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Experimental Investigation of Flutter and Divergence Characteristics of the Rocket-Motor Fin of the ASROC Missile

Description: Report presenting testing of models of rocket-motor fins of the ASROC missile for flutter and divergence in the supersonic flutter tunnel for a range of Mach numbers. Results indicate that both divergence of the overhung leading edge and flutter occur within the sea-level operating conditions of the missile at Mach numbers above 1.0. Results regarding the flutter boundary, type of flutter encountered, possible solutions to flutter problems, and possible effects of nondestructive type of flutter are provided.
Date: July 31, 1958
Creator: Levey, Gilbert M. & Hanson, Perry W.
Partner: UNT Libraries Government Documents Department
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An Investigation of the Longitudinal Stability and Afterbody Pressure Characteristics of Specialized Store Configurations at Transonic Speeds

Description: Report presenting an investigation to determine the longitudinal stability and afterbody pressure characteristics of the TX-14 and TX-16 special weapons at transonic and supersonic speeds. Results regarding dynamic testing and pressure testing are provided.
Date: March 31, 1954
Creator: Braden, John A. & Henry, Beverly Z., Jr.
Partner: UNT Libraries Government Documents Department
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Method for Estimating Lift Interference of Wing-Body Combinations at Supersonic Speeds

Description: Memorandum presenting the use of the modified slender-body method to predict the lift and moment interference of triangular wing-body combinations adapted to combinations with other than triangular wings. The methods are applied to the prediction of the lit-curve slopes of nearly 100 triangular, rectangular, and trapezoidal wing-body configurations.
Date: December 31, 1951
Creator: Nielsen, Jack N. & Kaattari, George E.
Partner: UNT Libraries Government Documents Department
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Effect of Nose Shape and Wing Thickness Ratio on the Drag at Zero Lift of a Missile Having Triangular Wings and Tails

Description: "Free-flight tests have been made to determine the drag at zero lift of several configurations of a missile having triangular wings and tails. Base-pressure measurements were also obtained for some of the configurations. The results show that increasing the wing thickness ratio from 4 to 6 percent increased the wing drag by about 100 percent at M = 1.3 and by about 30 percent at M = 1.8" (p. 1).
Date: May 31, 1950
Creator: Hall, James R. & Sandahl, Carl A.
Partner: UNT Libraries Government Documents Department
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Measurement of Static Forces on Externally Carried Bombs of Fineness Ratios 7.1 and 10.5 in the Flow Field of a Swept-Wing Fighter- Bomber Configuration at a Mach Number of 1.6

Description: Memorandum presenting forces and moments measured at Mach number 1.6 in the 4- by 4-foot supersonic pressure tunnel on bombs of fineness ratios 7.0 and 10.5 in the presence of a swept-wing fighter-bomber airplane configuration for a large number of positions under the fuselage. The results can be used to calculate bomb-drop paths.
Date: January 31, 1957
Creator: Geier, Douglas J. & Carlson, Harry W.
Partner: UNT Libraries Government Documents Department
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Free-jet performance of 16-inch ram-jet engine with several fuels

Description: Report presenting an investigation of several fuels in a 16-inch ramjet engine during a free-jet investigation of ramjet performance in a wind tunnel. The fuels used were gasoline, kerosene, blend of 50-percent gasoline and 50-percent propylene oxide, blend of 75-percent kerosene and 25-percent propylene oxide, and isopentane. Results regarding ranges of operation, combustion efficiencies, and weight and volume specific fuel consumptions obtained with various fuels.
Date: October 31, 1950
Creator: Wilcox, Fred A.
Partner: UNT Libraries Government Documents Department
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Investigation of a 1/5-scale model of a proposed high-submerged-speed submarine in the Langley full-scale tunnel

Description: Report presenting the results of an investigation to determine the drag, static stability, control effectiveness, boundary-layer conditions, and first-order effects of propeller operation on a scale model of a proposed high-submerged-speed submarine with various bridge-fairwater and tail configurations.
Date: October 31, 1950
Creator: Lipson, Stanley; Cocke, Bennie W. & Scallion, William I.
Partner: UNT Libraries Government Documents Department
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Application of blade cooling to gas turbines

Description: From Summary: "A review of the status of the knowledge on turbine-blade cooling and a description of pertinent NACA investigations are presented. The current limitations in performance of uncooled and cooled engines are briefly discussed. Finally, the knowledge available and investigations to increase the knowledge on heat transfer, cooling-flow, and performance characteristics of cooled turbines are discussed."
Date: May 31, 1950
Creator: Ellerbrock, Herman H., Jr. & Schafer, Louis J., Jr.
Partner: UNT Libraries Government Documents Department
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Experimental investigation of the effectiveness of various suction-slot arrangements as a means for increasing the maximum lift of the NACA 65(sub 3)-018 airfoil section

Description: Report presenting a wind-tunnel investigation to explore the possibility of employing boundary-layer suction slots as a means for delaying laminar separation at the leading edge and turbulent separation over the rear portions of the airfoil section at high lift coefficients. Results regarding lift and drag are explored.
Date: March 31, 1950
Creator: Racisz, Stanley F.
Partner: UNT Libraries Government Documents Department
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The effects of various parameters including Mach number on propeller blade flutter with emphasis on stall flutter

Description: Report presenting an investigation of the effects of many of the parameters significant to wing flutter on several untwisted rotating models to determine their significance with respect to stall flutter of propeller blades. The parameters included torsional stiffness, section thickness ratio, sweepback, length-chord ratio, section center-of-gravity location, blade taper, Mach number, and fluid density. Results regarding the considerations on method of presentation, experimental data and discussion, some possible applications, and a comparison of experiment with classical-flutter theory are provided.
Date: January 31, 1951
Creator: Baker, John E.
Partner: UNT Libraries Government Documents Department
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Measurements of average heat-transfer and friction coefficients for subsonic flow of air in smooth tubes at high surface and fluid temperatures

Description: An investigation of forced-convection heat transfer and associated pressure drops was conducted with air flowing through smooth tubes for an over-all range of surface temperature from 535 degrees to 3050 degrees r, inlet-air temperature from 535 degrees to 1500 degrees r, Reynolds number up to 500,000, exit Mach number up to 1, heat flux up to 150,000 btu per hour per square foot, length-diameter ratio from 30 to 120, and three entrance configurations. Most of the data are for heat addition to the air; a few results are included for cooling of the air. The over-all range of surface-to-air temperature ratio was from 0.46 to 3.5.
Date: December 31, 1950
Creator: Humble, Leroy V.; Lowdermilk, Warren H. & Desmon, Leland G.
Partner: UNT Libraries Government Documents Department
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Systematic two-dimensional cascade tests of NACA 65-series compressor blades at low speeds

Description: The performance of NACA 65-series compressor blade section in cascade has been investigated systematically in a low-speed cascade tunnel. Porous test-section side walls and for high-pressure-rise conditions, porous flexible end walls were employed to establish conditions closely simulating two-dimensional flow. Blade sections of design lift coefficients from 0 to 2.7 were tested over the usable angle-of-attack range for various combinations of inlet-flow angle. A sufficient number of combinations were tested to permit interpolation and extrapolation of the data to all conditions within the usual range of application. The results of this investigation indicate a continuous variation of blade-section performance as the major cascade parameters, blade camber, inlet angle, and solidity were varied over the test range. Summary curves of the results have been prepared to enable compressor designers to select the proper blade camber and angle of attack when the compressor velocity diagram and desired solidity have been determined.
Date: January 31, 1958
Creator: Emery, James C.; Herrig, L. Joseph; Erwin, John R. & Felix, A. Richard
Partner: UNT Libraries Government Documents Department
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A note on secondary flow in rotating radial channels

Description: "A general vector differential equation for the vorticity component parallel to a streamline is derived for steady, nonviscous, and incompressible flow in a rotating system. This equation is then simplified by restricting it to rotating radial channels and by making further simplifying assumptions. The simplified equation is used to solve for the secondary vorticity, the vorticity component parallel to the streamline, in three special cases involving different streamtube geometries; the results are presented in a series of figures" (p. 1).
Date: August 31, 1953
Creator: Kramer, James J. & Stanitz, John D.
Partner: UNT Libraries Government Documents Department
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Investigation to Determine the Effectiveness of a Split-Aileron Type Emergency Spin-Recovery Device for the Northrop XF-89 Airplane

Description: The present paper presents the results of a brief investigation made to determine the effectiveness of a proposed emergency spin-recovery device to be used during demonstration spins of the Northrop XF -89 airplane. The proposed device makes use of split-type ailerons deflected +/-60deg on the outboard wing (left wing in a right spin). Tests made on a model which represented the airplane to a scale of 7 indicated that, if an uncontrollable spin is obtained in the design gross--weight loading, the device is not sufficiently effective to insure recovery,.
Date: August 31, 1951
Creator: Neihouse, A. I. & Lee, H. A.
Partner: UNT Libraries Government Documents Department
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Theoretical Investigation of the Effects of the Artificial-Feel System on the Maneuvering Characteristics of the F-89 Airplane

Description: The possibility of overshooting the anticipated normal acceleration as a result of the artificial-feel characteristics of the F-89C airplane at a condition of minimum static stability was investigated analytically by means of an electronic simulator. Several methods of improving the stick-force characteristics were studied. It is shown that, due to the lag in build-up of the portion of the stick force introduced by the bobweight, it would be possible for excessive overshoots of normal acceleration to occur in abrupt maneuvers with reasonable assumed control movements. The addition of a transient stick force proportional to pitching acceleration (which leads the normal acceleration) to prevent this occurring would not be practical due to the introduction of an oscillatory mode to the stick-position response. A device to introduce a viscous damping force would Improve the stick-force characteristics so that normal acceleration overshoots would not be likely, and the variation of the maximum stick force in rapid pulse-type maneuvers with duration of the maneuver then would have a favorable trend.
Date: December 31, 1952
Creator: Abramovitz, Marvin; Schmidt, Stanley F. & Belsley, Steven E.
Partner: UNT Libraries Government Documents Department
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Rocket-Model Measurements of Zero-Lift Damping in Roll of the Bell MX-776 Missile at Mach Numbers from 0.6 to 1.56

Description: The zero-lift damping in roll of the Bell MX-776 missile has been measured by a sting-mounted rocket-model technique at Mach numbers from 0.6 to 1.56. The damping-in-roll data, in general, show no unusual variation with Mach number. Aileron rolling-moment effectiveness derived from these data and previously obtained rolling-effectiveness data appear reasonable,.
Date: December 31, 1953
Creator: Bland, William M., Jr. & Purser, Paul E.
Partner: UNT Libraries Government Documents Department
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Interim Report on Free-Spinning-Tunnel Investigation of a 1/25-Scale Model of the McDonnell F3H-1N Airplane, TED No. NACA AD 3100

Description: "An investigation was conducted in the Langley 20-foot free-spinning tunnel on a 1/23-scale model of the McDonnell F3H-1N airplane. The effects of control settings and movements upon the erect and inverted spin and recovery characteristics of the model were determined for the clean condition. Spin-recovery parachute tests were also performed. The results indicated that erect spins obtained on the airplane for the take-off or combat loadings should be satisfactorily terminated if full rudder reversal is accompanied by moving the ailerons to full with the spin (stick full right in a right spin)" (p. 1).
Date: December 31, 1954
Creator: Lee, Henry A. & Wilkes, L. Faye
Partner: UNT Libraries Government Documents Department
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Lift, Drag, Static Stability, and Buffet Boundaries of a Model of the McDonnell F3H-1N Airplane at Mach Numbers from 0.40 to 1.27, TED No. NACA DE 351

Description: "The National Advisory Committee for Aeronautics has conducted a flight test of a model approximating the McDonnell F3H-1N airplane configuration to determine its pitch-up and buffet boundaries, as well as the usual longitudinal stability derivatives obtainable from the pulsed- tail technique. The test was conducted by the freely flying rocket-boosted model technique developed at the Langley Laboratory; results were obtained at Mach numbers from 0.40 to 1.27 at corresponding Reynolds numbers of 2.6 x 10(exp 6) and 9.0 x 10(exp 6). The phenomena of pitch-up, buffet, and maximum lift were encountered at Mach numbers between 0.42 and 0.85" (p. 1).
Date: January 31, 1956
Creator: Crabill, Norman L.
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation at Low Speed of the Yawing Stability Derivatives of a 1/9-Scale Powered Model of the Convair XFY-1 Vertically Rising Airplane, TED No. NACA DE 373

Description: "An experimental investigation has been conducted in the Langley stability tunnel at low speed to deter+nine the yawing stability derivatives of a 1/9-scale powered model of the Convair XFY-1 vertically rising airplane. Effects of thrust coefficient were investigated for the complete model and for certain components of the model. Effects of control deflections and of propeller blade angle were investigated for the complete model" (p. 1).
Date: March 31, 1953
Creator: Queijo, M. J.; Wolhart, W. D. & Fletcher, H. S.
Partner: UNT Libraries Government Documents Department
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Effect of inlet oxygen concentration on combustion efficiency of J33 single combustor operating with gaseous propane

Description: Report presenting an investigation to determine the effect of oxygen concentration of the inlet oxygen-nitrogen mixture on the combustion efficiency of a J33 single combustor operating with gaseous propane fuel. Combustion efficiency data were obtained at a variety of combustion-inlet total pressures, fuel flow rates, and inlet oxygen concentrations. Results regarding combustor data, application of fundamental combustion properties to combustor data, application of simplified reaction kinetics equation to combustor data, comparison of liquid and gaseous fuel data, and limitations of correlation parameters.
Date: March 31, 1953
Creator: Graves, Charles C.
Partner: UNT Libraries Government Documents Department
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Pressure distribution and pressure drag for a hemispherical nose at Mach numbers 2.05, 2.54, and 3.04

Description: Report presenting an experimental investigation of the pressure distributions on a hemispherical nose 3.98 inches in diameter, mounted on a cylindrical support, at several Mach and Reynolds numbers. The Reynolds number was based on body diameter and free-stream conditions. Pressure-drag coefficients were calculated and good agreement was obtained with other testing.
Date: December 31, 1952
Creator: Chauvin, Leo T.
Partner: UNT Libraries Government Documents Department
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The effects of fences on the high-speed longitudinal stability of a swept-wing airplane

Description: Report presenting a series of fence installations tested on a swept-wing jet airplane to determine their effects on the longitudinal instability, or "pitch-up", encountered in high-maneuvering flight. Longitudinal-stability measurements were made at a variety of Mach numbers with nine fence configurations that varied in chordwise extent and spanwise position. Results regarding longitudinal stability, flow phenomena, buffeting and wing dropping, drag, and low-speed stalls are provided.
Date: August 31, 1953
Creator: Bray, Richard S.
Partner: UNT Libraries Government Documents Department
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Investigation of the NACA 1.167-(0)(03)-058 and NACA 1.167-(0)(05)-058 Three-Blade Propellers at Forward Mach Numbers to 0.92 Including Effects of Thrust-Axis Inclination

Description: Report presenting an investigation to determine the aerodynamic characteristics of two three-blade propellers over a range of blade angles and Mach numbers. The thick-blade propeller was more adversely affected by compressibility than the thin-blade propeller, and the maximum efficiency of the thin-blade propeller was higher than the thick-blade propeller.
Date: August 31, 1953
Creator: Demele, Fred A. & Otey, William R.
Partner: UNT Libraries Government Documents Department
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