Latest content added for UNT Digital Library Partner: UNT Libraries Government Documents Departmenthttps://digital.library.unt.edu/explore/partners/UNTGD/browse/?sort=title&fq=str_title_serial:NACA+Memorandum+Reports2011-11-17T17:13:32-06:00UNT LibrariesThis is a custom feed for browsing UNT Digital Library Partner: UNT Libraries Government Documents DepartmentAcceleration, Stress, and Deflection Measurements on the XB-15 Bomber in Gusty Air2011-11-17T17:13:32-06:00https://digital.library.unt.edu/ark:/67531/metadc61098/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc61098/"><img alt="Acceleration, Stress, and Deflection Measurements on the XB-15 Bomber in Gusty Air" title="Acceleration, Stress, and Deflection Measurements on the XB-15 Bomber in Gusty Air" src="https://digital.library.unt.edu/ark:/67531/metadc61098/small/"/></a></p><p>From Introduction: "This report presents the results of these tests which cover a total of about 70 flying hours on this airplane."</p>Accelerations and bottom pressures measured on a B-24D airplane in a ditching test2011-11-17T17:13:32-06:00https://digital.library.unt.edu/ark:/67531/metadc61135/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc61135/"><img alt="Accelerations and bottom pressures measured on a B-24D airplane in a ditching test" title="Accelerations and bottom pressures measured on a B-24D airplane in a ditching test" src="https://digital.library.unt.edu/ark:/67531/metadc61135/small/"/></a></p><p>From Introduction: "This report presents only that portion of the data from the first ditching which was to be used roughly establish the accelerations experienced by the pilot and the amount of water pressure to which the fuselage structure was subjected during the ditching."</p>Accelerations Measured at Center of Gravity and Along Span of the Wing of a B-24D Airplane in Landing Impacts2011-11-17T17:13:32-06:00https://digital.library.unt.edu/ark:/67531/metadc61134/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc61134/"><img alt="Accelerations Measured at Center of Gravity and Along Span of the Wing of a B-24D Airplane in Landing Impacts" title="Accelerations Measured at Center of Gravity and Along Span of the Wing of a B-24D Airplane in Landing Impacts" src="https://digital.library.unt.edu/ark:/67531/metadc61134/small/"/></a></p><p>Report presenting measurements of a Consolidated B-24D airplane of accelerations at various points on the wing during landing impacts. landings were made with the wheels initially stationary but free to rotate, with the brakes set before contact, and with the main wheels rotating prior to contact.</p>Additional power-on wind-tunnel tests of the 1/8-scale model of the Brewster F2A airplane with full-span slotted flaps2011-11-17T17:13:32-06:00https://digital.library.unt.edu/ark:/67531/metadc62635/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc62635/"><img alt="Additional power-on wind-tunnel tests of the 1/8-scale model of the Brewster F2A airplane with full-span slotted flaps" title="Additional power-on wind-tunnel tests of the 1/8-scale model of the Brewster F2A airplane with full-span slotted flaps" src="https://digital.library.unt.edu/ark:/67531/metadc62635/small/"/></a></p><p>"Additional tests as recommended in reference 1 were made in the 7- by 10-foot wind tunnel of the 1/8-scale model of the Brewster F2A airplane to determine the angle of attack of horizontal tail and the elevator angles required for trim with flaps down" (p. 1).</p>Aerodynamic Characteristics and Flap Loads of the Brake-Flap Installation on the 0.40-Scale Model of the F4F-3 Left Wing Panel2011-11-17T17:13:32-06:00https://digital.library.unt.edu/ark:/67531/metadc61360/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc61360/"><img alt="Aerodynamic Characteristics and Flap Loads of the Brake-Flap Installation on the 0.40-Scale Model of the F4F-3 Left Wing Panel" title="Aerodynamic Characteristics and Flap Loads of the Brake-Flap Installation on the 0.40-Scale Model of the F4F-3 Left Wing Panel" src="https://digital.library.unt.edu/ark:/67531/metadc61360/small/"/></a></p><p>"The data are presented in coefficient form and include lift, drag, and pitching-moment coefficients of the airfoil-flap comoinations and the normal-force, chord-force, and hinge-moment coefficients of the upper (perforated split) flap and lower (slotted) flap" (p. 1).</p>Aerodynamic Characteristics for Internal-Balance and Frise Type Ailerons on an NACA 6 Series Low-Drag Tip Section of the Wing for the XP-63 Airplane2011-11-17T17:13:32-06:00https://digital.library.unt.edu/ark:/67531/metadc61354/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc61354/"><img alt="Aerodynamic Characteristics for Internal-Balance and Frise Type Ailerons on an NACA 6 Series Low-Drag Tip Section of the Wing for the XP-63 Airplane" title="Aerodynamic Characteristics for Internal-Balance and Frise Type Ailerons on an NACA 6 Series Low-Drag Tip Section of the Wing for the XP-63 Airplane" src="https://digital.library.unt.edu/ark:/67531/metadc61354/small/"/></a></p><p>Report presenting testing in the two-dimensional turbulence tunnel of a model of the tip section of the wing of the XP-63 airplane. Several alterations of the skirts and balance on the internal-balance aileron were tested to obtain various aerodynamic characteristics of the aileron.</p>Aerodynamic Characteristics of a 1/8-Scale Powered Model of a High-Speed Bomber With a Dual Pusher Propeller Aft of the Empennage2011-11-17T17:13:32-06:00https://digital.library.unt.edu/ark:/67531/metadc61201/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc61201/"><img alt="Aerodynamic Characteristics of a 1/8-Scale Powered Model of a High-Speed Bomber With a Dual Pusher Propeller Aft of the Empennage" title="Aerodynamic Characteristics of a 1/8-Scale Powered Model of a High-Speed Bomber With a Dual Pusher Propeller Aft of the Empennage" src="https://digital.library.unt.edu/ark:/67531/metadc61201/small/"/></a></p><p>Report presenting wind-tunnel tests made to determine the aerodynamic characteristics of a scale model of a high-speed bomber with a dual pusher propeller aft of the empennage. Some of the results discussed include longitudinal, lateral, and directional stability and control, the empennage design, and ground effects on the aerodynamic characteristics. The results indicate that this particular airplane has several advantages with regard to stability and control over the conventional-type single-engine airplane configuration.</p>Aerodynamic Characteristics of Four Republic Airfoil Sections from Tests in Langley Two-Dimensional Low-Turbulence Tunnels2011-11-17T17:13:32-06:00https://digital.library.unt.edu/ark:/67531/metadc64938/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc64938/"><img alt="Aerodynamic Characteristics of Four Republic Airfoil Sections from Tests in Langley Two-Dimensional Low-Turbulence Tunnels" title="Aerodynamic Characteristics of Four Republic Airfoil Sections from Tests in Langley Two-Dimensional Low-Turbulence Tunnels" src="https://digital.library.unt.edu/ark:/67531/metadc64938/small/"/></a></p><p>"Four airfoils sections, designed by the Republic Aviation Corporation for the root and tip sections of the XF-12 airplane, were tested in the Langley two-dimensional low-turbulence tunnels to obtain their aerodynamic characteristics. Lift characteristics were obtained at Reynolds numbers of 3,000,000, 6,000,000, 9,000,000, and 14,000,000, whereas drag characteristics were obtained at Reynolds numbers of 3,000,000, 6,000,000, and 9,000,000. Pressure distributions were obtained for one of the root sections for several angles of attack at a Reynolds number of 2,600,000" (p. 1).</p>Aerodynamic Characteristics of Several Modifications of a 0.45-Scale Model of the Vertical Tail of the Curtiss XP-62 Airplane2011-11-17T17:13:32-06:00https://digital.library.unt.edu/ark:/67531/metadc62683/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc62683/"><img alt="Aerodynamic Characteristics of Several Modifications of a 0.45-Scale Model of the Vertical Tail of the Curtiss XP-62 Airplane" title="Aerodynamic Characteristics of Several Modifications of a 0.45-Scale Model of the Vertical Tail of the Curtiss XP-62 Airplane" src="https://digital.library.unt.edu/ark:/67531/metadc62683/small/"/></a></p><p>"In the course of an investigation to find a satisfactory vertical tail for the XP-62 airplane, a 0.45-scale vertical tail model on a stub fuselage was tested in the Langley 7- by 10-foot tunnel. This model was fitted with a flat plate to represent the horizontal tail surface. The data are presented herein for their general interest value rather than their application to this particular airplane" (p. 1).</p>Aerodynamic Data for a Wing Section of the Republic XF-12 Airplane Equipped With a Double Slotted Flap2011-11-17T17:13:32-06:00https://digital.library.unt.edu/ark:/67531/metadc61451/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc61451/"><img alt="Aerodynamic Data for a Wing Section of the Republic XF-12 Airplane Equipped With a Double Slotted Flap" title="Aerodynamic Data for a Wing Section of the Republic XF-12 Airplane Equipped With a Double Slotted Flap" src="https://digital.library.unt.edu/ark:/67531/metadc61451/small/"/></a></p><p>Report presenting an investigation in the two-dimensional low-turbulence tunnels for the purpose of developing an optimum flap configuration for maximum lift on an airfoil section for the Republic XF-12 airplane equipped with a double slotted flap. Lift and flap loads were obtained at several flap deflections for two flap paths. Results regarding lift, drag, and flap loads are provided.</p>Aerodynamic Tests of an A-M-65-AZON 1000-Pound Radio-Controlled Bomb in the LMAL 16-Foot High-Speed Tunnel2011-11-17T17:13:32-06:00https://digital.library.unt.edu/ark:/67531/metadc62572/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc62572/"><img alt="Aerodynamic Tests of an A-M-65-AZON 1000-Pound Radio-Controlled Bomb in the LMAL 16-Foot High-Speed Tunnel" title="Aerodynamic Tests of an A-M-65-AZON 1000-Pound Radio-Controlled Bomb in the LMAL 16-Foot High-Speed Tunnel" src="https://digital.library.unt.edu/ark:/67531/metadc62572/small/"/></a></p><p>Report presenting tests made in the LMAL 16-foot high-speed tunnel to determine the aerodynamic characteristics of a 1000-pound AN-M-65-AZON radio-controlled bomb at a Mach number range of 0.2 to 0.6. Over the Mach number range, the hinge-moment coefficients, yawing-moment coefficients, and lateral-force coefficients exhibited no important changes with increasing speed.</p>Aerodynamic Tests of an M-31 Bomb in the 8-Foot High-Speed Tunnel2011-11-17T17:13:32-06:00https://digital.library.unt.edu/ark:/67531/metadc62440/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc62440/"><img alt="Aerodynamic Tests of an M-31 Bomb in the 8-Foot High-Speed Tunnel" title="Aerodynamic Tests of an M-31 Bomb in the 8-Foot High-Speed Tunnel" src="https://digital.library.unt.edu/ark:/67531/metadc62440/small/"/></a></p><p>Report presenting aerodynamic tests of a 300-pound M-31 demolition bomb. Force tests at a range of angles of attack were made at Mach number 0.725, which corresponds to a speed of 810 feet per second at sea level. Results regard the drag, lift, and pitching moment are provided.</p>Aerodynamic Tests of an NACA 66(215)-116, a=0.6 Airfoil With a 0.25c Slotted Flap for the Fleetwings XA-39 Airplane2011-11-17T17:13:32-06:00https://digital.library.unt.edu/ark:/67531/metadc61411/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc61411/"><img alt="Aerodynamic Tests of an NACA 66(215)-116, a=0.6 Airfoil With a 0.25c Slotted Flap for the Fleetwings XA-39 Airplane" title="Aerodynamic Tests of an NACA 66(215)-116, a=0.6 Airfoil With a 0.25c Slotted Flap for the Fleetwings XA-39 Airplane" src="https://digital.library.unt.edu/ark:/67531/metadc61411/small/"/></a></p><p>Report presenting testing in the two-dimensional low-turbulence tunnels on a 24-inch-chord model of the NACA 66(215)-116 a = 0.6 airfoil with a 0.25-chord slotted flap. The optimum flap pivot positions were found for three different conditions. The conditions were determined from a consideration of the landing, take-off, and strafing requirements of the airplane.</p>The Aerodynamic Tests of Three Edo Floats for the SB2U-3, 0S2U-2, and XSB2C-2 Seaplanes - NACA Models 106-K, 107-K, and 125-AH2011-11-17T17:13:32-06:00https://digital.library.unt.edu/ark:/67531/metadc61712/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc61712/"><img alt="The Aerodynamic Tests of Three Edo Floats for the SB2U-3, 0S2U-2, and XSB2C-2 Seaplanes - NACA Models 106-K, 107-K, and 125-AH" title="The Aerodynamic Tests of Three Edo Floats for the SB2U-3, 0S2U-2, and XSB2C-2 Seaplanes - NACA Models 106-K, 107-K, and 125-AH" src="https://digital.library.unt.edu/ark:/67531/metadc61712/small/"/></a></p><p>Report presenting aerodynamic testing of scale models of the Edo seaplane floats for the SB2U-3, OS2U-2, and XSB2C-2 seaplanes. Various coefficients, pitching moment, yawing moment, and drag coefficients are provided.</p>Aerodynamics of the carburetor air scoop and the engine cowling of a single-engine torpedo-bomber-type airplane2011-11-17T17:13:32-06:00https://digital.library.unt.edu/ark:/67531/metadc62050/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc62050/"><img alt="Aerodynamics of the carburetor air scoop and the engine cowling of a single-engine torpedo-bomber-type airplane" title="Aerodynamics of the carburetor air scoop and the engine cowling of a single-engine torpedo-bomber-type airplane" src="https://digital.library.unt.edu/ark:/67531/metadc62050/small/"/></a></p><p>From Introduction: "An investigation of the power-plant installation of a single-engine torpedo-bomber-type airplane has been conducted in the NACA Cleveland altitude wind tunnel at the request of the Bureau of Aeronautics, Navy Department. A similar investigation was previously conducted on a three-tenths scale mock-up of the forward portion of the fuselage of this airplane in the Langley 20-foot tunnel. (See reference 1)."</p>Air-Flow and Performance Characteristics of Engine-Stage Supercharger of a Double-Row Radial Aircraft Engine 2: Effect of Design Variables2011-11-17T17:13:32-06:00https://digital.library.unt.edu/ark:/67531/metadc62038/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc62038/"><img alt="Air-Flow and Performance Characteristics of Engine-Stage Supercharger of a Double-Row Radial Aircraft Engine 2: Effect of Design Variables" title="Air-Flow and Performance Characteristics of Engine-Stage Supercharger of a Double-Row Radial Aircraft Engine 2: Effect of Design Variables" src="https://digital.library.unt.edu/ark:/67531/metadc62038/small/"/></a></p><p>Report presenting an investigation to determine the effect of the location of the diffuser vanes with respect to the supercharger outlets and the effect of flow conditions at the impeller inlet on the air-flow distribution in the outlets of the engine-stage supercharger of an 18-cylinder double-row radial aircraft engine. The effect of flow conditions at the impeller inlet was investigated by distorting the flow at the inlet and noting the effect in the supercharger outlets. Results regarding the diffuser effect and inlet effect are provided.</p>Air-flow and performance characteristics of the engine-stage supercharger of a double-row radial aircraft engine I: effect of operating variables2011-11-17T17:13:32-06:00https://digital.library.unt.edu/ark:/67531/metadc62036/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc62036/"><img alt="Air-flow and performance characteristics of the engine-stage supercharger of a double-row radial aircraft engine I: effect of operating variables" title="Air-flow and performance characteristics of the engine-stage supercharger of a double-row radial aircraft engine I: effect of operating variables" src="https://digital.library.unt.edu/ark:/67531/metadc62036/small/"/></a></p><p>From Introduction: "The tests reported herein, conducted during the early part of 1945, were made to determine the inherent charge-air distribution characteristics of the engine-stage supercharger of the double-row radial engine."</p>Airfoil Section Data From Tests of 10 Practical-Construction Sections of Helicopter Rotor Blades Submitted by the Sikorsky Aircraft Division, United Aircraft Corporation2011-11-17T17:13:32-06:00https://digital.library.unt.edu/ark:/67531/metadc61461/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc61461/"><img alt="Airfoil Section Data From Tests of 10 Practical-Construction Sections of Helicopter Rotor Blades Submitted by the Sikorsky Aircraft Division, United Aircraft Corporation" title="Airfoil Section Data From Tests of 10 Practical-Construction Sections of Helicopter Rotor Blades Submitted by the Sikorsky Aircraft Division, United Aircraft Corporation" src="https://digital.library.unt.edu/ark:/67531/metadc61461/small/"/></a></p><p>Report presenting 10 practical-construction models of sections of helicopter rotor blades tested in the NACA two-dimensional low-turbulence pressure tunnel at atmospheric pressure. Lift, drag, and pitching-moment characteristics of blades representing the present method of construction of the YR-4A helicopter were determined.</p>Altitude-wind-tunnel tests of power-plant installation in jet-propelled fighter2011-11-17T17:13:32-06:00https://digital.library.unt.edu/ark:/67531/metadc61183/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc61183/"><img alt="Altitude-wind-tunnel tests of power-plant installation in jet-propelled fighter" title="Altitude-wind-tunnel tests of power-plant installation in jet-propelled fighter" src="https://digital.library.unt.edu/ark:/67531/metadc61183/small/"/></a></p><p>From Introduction: "The research program included clean-up tests (unpublished data) and stability and control tests (reference 1) made in the NACA Langley full-scale tunnel. An investigation of the aerodynamic characteristics of the power-plant installation in the Cleveland altitude wind tunnel is discussed in this report."</p>Analysis and Correlation of Data Obtained by Six Laboratories on Fuel-Vapor Loss From Fuel Tanks During Simulated Flight2011-11-17T17:13:32-06:00https://digital.library.unt.edu/ark:/67531/metadc62280/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc62280/"><img alt="Analysis and Correlation of Data Obtained by Six Laboratories on Fuel-Vapor Loss From Fuel Tanks During Simulated Flight" title="Analysis and Correlation of Data Obtained by Six Laboratories on Fuel-Vapor Loss From Fuel Tanks During Simulated Flight" src="https://digital.library.unt.edu/ark:/67531/metadc62280/small/"/></a></p><p>Report presenting an analysis of data on fuel-vapor loss from fuel tanks during simulated flight obtained by six laboratories to show the effects of individual variables such as altitude, initial fuel temperature, rate of climb, booster-pump agitation, fuel depth, fuel-surface area, types of fuel, and vent-line pressure drop on fuel-vapor loss.</p>An analysis of the indications of the University of Chicago airborne turbulence indicator in gusty air2011-11-17T17:13:32-06:00https://digital.library.unt.edu/ark:/67531/metadc62668/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc62668/"><img alt="An analysis of the indications of the University of Chicago airborne turbulence indicator in gusty air" title="An analysis of the indications of the University of Chicago airborne turbulence indicator in gusty air" src="https://digital.library.unt.edu/ark:/67531/metadc62668/small/"/></a></p><p>From Introduction: "The present report has been prepared to discuss the indications obtained from the University of Chicago turbulence indicator in relation to simultaneous measurement of atmospheric gustiness made by the NACA, which are summarized herein."</p>Analysis of V-G Records from the SNB-1 Airplane2011-11-17T17:13:32-06:00https://digital.library.unt.edu/ark:/67531/metadc62643/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc62643/"><img alt="Analysis of V-G Records from the SNB-1 Airplane" title="Analysis of V-G Records from the SNB-1 Airplane" src="https://digital.library.unt.edu/ark:/67531/metadc62643/small/"/></a></p><p>Availability data obtained on SNB-1 trainer-class airplanes were analyzed and results presented as flight envelopes which predict occurrences of large values of air speed and acceleration. Comparison is made with SNJ-4 trainer-class airplane data analyzed by the same method. It is concluded that flight envelopes are satisfactory; that the two types show large differences in flight loads and speeds experience; and that SNB-1 will seldom, if ever, exceed design limit load factor and restricted speed, which SNJ-4 can be expected to exceed design-limit load factor and restricted speed in a very small number of flight hours.</p>Analysis of V-G Records From the SNJ-4 Airplane2011-11-17T17:13:32-06:00https://digital.library.unt.edu/ark:/67531/metadc62613/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc62613/"><img alt="Analysis of V-G Records From the SNJ-4 Airplane" title="Analysis of V-G Records From the SNJ-4 Airplane" src="https://digital.library.unt.edu/ark:/67531/metadc62613/small/"/></a></p><p>Report discusses an attempt to adapt a method of analysis of V-G data to predict the occurrences of large values of airspeed and acceleration from an SNJ-4 airplane; the data are presented as "flight envelopes". The flight envelopes "predict that, on average, in a stated number of flight hours, one airspeed, one positive acceleration, and one negative acceleration will exceed the envelope with equal probability of the accelerations being experienced at any airspeed" (from Discussion). The analysis method shows promise for predicting flight loads and speeds for airplanes on which loads due to maneuvers predominate.</p>Analytical investigation of the stability of an F8F dropping model with automatic stabilization2011-11-17T17:13:32-06:00https://digital.library.unt.edu/ark:/67531/metadc61655/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc61655/"><img alt="Analytical investigation of the stability of an F8F dropping model with automatic stabilization" title="Analytical investigation of the stability of an F8F dropping model with automatic stabilization" src="https://digital.library.unt.edu/ark:/67531/metadc61655/small/"/></a></p><p>From Introduction: "All results are presented in the form of motions following abrupt displacements of fixed magnitude - 20^o in bank and 15^o in pitch and yaw - from the reference attitude."</p>Antiknock Effectiveness of Xylidines in Small-Scale Engines2011-11-17T17:13:32-06:00https://digital.library.unt.edu/ark:/67531/metadc62346/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc62346/"><img alt="Antiknock Effectiveness of Xylidines in Small-Scale Engines" title="Antiknock Effectiveness of Xylidines in Small-Scale Engines" src="https://digital.library.unt.edu/ark:/67531/metadc62346/small/"/></a></p><p>"The data presented in this report are part of a general program to determine the effects of xylidines on the knock-limited performance of currently used aviation fuels" (p. 2).</p>Attainment of a Straight-Line Trajectory for a Preset Guided Missile With Special Reference to Effect of Wind or Target Motion2011-11-17T17:13:32-06:00https://digital.library.unt.edu/ark:/67531/metadc62433/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc62433/"><img alt="Attainment of a Straight-Line Trajectory for a Preset Guided Missile With Special Reference to Effect of Wind or Target Motion" title="Attainment of a Straight-Line Trajectory for a Preset Guided Missile With Special Reference to Effect of Wind or Target Motion" src="https://digital.library.unt.edu/ark:/67531/metadc62433/small/"/></a></p><p>Report discusses the results of a study "of the requirements for the attainment of a straight-line trajectory for a preset guided missile in the presence of wind or target motion" (from Summary). Information about the straight-line trajectory, position of the launching airplane, straight-line collision course, and arrangement of the autopilot in the missile is provided. Recommendations are also made about the creation of a bombsight mounting for the pilot of the launching airplane in order to attain the desired straight-line collision course.</p>Bending and Shear Stresses Developed by the Instantaneous Arrest of the Root of a Cantilever Beam With a Mass at Its Tip2011-11-17T17:13:32-06:00https://digital.library.unt.edu/ark:/67531/metadc62215/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc62215/"><img alt="Bending and Shear Stresses Developed by the Instantaneous Arrest of the Root of a Cantilever Beam With a Mass at Its Tip" title="Bending and Shear Stresses Developed by the Instantaneous Arrest of the Root of a Cantilever Beam With a Mass at Its Tip" src="https://digital.library.unt.edu/ark:/67531/metadc62215/small/"/></a></p><p>Report discusses an investigation into the behavior of a cantilever beam in transverse motion with a mass at its tip when the root is suddenly brought to rest. Equations for determining the stresses, deflections, and accelerations that arise in the beam are also provided. This testing can be applied to the shock created in an airplane when landing and the vibrations that result.</p>Calculation of the Aileron and Elevator Stick Forces and Rudder Pedal Forces for the Bell XP-83 Airplane (Project MX-511) in Spins2011-11-17T17:13:32-06:00https://digital.library.unt.edu/ark:/67531/metadc61570/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc61570/"><img alt="Calculation of the Aileron and Elevator Stick Forces and Rudder Pedal Forces for the Bell XP-83 Airplane (Project MX-511) in Spins" title="Calculation of the Aileron and Elevator Stick Forces and Rudder Pedal Forces for the Bell XP-83 Airplane (Project MX-511) in Spins" src="https://digital.library.unt.edu/ark:/67531/metadc61570/small/"/></a></p><p>"Aileron and elevator stick forces and rudder pedal forces for the Bell XP-83 airplane in spins have been calculated. The results indicate that the aileron and elevator stick forces may be excessive unless some suitable booster or more highly balanced control surfaces are used. The pilot will be able to move the surfaces only slightly from their normal floating locations" (p. 1).</p>Calibrations of Service Pitot Tubes in the Langley 24-Inch High-Speed Tunnel2011-11-17T17:13:32-06:00https://digital.library.unt.edu/ark:/67531/metadc62408/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc62408/"><img alt="Calibrations of Service Pitot Tubes in the Langley 24-Inch High-Speed Tunnel" title="Calibrations of Service Pitot Tubes in the Langley 24-Inch High-Speed Tunnel" src="https://digital.library.unt.edu/ark:/67531/metadc62408/small/"/></a></p><p>Report discusses calibration testing performed on a Kollsman type G-1 and an NAF No. 1 pitot tube at several Mach numbers and angles of attack. The effect of drain holes on the flow within the pitot tube was analyzed and the ability to estimate the error in the total pressure was created. The accuracy of the extrapolated and estimated values were found to be within reasonable limits.</p>Characteristics of Several Single- and Dual-Rotating Propellers in Negative Thrust2011-11-17T17:13:32-06:00https://digital.library.unt.edu/ark:/67531/metadc62187/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc62187/"><img alt="Characteristics of Several Single- and Dual-Rotating Propellers in Negative Thrust" title="Characteristics of Several Single- and Dual-Rotating Propellers in Negative Thrust" src="https://digital.library.unt.edu/ark:/67531/metadc62187/small/"/></a></p><p>Report discusses the thrust and power characteristics of several single- and dual-rotating propellers with differing blade width and number of blades for negative-thrust operation from -45 degrees to 145 degrees blade angle. From Summary: "The tests indicate that it is possible to predict for a given propeller design characteristics in the negative-thrust range from known characteristics at a different activity factor. Adequate negative thrusts were indicated for extremely high positive as well as negative blade angles."</p>Characteristics of the BMW 801D2 Automatic Engine Control as Determined From Bench Tests2011-11-17T17:13:32-06:00https://digital.library.unt.edu/ark:/67531/metadc62109/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc62109/"><img alt="Characteristics of the BMW 801D2 Automatic Engine Control as Determined From Bench Tests" title="Characteristics of the BMW 801D2 Automatic Engine Control as Determined From Bench Tests" src="https://digital.library.unt.edu/ark:/67531/metadc62109/small/"/></a></p><p>Report discusses the results of bench testing on a German BMW 301D2 to determine the relation between the control parameters and any special methods by which the control principles are adapted to the control of the engine. Characteristics are presented for a variety of simulated manifold pressures, charge-air temperatures, engine speeds, and altitudes. Special attention is paid to the pressure characteristics of the servo-oil system and the potential effects of its failure on the operation of the automatic engine-control system.</p>Charts Showing Stability and Control Characteristics of Airplanes in Flight2011-11-17T17:13:32-06:00https://digital.library.unt.edu/ark:/67531/metadc60953/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc60953/"><img alt="Charts Showing Stability and Control Characteristics of Airplanes in Flight" title="Charts Showing Stability and Control Characteristics of Airplanes in Flight" src="https://digital.library.unt.edu/ark:/67531/metadc60953/small/"/></a></p><p>Report presents a series of charts used to demonstrate typical good and undesirable airplane characteristics as determined in flight that were used to facilitate discussion at a series of conferences between the National Advisory Committee, Army, Navy, and representatives of the aircraft industry. For each chart, the purpose of the test, the flight technique used, the items recorded, and the evaluation and interpretation of the data obtained were provided. Additional figures drawn on the board during the conferences are not reproduced in the report.</p>Comparison of free-spinning wind-tunnel results with corresponding full-scale spin results2011-11-17T17:13:32-06:00https://digital.library.unt.edu/ark:/67531/metadc61109/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc61109/"><img alt="Comparison of free-spinning wind-tunnel results with corresponding full-scale spin results" title="Comparison of free-spinning wind-tunnel results with corresponding full-scale spin results" src="https://digital.library.unt.edu/ark:/67531/metadc61109/small/"/></a></p><p>Report presenting a study of comparable information on full-scale spinning results and NACA free-spinning wind-tunnel results in order to determine the degree of reliability of tunnel results in predicting the spinning behavior of airplanes. Satisfactory agreement between model and airplane was found in 16 instances and disagreement was found in 5 instances.</p>Comparison of Predicted and Actual Control-Fixed Stability and Control Characteristics of a Douglas A-26B Airplane2011-11-17T17:13:32-06:00https://digital.library.unt.edu/ark:/67531/metadc61056/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc61056/"><img alt="Comparison of Predicted and Actual Control-Fixed Stability and Control Characteristics of a Douglas A-26B Airplane" title="Comparison of Predicted and Actual Control-Fixed Stability and Control Characteristics of a Douglas A-26B Airplane" src="https://digital.library.unt.edu/ark:/67531/metadc61056/small/"/></a></p><p>Report presents a comparison of predicted qualities of the A-26B airplane with actual flying qualities determined in testing. From Summary: "The results indicate that the control-fixed, power-off stability and control characteristics of a conventional airplane can be predicted from the dimensions of the airplane and from general wind-tunnel data now available with sufficient accuracy for design purposes. No estimate of control forces, of effects of power on stability, or of adverse aileron yaw has been made."</p>Comparison of the compressive strength of panels with Alclad 24S-T81 sheet or with Alclad 24S-T86 sheet riveted to Alclad 24S-T84 hat-section stiffeners2011-11-17T17:13:32-06:00https://digital.library.unt.edu/ark:/67531/metadc60919/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc60919/"><img alt="Comparison of the compressive strength of panels with Alclad 24S-T81 sheet or with Alclad 24S-T86 sheet riveted to Alclad 24S-T84 hat-section stiffeners" title="Comparison of the compressive strength of panels with Alclad 24S-T81 sheet or with Alclad 24S-T86 sheet riveted to Alclad 24S-T84 hat-section stiffeners" src="https://digital.library.unt.edu/ark:/67531/metadc60919/small/"/></a></p><p>From Summary: "Compression tests were made of two groups of panel specimens with hat-section stiffeners. The groups were identical except that the flat sheet of one group was Alclad 24S-T81 and of the other Alclad 24S-T86. Results of the tests are given in tables or charts which show the average stress at which the sheet buckles and the average stress at the maximum load."</p>Comparison of the Knock-Limited Performance of Triptane With 23 Other Purified Hydrocarbons2011-11-17T17:13:32-06:00https://digital.library.unt.edu/ark:/67531/metadc62298/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc62298/"><img alt="Comparison of the Knock-Limited Performance of Triptane With 23 Other Purified Hydrocarbons" title="Comparison of the Knock-Limited Performance of Triptane With 23 Other Purified Hydrocarbons" src="https://digital.library.unt.edu/ark:/67531/metadc62298/small/"/></a></p><p>"The knock-limited performance of blends containing General Motors triptane in S reference fuel and in an S plus M base fuel was determined in 17.6, F-3, F-4, and full-scale (single cylinder) engines. The results obtained are presented and are compared with published data from similar tests of 12 aromatics, 10 paraffins (including highly purified triptane), and 2 olefins. The comparison of fuels - which is based on a consideration of (a) antiknock blending sensitivity, (b) lead susceptibility, (c) temperature sensitivity, and (d) comparison of small-scale and full-scale engine data - is presented by means of bar graphs" (p. 1).</p>A comparison of three spinner-diffuser designs in an NACA D(sub S) cowling for the Pratt & Whitney R-2800 engine2011-11-17T17:13:32-06:00https://digital.library.unt.edu/ark:/67531/metadc62100/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc62100/"><img alt="A comparison of three spinner-diffuser designs in an NACA D(sub S) cowling for the Pratt & Whitney R-2800 engine" title="A comparison of three spinner-diffuser designs in an NACA D(sub S) cowling for the Pratt & Whitney R-2800 engine" src="https://digital.library.unt.edu/ark:/67531/metadc62100/small/"/></a></p><p>Report presenting testing to determine which of three spinner-diffuser designs on an NACA cowling was the most effective in cooling a Pratt & Whitney R-2800 engine installation. The results of pressure-distribution studies in front of and behind each bank of cylinders are presented for a wide range of propeller-operating conditions.</p>Compression Tests of Six Curved Paper-Base Plastic Panels With Outward-Acting Normal Pressure2011-11-17T17:13:32-06:00https://digital.library.unt.edu/ark:/67531/metadc60910/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc60910/"><img alt="Compression Tests of Six Curved Paper-Base Plastic Panels With Outward-Acting Normal Pressure" title="Compression Tests of Six Curved Paper-Base Plastic Panels With Outward-Acting Normal Pressure" src="https://digital.library.unt.edu/ark:/67531/metadc60910/small/"/></a></p><p>Report presenting results of compression tests of six paper-base plastic panels with outward-acting normal pressure. All panels failed by separation of the skin, either from the rib or from the stiffeners. Results regarding the introduction of air pressure and types of failures encountered are provided.</p>Compressive Strength of Corrugated-Sheet-Stiffened Panels for Consolidated XB-36 Airplane2011-11-17T17:13:32-06:00https://digital.library.unt.edu/ark:/67531/metadc62614/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc62614/"><img alt="Compressive Strength of Corrugated-Sheet-Stiffened Panels for Consolidated XB-36 Airplane" title="Compressive Strength of Corrugated-Sheet-Stiffened Panels for Consolidated XB-36 Airplane" src="https://digital.library.unt.edu/ark:/67531/metadc62614/small/"/></a></p><p>"Compression tests were made of 63 panels stiffened with corrugated sheet. The specimens were constructed from artificially aged alclad 24S-T aluminum alloy with minimum guaranteed yield strengths of 57 and 48 kips per square inch for the flat- and corrugated-sheet materials, respectively. Results of the tests are presented in charts which show the average stresses at the maximum load and at buckling of the sheet" (p. 1).</p>Control-Motion Studies of the PBM-3 Flying Boat in Abrupt Pull-Ups2011-11-17T17:13:32-06:00https://digital.library.unt.edu/ark:/67531/metadc60908/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc60908/"><img alt="Control-Motion Studies of the PBM-3 Flying Boat in Abrupt Pull-Ups" title="Control-Motion Studies of the PBM-3 Flying Boat in Abrupt Pull-Ups" src="https://digital.library.unt.edu/ark:/67531/metadc60908/small/"/></a></p><p>Report presenting a control-motion study in flight that is part of series covering a range of types and sizes of modern airplanes. This particular one involves the PBM-3 flying boat, which is equipped with a control mechanism typical of the cable-type systems in large transport, cargo, or bomber airplanes as well as those employed in flying boats. The elasticity of the elevator control system of the PBM-3 was such to limit the obtainable acceleration to about 3g for center-of-gravity positions in the usual operating range; that is, 26 to 30 percent mean aerodynamic chord, and for the range of airspeeds covered by the tests.</p>Control of Cylinder Temperatures by Thermostatically Operated Internal-Coolant Valves2011-11-17T17:13:32-06:00https://digital.library.unt.edu/ark:/67531/metadc61968/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc61968/"><img alt="Control of Cylinder Temperatures by Thermostatically Operated Internal-Coolant Valves" title="Control of Cylinder Temperatures by Thermostatically Operated Internal-Coolant Valves" src="https://digital.library.unt.edu/ark:/67531/metadc61968/small/"/></a></p><p>Report discusses the results of testing conducted to determine the performance of automatic, internal-coolant valves actuated by cylinder temperatures.The performance of the valves with respect to temperature sensitivity, rapidity of response, and hunting characteristics is described. The relative effects on cylinder performance obtained by internally supplying water and additional fuel were also examined.</p>A Cooling Correlation Equation for a Double-Row Radial Engine Based on the Temperature of the Exhaust-Valve Seat2011-11-17T17:13:32-06:00https://digital.library.unt.edu/ark:/67531/metadc62018/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc62018/"><img alt="A Cooling Correlation Equation for a Double-Row Radial Engine Based on the Temperature of the Exhaust-Valve Seat" title="A Cooling Correlation Equation for a Double-Row Radial Engine Based on the Temperature of the Exhaust-Valve Seat" src="https://digital.library.unt.edu/ark:/67531/metadc62018/small/"/></a></p><p>Report discussing a cooling-correlation equation based on the average temperature of exhaust-valve seats of a large double-row radial engine. From the equation, predicts can be made about the cooling-air pressure drop required to cool the critical region of engine cylinders. Using a modified carburetor to improve the fuel-air-ratio distribution to the cylinders increased the accuracy of the equation's predictions.</p>Cooling in Cruising Flight With Low Fuel-Air Ratios2011-11-17T17:13:32-06:00https://digital.library.unt.edu/ark:/67531/metadc61978/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc61978/"><img alt="Cooling in Cruising Flight With Low Fuel-Air Ratios" title="Cooling in Cruising Flight With Low Fuel-Air Ratios" src="https://digital.library.unt.edu/ark:/67531/metadc61978/small/"/></a></p><p>Report presenting testing of a Pratt & Whitney R-1830-43 engine mounted in a B-24D nacelle in the full-scale wind tunnel in order to investigation the potential improvements of fuel economy. Suggestions for improving the cruising power and cruising range by operating at specified fuel-air ratios are provided.</p>Cooling Investigation of a B-24D Engine-Nacelle Installation in the NACA Full-Scale Tunnel2011-11-17T17:13:32-06:00https://digital.library.unt.edu/ark:/67531/metadc62117/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc62117/"><img alt="Cooling Investigation of a B-24D Engine-Nacelle Installation in the NACA Full-Scale Tunnel" title="Cooling Investigation of a B-24D Engine-Nacelle Installation in the NACA Full-Scale Tunnel" src="https://digital.library.unt.edu/ark:/67531/metadc62117/small/"/></a></p><p>Report presenting an investigation conducted in the full-scale tunnel to determine methods of improving the cooling of the B-24D engine installation. The B-24D is a four-engine high-wing monoplane having a span of 110 feet, a wing area of 1048 square feet, and a gross weight of 56,000 pounds.</p>Cooling of a Double-Row Radial Engine by Water Injection to the Individual Cylinders2011-11-17T17:13:32-06:00https://digital.library.unt.edu/ark:/67531/metadc62015/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc62015/"><img alt="Cooling of a Double-Row Radial Engine by Water Injection to the Individual Cylinders" title="Cooling of a Double-Row Radial Engine by Water Injection to the Individual Cylinders" src="https://digital.library.unt.edu/ark:/67531/metadc62015/small/"/></a></p><p>"An injection system that supplies water to each cylinder of a double-row radial engine was tested...as part of a general investigation of the power-plant installation of a four-engine heavy bomber. The tests were conducted to determine the effectiveness of water injection in cooling the engine during take-off. The injection of 500 pounds of water at the take-off power condition reduced the maximum measured exhaust-valve-seat temperature 64 degrees Fahrenheit and the maximum spark-plug-gasket temperature 55 degrees Fahrenheit" (p. 1).</p>Cooling of Gas Turbines, 2, Effectiveness of Rim Cooling of Blades2011-11-17T17:13:32-06:00https://digital.library.unt.edu/ark:/67531/metadc65597/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc65597/"><img alt="Cooling of Gas Turbines, 2, Effectiveness of Rim Cooling of Blades" title="Cooling of Gas Turbines, 2, Effectiveness of Rim Cooling of Blades" src="https://digital.library.unt.edu/ark:/67531/metadc65597/small/"/></a></p><p>An analysis of rim cooling, which cools the blade by condition alone, was conducted. Gas temperatures ranged from 1300 degrees to 1900 degrees F and rim temperatures from 0 degrees to 1000 degrees F below gas temperatures. Results show that gas temperature increases up to 200 degrees F are permissible provided that the blades are cooled by 400 degrees to 500 degrees F below the gas temperature. Relatively small amounts of blade cooling, at constant gas temperature, give large increases in blade life. Dependence of rim cooling on heat-transfer coefficient, blade dimensions, and thermal conductivity is determined by a single parameter.</p>Correlation of Engine-Cooling Data2011-11-17T17:13:32-06:00https://digital.library.unt.edu/ark:/67531/metadc61958/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc61958/"><img alt="Correlation of Engine-Cooling Data" title="Correlation of Engine-Cooling Data" src="https://digital.library.unt.edu/ark:/67531/metadc61958/small/"/></a></p><p>Report discusses a method of correlating engine-cooling data and its application to a representative engine-cooling test. Considerations for the correlation method are given, but the application to specific engine-cooling problems should be simple and direct. Information about experimental procedure and an example with specific values are included.</p>Correlation of Mixture Temperature Data Obtained From Bare Intake-Manifold Thermocouples2011-11-17T17:13:32-06:00https://digital.library.unt.edu/ark:/67531/metadc61878/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc61878/"><img alt="Correlation of Mixture Temperature Data Obtained From Bare Intake-Manifold Thermocouples" title="Correlation of Mixture Temperature Data Obtained From Bare Intake-Manifold Thermocouples" src="https://digital.library.unt.edu/ark:/67531/metadc61878/small/"/></a></p><p>"A relatively simple equation has been found to express with fair accuracy, variation in manifold-charge temperature with charge in engine operating conditions. This equation and associated curves have been checked by multi cylinder-engine data, both test stand and flight, over a wide range of operating conditions. Average mixture temperatures, predicted by the equations of this report, agree reasonably well with results within the same range of carburetor-air temperatures from laboratories and test stands other than the NACA" (p. 1).</p>Correlation of the Characteristics of Single-Cylinder and Flight Engines in Tests of High-Performance Fuels in an Air-Cooled Engine 1 - Cooling Characteristics2011-11-17T17:13:32-06:00https://digital.library.unt.edu/ark:/67531/metadc62546/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc62546/"><img alt="Correlation of the Characteristics of Single-Cylinder and Flight Engines in Tests of High-Performance Fuels in an Air-Cooled Engine 1 - Cooling Characteristics" title="Correlation of the Characteristics of Single-Cylinder and Flight Engines in Tests of High-Performance Fuels in an Air-Cooled Engine 1 - Cooling Characteristics" src="https://digital.library.unt.edu/ark:/67531/metadc62546/small/"/></a></p><p>Variable charge-air flow, cooling-air pressure drop, and fuel-air ration investigations were conducted to determine the cooling characteristics of a full-scale air-cooled single cylinder on a CUE setup. The data are compared with similar data that were available for the same model multicylinder engine tested in flight in a four-engine airplane. The cylinder-head cooling correlations were the same for both the single-cylinder and the flight engine. The cooling correlations for the barrels differed slightly in that the barrel of the single-cylinder engine runs cooler than the barrel of te flight engine for the same head temperatures and engine conditions.</p>Correlation of the Characteristics of Single-Cylinder and Flight Engines in Tests of High-Performance Fuels in an Air-Cooled Engine 2 - Knock-Limited Charge-Air Flow and Cylinder Temperatures2011-11-17T17:13:32-06:00https://digital.library.unt.edu/ark:/67531/metadc62547/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc62547/"><img alt="Correlation of the Characteristics of Single-Cylinder and Flight Engines in Tests of High-Performance Fuels in an Air-Cooled Engine 2 - Knock-Limited Charge-Air Flow and Cylinder Temperatures" title="Correlation of the Characteristics of Single-Cylinder and Flight Engines in Tests of High-Performance Fuels in an Air-Cooled Engine 2 - Knock-Limited Charge-Air Flow and Cylinder Temperatures" src="https://digital.library.unt.edu/ark:/67531/metadc62547/small/"/></a></p><p>An investigation was conducted to correlate the knock limited performance of flight and single-cylinder engines under a variety of operating conditions.</p>