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

Description: Report presenting an investigation in the stability tunnel at low speed to determine the rolling characteristics at combined angles of attack and sideslip for a model of a fighter-type airplane with a 45 degree sweptback wing. Testing was performed with the original vertical tail and a vertical tail with a 27 percent larger exposed area. Results regarding the static longitudinal stability, directional stability, and effect of the different tails are presented.
Date: September 1, 1955
Creator: Jaquet, Byron M. & Fletcher, H. S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of a high-pressure-ratio eight-stage axial-flow research compressor with two transonic inlet stages 6: over-all performance, rotating stall, and blade vibration at low and intermediate compressor speeds

Description: Report presenting an investigation to determine the overall performance of the modified eight-stage axial-flow compressor with new fourth-stage stator blades as part of a study of the problems encountered in a high-pressure-ratio axial-flow compressor with transonic inlet stages. The performance of the compressor was determined over a range of weight flows at equivalent speeds from 30 to 100 percent of design speed.
Date: November 1, 1955
Creator: Standahar, Raymond M.; Hanson, Morgan P. & Geye, Richard P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Longitudinal Aerodynamic Characteristics at Transonic Speeds of a Complete Model With an Unswept Wing and a Sweptback Horizontal Tail at Two Vertical Locations

Description: Memorandum presenting an investigation to determine the static longitudinal stability contribution of a horizontal tail at two vertical locations behind a 4-percent-thick unswept-wing-fuselage combination at transonic speeds. The model used in tests is comprised of an unswept wing located in the midwing position on a body of revolution and a sweptback horizontal tail mounted on a vertical tail.
Date: September 1, 1955
Creator: Hieser, Gerald & Kudlacik, Louis
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Spark ignition of flowing gases 5: application of fuel-air-ratio and initial-temperature data to ignition theory

Description: Report presenting a study to show the effect of fuel-air ratio and initial temperature on spark-ignition energy and to apply the results to a previously developed theory of ignition. Results regarding initial-temperature effect and fuel-air-ratio effect are provided.
Date: November 1, 1955
Creator: Swett, Clyde C., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Hydrodynamic Pressure Distribution Obtained With a Streamline Body Equipped With Chine Strips

Description: Memorandum presenting an investigation to determine the nature of the pressure distribution and the order of magnitude of the pressures on a streamline body moving on a water surface. The body of revolution was equipped with chine strips and had a fineness ratio of 9. The results from the investigation indicate that there is a characteristic pattern of hydrodynamic pressure distribution for streamline bodies equipped with chine strips and moving on a water surface.
Date: September 1, 1955
Creator: Weinflash, Bernard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Comparative Dispersion Data From Ground-Launched 2.25-Inch Rockets Equipped With Cruciform and Monoplane Fins

Description: Report presenting testing of about 150 rounds of 2.25-inch subcaliber aircraft rockets equipped with standard cruiform fins and twisted monoplane fins. No significant difference in dispersion was observed for the different configurations of fins on the rockets. Results regarding the stability of the different types of rockets, and general characteristics of the flight paths are provided.
Date: November 1, 1955
Creator: Purser, Paul E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Low-Speed Wind-Tunnel Tests of a 1/8-Scale Model of the Bell D-188A VTOL Airplane

Description: Report discussing the results of an investigation to determine the low-speed power-off stability and control characteristics of a model of the Bell D-188A VTOL airplane. The static stability and control characteristics were generally satisfactory except above certain angles of attack and aileron effectiveness dropped off as the angle of attack was increased. Modifications for increasing the directional stability by altering the vertical tails are also described.
Date: August 1, 1958
Creator: McKinney, Marion O. & Smith, Charles C., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

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

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

Investigation of Power Requirements for Ice Prevention and Cyclical De-Icing of Inlet Guide Vanes with Internal Electric Heaters

Description: "An investigation was conducted to determine the electric power requirements necessary for ice protection of inlet guide vanes by continuous heating and by cyclical de-icing. Data are presented to show the effect of ambient-air temperature, liquid-water content, air velocity, heat-on period, and cycle times on the power requirements for these two methods of ice protection. The results showed that for a hypothetical engine using 28 inlet guide vanes under similar icing conditions, cyclical de-ic… more
Date: December 1, 1950
Creator: von Glahn, Uwe & Blatz, Robert E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Investigation of the Afterbody Pressure Distribution and Fin Loading Characteristics of a Specialized Store Configuration at Transonic Speeds

Description: Report presenting an investigation in the transonic pressure tunnel to determine the afterbody pressure distribution and fin loading characteristics of two configurations of the TX-21 special weapon. The only different in the two configurations was the nose contour, with one having a hemispherical-flat shape and one with a double-radius ogive-flat shape. Results regarding the pressure port, fin loads, and force measurements are provided.
Date: August 1, 1956
Creator: Henry, Beverly Z., Jr. & Braden, John A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Survey of Supersonic Inlets for High Mach Number Applications

Description: Report discussing various inlet design philosophies based on the results of testing at Mach numbers up to 5. The most ideal inlet design was found to be one with combined external-plus-internal compression due to problems noted with both external-only and internal-only inlets.
Date: April 1, 1958
Creator: Connors, James F. & Allen, John L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Performance of Several Half-Conical Side Inlets at Supersonic and Subsonic Speeds

Description: Report discussing an evaluation of a series of half-conical side inlets mounted on the fuselage of a supersonic aircraft at various Mach numbers. Information about the maximum total-pressure recovery, asymmetrical operation of the twin-duct system, potential reduction in stable mass-flow range, boundary-layer diverter height, and engine mass flow is described.
Date: February 1, 1956
Creator: Stitt, Leonard E.; Cubbison, Robert W. & Flaherty, Richard J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Afterburner Performance With Combustion-Chamber Lengths From 10 to 62 Inches at Several Afterburner-Inlet Temperatures

Description: Effect of variation of combustion chamber length and inlet temperature on low pressure-loss sea level afterburner. A 70-percentage-point reduction in combustion efficiency resulted when the combustion-chamber length was reduced from 62 to 10 inches.
Date: February 1, 1956
Creator: Ciepluch, Carl C.; Velie, Wallace W. & Burley, Richard R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Transonic Wind-Tunnel Investigation of the Performance and of the Static Stability and Control Characteristics of a 1/15-Scale Model of the Grumman F9F-9 Airplane, Ted No. NACA DE 390

Description: Report presenting an investigation of the aerodynamic characteristics of a model of the Grumman F9F-9 airplane in the transonic tunnel. Results regarding the transonic drag-rise increment, drag analysis, and effective downwash angle are provided.
Date: October 1, 1954
Creator: Bielat, Ralph P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Measurement of Static Forces on Internally Carried Bombs of Two Different Bluff Shapes in the Flow Field of a Swept-Wing Fighter-Bomber Configuration at a Mach Number of 1.6

Description: Report discussing the influence of forces and moments on a fighter-bomber airplane with an open bomb bay and on two bluff bomb shapes in various positions below the fuselage and plane of symmetry. The wing was found to have a noticeable effect on bomb forces and that bluff bombs affect the longitudinal characteristics of the wing-fuselage combination.
Date: April 1, 1957
Creator: Geier, Douglas J. & Robins, A. Warner
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

First Landing of Bell X-2 Research Airplane

Description: Report presenting testing regarding the Bell X-2 supersonic research airplane, which is equipped with a skid main landing gear and nose wheel, to determine the low-speed handling qualities and landing characteristics. Results regarding the landing approach pattern, time histories, and final resting position of the airplane at landing are provided.
Date: October 1, 1952
Creator: Day, Richard E. & Stillwell, Wendell H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Fuel investigation in a tubular-type combustor of a turbojet engine

Description: A series of 11 fuels ranging in volatility and including various types of hydrocarbons were tested in a single tubular combustion chamber of a turbojet engine under inlet-air conditions simulating engine operation at two speeds at an altitude of 40,000 feet. Temperature-rise data at various fuel-air ratios were obtained for each set of air-flow conditions. Results regarding the effect of combustor inlet-air conditions on temperature rise, four different series of tests, and a review of some gen… more
Date: August 1, 1947
Creator: Tischler, Adelbert O. & Dittrich, Ralph T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An empirically derived method for calculating pressure distribution at supercritical Mach numbers and moderate angles of attack

Description: Report presenting a procedure for calculating pressure distributions over airfoils at supercritical Mach numbers. Only the forward portion of the airfoil, where interaction between local boundary-layer thickness and local-pressure distribution is negligible, is considered in detail. The method cannot be considered definitive because it requires that certain characteristics regarding pressure distributions and geometric properties be known.
Date: April 1, 1947
Creator: Nitzberg, Gerald E. & Sluder, Loma E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

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

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

Reduction of profile drag at supersonic velocities by the use of airfoil sections having a blunt trailing edge

Description: Report presenting a preliminary theoretical and experimental investigation of the supersonic characteristics of blunt-trailing-edge airfoils. Results regarding the drag measurements at zero lift, measurements at angle of attack, and a general discussion of the theoretical and experimental results is provided.
Date: November 1, 1949
Creator: Chapman, Dean R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic Characteristics of a Wing With Quarter-Chord Line Swept Back 45 Degrees, Aspect Ratio 6, Taper Ratio 0.6, and NACA 65A006 Airfoil Section

Description: Report discussing a wing-alone and wing-fuselage configuration with particular characteristics as part of a series of tests of wings using the transonic-bump test technique. Lift, drag, pitching moment, and root bending moment were obtained for the configurations. The effective downwash angles and dynamic-pressure characteristics in the tail region are also described.
Date: November 1, 1949
Creator: Goodson, Kenneth W. & Few, Albert G., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of airfoil section and tip tanks on the aerodynamic characteristics at high subsonic speeds of an unswept wing of aspect ratio 5.16 and taper ratio 0.61

Description: Report presenting an investigation of the effect of two wing sections and a tip tank on the aerodynamic characteristics of a rigid unswept wing in the high-speed tunnel over a Mach number range of 0.60 to 0.90. Results regarding the effect of original airfoil sections, effect of modifications to Section B, effect of tip tank, and characteristics of the tip tank in the presence of the wing are provided.
Date: December 1, 1949
Creator: Silvers, H. Norman & Spreeman, Kenneth P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

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

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