National Advisory Committee for Aeronautics (NACA) - 16 Matching Results

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Wind-Tunnel Investigation of an NACA 66-Series 16-Percent-Thick Low-Drag Tapered Wing With Fowler and Split Flaps

Description: Report presenting testing to determine the aerodynamic characteristics of an NACA 66-series 16-percent-thick low-drag tapered wing with Fowler and split flaps. The wing had a straight trialing edge and a constant-chord center section. Results regarding lift and pitching-moment characteristics and stalling characteristics are provided.
Date: January 1946
Creator: Neely, Robert H. & Foster, Gerald V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of Compressibility on the Pressure and Forces Acting on a Modified NACA 65,3-019 Airfoil Having a 0.20-Chord Flap

Description: "An investigation has been conducted in the Langley rectangular high-speed tunnel to determine the effect of compressibility on the pressure distribution for a modified NACA 65,3-019 airfoil having a 0.20-chord flap. The investigation was made for an angle-of-attack range extending from -2 to 12 deg at .20 flap deflections from 0 to -12 deg. Test data were obtained for Mach numbers from 0.28 to approximately 0.74" (p. 1).
Date: January 1946
Creator: Lindsey, W. F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Occurrence of Iron Oxides on Cast-Iron Engine Surfaces After Operation

Description: Report presenting an examination of the surfaces of used cast-iron piston rings from various single-cylinder aircraft engine tests by electron diffraction. Generally, the oxide patterns were obtained to an appreciable extent from only the top compression ring of the piston-ring assembly; the other rings gave predominately a graphite pattern.
Date: February 1946
Creator: Nowick, A. S. & Brockway, L. O.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Determination of the Stability and Control Characteristics of a Straight-Wing, Tailless Fighter-Airplane Model in the Langley Free-Flight Tunnel

Description: Report presenting an investigation to determine the stability and control characteristics of a straight-wing, tailless fighter model with a pusher propeller in the free-flight tunnel. The investigation consisted principally of force and flight tests of a powered dynamic model. Results regarding longitudinal stability, longitudinal control, trim at high angles of attack, lateral stability, and lateral control are provided.
Date: February 1946
Creator: Seacord, Charles L., Jr. & Ankenbruck, Herman O.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Investigation at High Speeds of Profile Drag of Wing of a P-47D Airplane Having Production Surfaces Covered with Camouflage Paint

Description: Wing section outboard of flap was tested by wake surveys in Mach range of 0.25 - 0.78 and lift coefficient range 0.06 - 0.69. Results indicated that minimum profile-drag coefficient of 0.0097 was attained for lift coefficients from 0.16 to 0.25 at Mach less than 0.67. Below Mach number at which compressibility shock occurred, variations in Mach of 0.2 had negligible effect on profile drag coefficient. Shock was not evident until critical Mach was exceeded by 0.025.
Date: March 1946
Creator: Zalovcik, John A. & Daum, Fred L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effects of Specific Types of Surface Roughness on Boundary-Layer Transition

Description: Report presenting tests conducted with two typical low-drag airfoils of 90-inch chord to determine the effects of surface projections, grooves, and sanding scratches on boundary-layer transition. Data were obtained for projections of various sizes and chordwise locations on both low-drag airfoils.
Date: February 1946
Creator: Loftin, Laurence K., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Development of Wing Inlets

Description: Lift, drag, internal flow, and pressure distribution measurements were made on a low-drag airfoil incorporating various air inlet designs. Two leading-edge air inlets are developed which feature higher lift coefficients and critical Mach than the basic airfoil. Higher lift coefficients and critical speeds are obtained for leading half of these inlet sections but because of high suction pressures near exist, slightly lower critical speeds are obtained for the entire inlet section than the basic … more
Date: March 1946
Creator: Racisz, Stanley F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Critical Mach Numbers of Thin Airfoil Sections with Plain Flaps

Description: Critical Mach number as function of lift coefficient is determined for certain moderately thick NACA low-drag airfoils. Results, given graphically, included calculations on same airfoil sections with plain flaps for small flap deflections. Curves indicate optimum critical conditions for airfoils with flaps in such form that they can be compared with corresponding results for zero flap deflections. Plain flaps increase life-coefficient range for which critical Mach number is in region of high va… more
Date: April 1946
Creator: Pardee, Otway O'M. & Heaslet, Max A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Stability and Control Force Tests of Four- and Six-Unit Wing Designs of Low Aspect Ratio and 20 Degree Triangular Plan Form

Description: Report presenting an investigation to obtain force-test data on a wing design suitable for high-speed guided missiles, especially data on rolling moments produced in yawed and pitched attitudes. Force tests were conducted on two models of a wing design of low aspect ratio and 20 degree triangular plan form. Results regarding the application of results, four-unit wing design, and six-unit wing design are provided.
Date: May 1946
Creator: Paulson, John W.; Varney, Elizabeth P. & Johnson, Joseph L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Paths of target-seeking missiles in two dimensions

Description: Report presenting a discussion of some of the parameters that enter into the equation of the path of a missile which is pursuing its target. The missile is assumed to be guided by a target seeker that might be employed in any one of several ways. Results regarding the normal-pursuit navigation, constant navigation, proportional navigation, line-of-sight navigation, and effect of angle of attack and sideslip are provided.
Date: July 1946
Creator: Watkins, Charles E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Field of Flow About a Jet and Effect of Jets on Stability of Jet-Propelled Airplanes

Description: A theoretical investigation was conducted on jet-induced flow deviation. Analysis is given of flow inclination induced outside cold and hot jets and jet deflection caused by angle of attack. Applications to computation of effects of jet on longitudinal stability and trim are explained. Effect of jet temperature on flow inclination was found small when thrust coefficient is used as criterion for similitude. The average jet-induced downwash over tail plane was obtained geometrically.
Date: April 1946
Creator: Ribner, Herbert S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Parameters determining performance of supersonic pilotless airplanes powered by ram-compression power planes

Description: Report presenting the dimensional parameters of ram-compression power plants as related to their thrust and economy performance and an investigation of the speed and range performance possibilities of a family of pilotless airplanes powered with one of the power plants. The analysis of the power plants includes the power-plant configuration, aerodynamic and thermodynamic cycle, constants used in the computations, power-plant performance, and operation of the power unit with fixed areas at vario… more
Date: June 1946
Creator: Hill, Paul R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A method for the calculation of external lift, moment, and pressure drag of slender open-nose bodies of revolution at supersonic speeds

Description: Report presenting a method for the calculation of the external lift, moment, and pressure drag of slender open-nose bodies of revolution at supersonic speeds. The lift, moment, and pressure drag of a typical ramjet body shape are calculated at several Mach numbers. Results regarding the results of the calculations, comparison with experiment, and another application of the method are provided.
Date: March 1946
Creator: Parker, Hermon M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Approximate Formulas for the Computation of Turbulent Boundary-Layer Momentum Thicknesses in Compressible Flows

Description: Report presenting approximate formulas for the computation of the momentum thickness of turbulent boundary layers on two-dimensional bodies, on bodies of revolution at zero angle of attack, and on the inner surfaces of round channels all in compressible flow given in the form of integrals that can be conveniently computed. Results for skin-friction formulas, laminar boundary layers, and full thickness of boundary layer are provided.
Date: March 1946
Creator: Tetervin, Neal
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Theory and Application of Hot-Wire Instruments in the Investigation of Turbulent Boundary Layers

Description: Report presenting an account of the recent developments in hot-wire instruments for use in turbulent boundary layers to determine the magnitude of the several components of the turbulent velocity fluctuations together with the correlation between them and turbulent shearing stress.
Date: March 1946
Creator: Schubauer, G. B. & Klebanoff, P. S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigations on Laminar Boundary-Layer Stability and Transition on Curved Boundaries

Description: Report presenting an investigation of the transition of the boundary layer from the laminar to the turbulent region on a flat plate, on the concave and convex side of a plate with a 20-foot radius of curvature, and on the convex side of a plate with a 30-inch radius of curvature.
Date: May 1946
Creator: Liepmann, Hans W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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