problems that most frequently arise with airfoils on helicopters. A reference list of published reports on airfoil section characteristics which are useful in regards to these helicopter problems is also included.
Date: September 22, 1948
Creator: Gustafson, F. B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tests of a triangular wing of aspect ratio 2 in the Ames 12-foot pressure wind tunnel 2: the effectiveness and hinge moments of a constant-chord plain flap

Description: Report presenting a semispan triangular wing with a constant-chord trailing-edge flap to evaluate the aerodynamic characteristics of the wing with landing speeds up to a Mach number of 0.95. Tests were included to ascertain the effects of the addition of a body and of modifications to the airfoil section. Results regarding the wing alone with low Mach number, wing alone with high Mach number, effect of the body, effect of the flap, effect of Mach number, lift-drag ratio, and wing-profile modifi… more
Date: September 21, 1948
Creator: Stephenson, Jack D. & Amuedo, Arthur R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tests of a triangular wing of aspect ratio 2 in the Ames 12-foot pressure wind tunnel III : the effectiveness and hinge moments of a skewed wing-tip flap

Description: Results of wind-tunnel tests of a semispan model of a triangular wing of aspect ratio 2 with a skewed wing-tip flap are presented. Lift, drag, pitching-moment, and hinge-moment data are included for subsonic Mach numbers up to 0.95. The flap showed extremely high hinge moments and low effectiveness as a longitudinal control. Although less affected by compressibility, this flap is indicated to be inferior to a constant-chord flap when applied to this triangular wing.
Date: September 21, 1948
Creator: Kolbe, Carl D. & Tinling, Bruce E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A theoretical lateral-stability analysis of XC-120 airplane

Description: "A theoretical lateral-stability analysis of the XC-120 airplane, equipped with a detachable fuselage, was made to determine the effect on the lateral stability of the high angle of wing incidence for which the airplane was designed. The results of the investigation indicated that the lateral stability of the airplane is satisfactory with or without the detachable fuselage installed" (p. 1).
Date: September 17, 1948
Creator: Sternfield, Leonard & Gates, Ordway B., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Performance investigation of can-type combustor 1: instrumentation, altitude operational limits and combustion efficiency

Description: Report presenting an investigation of the performance of a single can-type combustor designed for a turbojet engine equipped with an 11-stage axial-flow compressor and a single-stage turbine. The investigation was conducted to determine the altitude operational limits of the engine for two fuels, combustion efficiencies at various simulated conditions of altitude and engine speed, combustor-outlet temperature distribution for several altitudes at constant engine speed, and combustor total-press… more
Date: September 16, 1948
Creator: Cook, William P. & Zettle, Eugene V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Preliminary investigation of effects of combustion in ram jet on performance of supersonic diffusers 1: shock diffuser with triple-shock projecting cone

Description: Report presenting an investigation in the 20-inch supersonic tunnel at Mach number 1.92 with a 3.6-inch-diameter ram jet to determine the effects of combustion on the performance of a shock diffuser with a triple-shock projecting cone. Results are presented for a range of outlet areas and fuel flows with both single- and split-fuel-injection systems. Results regarding diffuser performance with combustion, combustion with constant outlet-inlet area ratio, combustion with constant fuel flow, diff… more
Date: September 15, 1948
Creator: Connors, J. F. & Schroeder, A. H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Study of effects of sweep on the flutter of cantilever wings

Description: An experimental and analytical investigation of the flutter of sweptback cantilever wings is reported. The experiments employed groups of wings swept back by rotating and by shearing. The angle of sweep range from 0 degree to 60 degrees and Mach numbers extended to approximately 0.85. A theoretical analysis of the air forces on an oscillating swept wing of high length-chord ratio is developed, and the approximations inherent in the assumptions are discussed. Comparison with experiment indicates… more
Date: September 9, 1948
Creator: Barmby, J. G.; Cunningham, H. J. & Garrick, I. E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Performance of conical jet nozzles in terms of flow and velocity coefficients

Description: Performance characteristics of conical jet nozzles were determined in an investigation covering a range of pressure ratios from 1.0 to 2.8, cone half-angles from 5 degrees to 90 degrees, and outlet-inlet diameter ratios from 0.50 to 0.91. All nozzles investigated had an inlet diameter of 5 inches. The flow coefficients of the conical nozzles investigated were dependent on the cone half-angle, outlet-inlet diameter ratio, and pressure ratio. The velocity coefficients were essentially constant at… more
Date: September 7, 1948
Creator: Grey, Ralph E. & Wilsted, H. Dean
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Preliminary Investigation of Various Ailerons on a 42 Degree Sweptback Wing for Lateral Control at Transonic Speeds

Description: Report presenting an investigation at transonic speeds in the high speed tunnel to determine the rolling-effectiveness characteristics of several aileron arrangements for use on a 42 degree sweptback wing. Results regarding the rolling-moment coefficients, variation of coefficient with Mach number, outboard cusp aileron, and use of the leading-edge flaps are provided.
Date: September 7, 1948
Creator: Turner, Thomas R.; Lockwood, Vernard E. & Vogler, Raymond D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Transonic Drag Characteristics of a Wing-Body Combination Showing the Effect of a Large Wing Fillet

Description: "Results of an investigation by the free-fall method are presented herein for a configuration having a body of revolution of fineness ratio 12 and 45 degrees sweptback wing mounted aft of the maximum diameter of the body. The fillets were designed to provide large increases in the sweep of the leading edge and the line of maximum thickness as the wing root was approached. Comparison of these results with those for the same configuration without fillets shows that the addition of wing fillets in… more
Date: September 7, 1948
Creator: Cheatham, Donald C. & Kurbjun, Max C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Measurements of the Longitudinal Stability and Control Characteristics of the Grumman F8F-1 Airplane, TED No. NACA 2379

Description: A series of flight tests have been made at the Langley Flight Research Division at the request of the Bureau of Aeronautics, Department of the Navy, to determine the flying qualities of the Grumman F8F-1 air- plane. This paper presents the test results necessary to determine the longitudinal stability and control characteristics end the stalling characteristics. The range of Mach numbers covered in this investigation was approximately 0.10 to 0.62, and no attempt was made to investigate compres… more
Date: September 3, 1948
Creator: Assadourian, Arthur & Reeder, John P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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