Technical Report Archive & Image Library (TRAIL) - 1,263 Matching Results

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Aerodynamic Characteristics of a 1/8-Scale Powered Model of a High-Speed Bomber With a Dual Pusher Propeller Aft of the Empennage

Description: 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-… more
Date: October 12, 1945
Creator: Weiberg, James A. & Schnurbusch, Alfred W.
Partner: UNT Libraries Government Documents Department
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Flying Qualities of a High-Speed Bomber With a Dual Pusher Propeller Aft of the Empennage as Estimated From Wind-Tunnel Tests of a 1/8-Scale Powered Model

Description: Report discussing the flying qualities of a high-speed bomber with a dual pusher propeller aft of the empennage. The airplane was found to have satisfactory flying qualities except for stability issues with aft center of gravity, high elevator control forces in landing, insufficient elevator control in take-off, and low rudder-free directional stability.
Date: November 4, 1944
Creator: Weiberg, James A. & Schnurbusch, Alfred W.
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Tests of the 0.15-Scale Powered Model of the Fleetwings XBTK-1 Airplane: Longitudinal Stability and Control

Description: "An investigation was made of the static longitudinal stability, and control and stall characteristics of XBTK-1 dive bomber. Results indicate that the longitudinal stability will probably be satisfactory for all contemplated flight conditions at the rear-most CG location with elevator both fixed and free. Power effects were small. Sufficient elevator control will be available to trim in any flight condition above the ground" (p. 1).
Date: May 1945
Creator: Weil, Joseph & Boykin, Rebecca I.
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Tests of the 1/8-Scale Powered Model of the Curtiss XBTC-2 Airplane 1: Preliminary Investigation of Longitudinal Stability

Description: Report presenting a series of wind-tunnel tests made in the 7- by 10-foot tunnel of the Curtiss XBTC-2 model with power. The object of the tests was to determine and to improve, as necessary, the complete aerodynamic characteristics of the model. The report includes the results of the longitudinal stability investigation of the original model along with results from tests of various modifications.
Date: June 1944
Creator: Weil, Joseph & Wells, Evalyn G.
Partner: UNT Libraries Government Documents Department
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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

Description: 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."
Date: April 1944
Creator: Weinberger, Robert A.; Rossman, Carl A. & Fisher, Gordon P.
Partner: UNT Libraries Government Documents Department
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Compressive Strength of Corrugated-Sheet-Stiffened Panels for Consolidated XB-36 Airplane

Description: "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).
Date: January 1944
Creator: Weinberger, Robert A.; Sperry, William C. & Dobrowski, Charles V.
Partner: UNT Libraries Government Documents Department
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Flight and Test-Stand Investigation of High-Performance Fuels in Modified Double-Row Radial Air-Cooled Engines 1: Determination of the Cooling Characteristics of the Flight Engine

Description: Report discussing the cooling characteristics of a modified 14-cylinder double-row radial air-cooled engine installed in a four-engine airplane at a pressure altitude of 7000 feet. Testing of the variable charge-air flow, variable cooling-air pressure drop, and variable fuel-air ratio was conducted. The cooling equation, temperature-limited performance, maximum engine temperatures, and other information predicted by calculations is described.
Date: July 9, 1945
Creator: Werner, Milton; Blackman, Calvin C. & White, H. Jack
Partner: UNT Libraries Government Documents Department
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Pressure loss in ducts with compound elbows

Description: From Summary: "Results are presented of measurement of the pressure drop in ducts produced by two equal 90 degree elbows arranged at three different angular positions to each other, placed adjacent to each other, or separated by straight ducts of various lengths. The measured pressure drops have been analyzed and correlated, and the results are summarized in the form of curves adapted for design computations of pressure drop in compound-duct bends."
Date: February 1943
Creator: Weske, John R.
Partner: UNT Libraries Government Documents Department
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Accelerations Measured at Center of Gravity and Along Span of the Wing of a B-24D Airplane in Landing Impacts

Description: 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.
Date: August 1944
Creator: Westfall, John R.
Partner: UNT Libraries Government Documents Department
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Flight tests of F2A-2 airplane with full-span slotted flaps and trailing-edge and slot-lip ailerons

Description: Report presenting flight tests of a Navy F2A-2 specially equipped with full-scale slotted flaps and two sets of lateral controls: internally balanced, sealed ailerons on the flap trailing edge for use with the flaps up and slot lip ailerons for use with the flaps down. Results regarding aileron characteristics, maximum lift coefficients and stalling characteristics, and longitudinal stability and control are provided.
Date: December 1943
Creator: Wetmore, Joseph W.
Partner: UNT Libraries Government Documents Department
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The relation between spanwise variations in the critical Mach number and spanwise load distributions

Description: "Data are presented to show the changes that occur in the spanwise load distributions on wings when the critical Mach number is exceeded. The data indicate that the magnitude of the changes in spanwise load distribution varies with the magnitude of the spanwise variation in the critical Mach numbers of the sections. Means of reducing the magnitudes of such changes are considered" (p. 1).
Date: December 1944
Creator: Whitcomb, Richard T.
Partner: UNT Libraries Government Documents Department
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Physical Data on Certain Alloys for High Temperature Applications

Description: Report presenting data constituting a summary of the physical properties of 120 samples of metal alloys, representing 86 different compositions which have been investigated for their suitability as turbosupercharger wheel materials. Some of the reported data include the chemical composition, fabrication procedure, tensile-test and hardness values at room temperature, and tensile and rupture-test characteristics at 1200 degrees Fahrenheit.
Date: April 1943
Creator: White, A. E.; Freeman, J. W. & Rote, F. B.
Partner: UNT Libraries Government Documents Department
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Effect of Fuel Volatility on Performance of a Wright R-2600-8 Engine as Influenced by Mixture Distribution

Description: Report presenting an investigation to determine the effect of fuel volatility on engine power and economy as influenced by mixture distribution. Tests of four fuels of different volatility were conducted on a Wright R-2600-8 engine at desired cruising power, maximum cruising power, normal rated power, and takeoff power.
Date: September 1944
Creator: White, H. Jack & Engelman, Helmuth W.
Partner: UNT Libraries Government Documents Department
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Correlation of Mixture Temperature Data Obtained From Bare Intake-Manifold Thermocouples

Description: "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… more
Date: January 1946
Creator: White, H. Jack & Gammon, Goldie L.
Partner: UNT Libraries Government Documents Department
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Flight and Test-Stand Investigation of High-Performance Fuels in Double-Row Radial Air-Cooled Engines 3: Comparison of Cooling Characteristics of Flight and Test-Stand Engines

Description: Report presenting the cooling characteristics of a 14-cylinder double-row radial air-cooled engines in a test stand and in flight. Three types of cooling tests were made for both engines: variable charge-air flow, variable cooling-air pressure drop, and variable fuel-air ratio. For the same operating conditions, the test-stand engine was found to run consistently cooler than the flight engine.
Date: February 1945
Creator: White, H. Jack; Blackman, Calvin C. & Dandois, Marcel
Partner: UNT Libraries Government Documents Department
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Flight and Test-Stand Investigation of High-Performance Fuels in Double-Row Radial Air-Cooled Engines 2: Flight Knock Data and Comparison of Fuel Knock Limits With Engine Cooling Limits in Flight

Description: Report discussing a comparison of the antiknock characteristics of triptane with a temperature-sensitive blending agent and of the fuel knock limits with engine cooling limits. Estimates were also made of temperature-limited engine performance at several flight and engine conditions.
Date: December 30, 1944
Creator: White, H. Jack; Blackman, Calvin C. & Werner, Milton
Partner: UNT Libraries Government Documents Department
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Flight and Test-Stand Investigation of High-Performance Fuels in Modified Double-Row Radial Air-Cooled Engines 2: Flight Knock Data and Comparison of Fuel Knock Limits With Engine Cooling Limits in Flight

Description: Report discussing tests on three fuels in a 14-cylinder double-row radial air-cooled engine at different engine speeds, blower ratios, and spark settings.
Date: August 4, 1945
Creator: White, H. Jack; Pragliola, Philip C. & Blackman, Calvin C.
Partner: UNT Libraries Government Documents Department
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Flight Tests of Modifications to Improve the Aileron Control Characteristics of a North American XP-51 Airplane (AC No. 41-38)

Description: Investigations were undertaken to improve the ailerons of a P-51 fighter so as to obtain greater effectiveness without increasing the stick forces. Modifications consisted of increasing the deflection range of the aileron to 70 percent and changing the original concave section to a thick section with beveled trailing edge. Results of the modified ailerons showed an increase in effectiveness over the original aileron of 70 percent at low speed and 55 percent at high speeds.
Date: June 1942
Creator: White, M. D. & Hoover, Herbert H.
Partner: UNT Libraries Government Documents Department
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Effect of power on the stick-fixed neutral points of several single-engine monoplanes as determined in flight

Description: Report presenting an analysis of the effect of power on the variation of stick-fixed neutral point with lift coefficient for several single-engine monoplanes. Testing occurred with the power off and with rated, climbing, or wave-off power and with flaps neutral and deflected. Results for these different conditions are provided.
Date: August 1944
Creator: White, Maurice D.
Partner: UNT Libraries Government Documents Department
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Estimation of stick-fixed neutral points of airplanes

Description: Report presenting a method for calculating the stick-fixed neutral point of an airplane with the propeller windmilling, the flaps neutral, and landing gear retracted. The methods used in this report should be useful in estimating the stick-fixed neutral points of new designs for all flight conditions.
Date: March 1945
Creator: White, Maurice D.
Partner: UNT Libraries Government Documents Department
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Flight tests of beveled-trailing-edge ailerons with various modifications on a North American XP-51 airplane (AAF No.41-38)

Description: Report presenting flight testing using a North American XP-51 airplane with several arrangements of beveled-trailing-edge ailerons to determine the most satisfactory arrangement. Results regarding the aileron configuration, trimming tabs, and factors affecting symmetry of aileron characteristics are provided.
Date: December 1943
Creator: White, Maurice D. & Hoover, Herbert H.
Partner: UNT Libraries Government Documents Department
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Flight Investigation of Modifications to Improve the Elevator Control-Force Characteristics of the Curtiss SB2C-1C Airplane in Maneuvers

Description: Report discussing tests on three sets of elevators with various combinations of section contour, balancing tabs, bobweights, and control-system mechanical advantage on an SB2C-1C airplane. Effects on maneuvering stability, a comparison of production elevators and recommended arrangement, and internal elevator pressures are described.
Date: April 1945
Creator: White, Maurice D. & Reeder, John P.
Partner: UNT Libraries Government Documents Department
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Flying Qualities and Stalling Characteristics of North American XP-51 Airplane

Description: Report presenting a flight investigation of the flying qualities and stalling characteristics of a North American XP-51 airplane. The short-period longitudinal oscillation disappeared within one cycle in all conditions tested. Requirements for satisfactory stalling characteristics were met in all respects except for stall warning.
Date: April 1943
Creator: White, Maurice D.; Hoover, Herbert H. & Garris, Howard W.
Partner: UNT Libraries Government Documents Department
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Tests of an Adjustable-Area Exhaust Nozzle for Jet-Propulsion Engines

Description: Report discussing a comparison between a centrifugal-flow-type turbojet engine with an adjustable-area exhaust nozzle and with a series of fixed-area nozzles of various throat diameters. The adjustable-area nozzle was found to be as efficient as the fixed-area nozzles in testing. Information about the corrected static thrust, fuel flow, and tail-pipe gas temperature for both types of nozzles is provided.
Date: August 16, 1945
Creator: Wilcox, E. C.
Partner: UNT Libraries Government Documents Department
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