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Lift and Drag Tests of Three Airfoil Models With Fowler Flaps Submitted by Consolidated Aircraft Corporation

Description: Report presenting lift and drag tests made in the two-dimensional tunnel of three airfoil models. The models represented intermediate sections on alternative wings of the XB-32 airplane and were equipped with 0.30 Fowler flaps. Results regarding the Davis model, the C.A.C. model, and low-drag model are provided.
Date: December 1941
Creator: Abbott, Ira H. & Turner, Harold R., Jr.
Partner: UNT Libraries Government Documents Department

High-Speed Wind-Tunnel Tests of a 1/6-Scale Model of a Twin-Engine Pursuit Airplane

Description: Report presenting testing of a scale model of a twin-engine pursuit airplane in order to investigate the possibility of high-speed diving difficulties and to find remedies for them. Most of the data were obtained in force tests, although some pressure-distribution measurements, elevator hinge moments, and wake surveys were also made. The tests showed that the airplane will experience serious diving moments above lift coefficients of 0.5 at a Mach number of 0.65, and 0.1 at a Mach number of 0.725.
Date: December 1942
Creator: Ganzer, Victor M.
Partner: UNT Libraries Government Documents Department

Analysis and Correlation of Data Obtained by Six Laboratories on Fuel-Vapor Loss From Fuel Tanks During Simulated Flight

Description: 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.
Date: December 1944
Creator: Stone, Charles S.; Baker, Sol & Englert, Gerald W.
Partner: UNT Libraries Government Documents Department

Wind Tunnel Investigation of the Effects of Slot Shape and Flap Location on the Characteristics of a Low-Drag Airfoil Equipped with a 0.25-Chord Slotted Flap

Description: Tests were conducted at dynamic pressure of 50 lb per square foot with lift drag and pitch moment measurements throughout useful angle of attack range for constant flap deflection and position of a low-drag airfoil. Two slots were investigated and practical flap paths were selected for each Slot shape had a negligible effect on the maximum lift coefficient flap deflected, the rounded-entry slot had lower profile drag.
Date: December 1944
Creator: Holtzclaw, Ralph W. & Weisman, Yale
Partner: UNT Libraries Government Documents Department

Power-Off Tests of the Northrop N9M-2 Tailless Airplane in the 40- by 80-Foot Wind Tunnel

Description: Report discussing tests on the N9M-2 airplane to evaluate the airplane efficiency factor and to investigate the characteristics of the aeroboost in the elevon control system. The efficiency factor compared reasonably well to conventional airplanes and the aeroboost system and valve-chatter tests were satisfactory.
Date: December 14, 1944
Creator: Stevens, Victor I., Jr. & McCormack, Gerald M.
Partner: UNT Libraries Government Documents Department

Flight and Test-Stand Investigation of High-Performance Fuels in Double-Row Radial Air-Cooled Engines 1: Determination of Cooling Characteristics of Flight Engine

Description: Report discussing the cooling characteristics of a 14-cylinder double-row radial air-cooled engine in a four-engine airplane. The effects of charge-air flow, cooling-air pressure drop, and fuel-air ratio on the cooling characteristics were measured separately. The cooling equation, rear middle-barrel temperature, cooling-limited manifold pressure, and maximum cruising power versus temperature-limited power are described.
Date: December 20, 1944
Creator: Blackman, Calvin C.; White, H. Jack & Pragliola, Philip C.
Partner: UNT Libraries Government Documents Department

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

Process of Lead-Deposit Accumulations on Aircraft-Engine Spark Plugs

Description: Report discussing an investigation of the progressive accumulation of load deposits on spark plugs under nonvarying operating conditions. Deposit-weight determinations and photographic observations are presented, and the specific characteristics of deposit accumulation are described.
Date: December 1945
Creator: Sloop, J. L.; Kinney, George R. & Rowe, William H.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Investigation of Alternative Propellers Operating Behind Deflected Wing Flaps for the XB-36 Airplane

Description: Report discussing testing on the aerodynamic characteristics of two pusher propellers with the same plan form but different airfoil sections behind a slotted flap on the XD-36 airplane. Testing was carried out over the range of blade angles and flap deflections necessary to cover all flight conditions. The effects of flaps and of tip Mach number are described in detail.
Date: December 1945
Creator: Boxer, Emanuel
Partner: UNT Libraries Government Documents Department

Lift and Drag Characteristics of a Low-Drag Airfoil With Slotted Flap Submitted by Curtiss-Wright Corporation

Description: Report presenting a wooden model equipped with a slotted flap that was tested in the two-dimensional tunnel. It represented a wing section of the Curtiss-Wright P-60A airplane and the NACA 66,2-118 section. Results regarding lift characteristics, drag coefficients, and flap deflection characteristics are provided.
Date: December 1941
Creator: Abbott, Ira H.
Partner: UNT Libraries Government Documents Department

Pressure-Distribution Measurements of a Low-Drag Airfoil With Slotted Flap Submitted by Curtiss-Wright Corporation

Description: "Pressure-distribution measurements were made at the request of the Materiel Division, U.S. Army Air Corps, on a 24-inch-chord wooden model equipped with a slotted flap and submitted by the Curtiss-Wright Corporation. The tests were made in the Langley two-dimensional tunnel at a Reynolds number of about 5,600,000" (p. 1).
Date: December 1941
Creator: Abbott, Ira H.
Partner: UNT Libraries Government Documents Department

Tests of a Thermal Ice-Prevention System for a Wing Leading-Edge Landing-Light Installation

Description: Report discussing the creation of a thermal ice-prevention system of a bomber-type airplane to provide protection against ice and fog formations on the transparent fairing over the landing light in the wing leading edge. A comparison between the design performance and actual performance showed that the outer-surface heat-transfer coefficient was correctly predicted, but the inner-surface heat-transfer coefficient was four times as large, leading to failure of the plastic fairing.
Date: December 1944
Creator: Hillendahl, Wesley H.
Partner: UNT Libraries Government Documents Department

Flight Tests of Various Tail Modifications on the Brewster XSBA-1 Airplane 2: Measurements of Flying Qualities with Tail Configuration Number Two

Description: Several tail modifications of the Brewster XSBA-1 scout-bomber were investigated and results compared. Modifications consisted of variation of the chord of the elevator and rudder while the total area of the surfaces is kept constant and variations of the total area of the vertical tail surface. Configuration number 2 reduced trim changes by 50 percent and reduced average elevator control force gradient from 30 to 27 pounds/g. Stick travel required to stall in maneuver was 4.6 inches.
Date: December 1943
Creator: Phillips, W. H. & Crane, H. L.
Partner: UNT Libraries Government Documents Department

Charts Showing Stability and Control Characteristics of Airplanes in Flight

Description: 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.
Date: December 1944
Creator: Stability and Control Section. Flight Research Division
Partner: UNT Libraries Government Documents Department

Analysis of V-G Records From the SNJ-4 Airplane

Description: 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.
Date: December 1945
Creator: Wilkerson, M. & Bennett, S. A.
Partner: UNT Libraries Government Documents Department

Measurement of Flying Qualities of a Douglas A-26B Airplane (AAF No. 41-39120) 1: Longitudinal Stability and Control Characteristics

Description: Report discussing testing of the Douglas A-26B to determine the longitudinal stability and control characteristics. Information about the elevator, stick-fixed and stick-free stability, center of gravity, and flap effects are described.
Date: December 6, 1944
Creator: Crane, H. L.; Sjoberg, S. A. & Hoover, H. H.
Partner: UNT Libraries Government Documents Department

Measurements in Flight of the Stability, Lateral Control, and Stalling Characteristics of an Airplane Equipped With Full-Span Zap Flaps and Spoiler-Type Ailerons

Description: Report presenting the stability, lateral-control, and stalling characteristics of an airplane modified to accommodate full-span Zap flaps.The static and dynamic longitudinal and lateral stability was satisfactory, but there were some undesirable lateral-control characteristics, including excessive friction and elasticity.
Date: December 1943
Creator: Spahr, J. Richard & Christophersen, Don R.
Partner: UNT Libraries Government Documents Department

Knock-Limited Performance of Blends of AN-F-28 Fuel Containing 2 Percent Aromatic Amines 4

Description: Report discussing tests on the effect of 2-percent additions of 13 aromatic amines on the knock-limited performance of 28-R fuel in a CFR engine. The amines tested gave good rich mixture response at standard F-4 operating conditions, but were sensitive to engine severity at lean fuel-air ratios.
Date: December 21, 1944
Creator: Alquist, Henry E. & Tower, Leonard K.
Partner: UNT Libraries Government Documents Department

Laboratory Investigation of Icing in the Carburetor and Supercharger Inlet Elbow of an Aircraft Engine 1: Description of Setup and Testing Technique

Description: Report discussing icing and de-icing of the carburetor and supercharger inlet of typical aircraft engine induction systems. A description of the systems used to control and simulate different conditions is provided.
Date: December 1945
Creator: Mulholland, Donald R.; Rollin, Vern G. & Galvin, Herman B.
Partner: UNT Libraries Government Documents Department

Laboratory Investigation of Icing in the Carburetor and Supercharger Inlet Elbow of an Aircraft Engine 3: Heated Air as a Means of De-Icing the Carburetor and Supercharger Inlet Elbow

Description: Report discussing the use of a twin-barrel injection carburetor and a supercharger inlet elbow to establish the relation between wet- and dry-bulb temperatures of the de-icing air and time required to recover from air-flow loss due to icing. The tests were performed at several power conditions, icing conditions, temperatures, and dry and humidified air. De-icing time was found to be a function of the nature of the ice formation and of the wet-bulb temperature of the de-icing air.
Date: December 1945
Creator: Lyons, Richard E. & Coles, Willard D.
Partner: UNT Libraries Government Documents Department

Laboratory Investigation of Icing in the Carburetor and Supercharger Inlet Elbow of an Aircraft Engine 5: Effect of Injection of Water-Fuel Mixtures and Water-Ethanol-Fuel Mixtures on the Icing Characteristics

Description: Report discussing the effects of internal coolants injected with fuel on the icing characteristics of a twin-barrel injection carburetor mounted on an engine-stage supercharger assembly. The tests were made at conditions that simulated war emergency power and at a variety of water-fuel ratios, carburetor-air temperatures, and carburetor-air relative humidities.
Date: December 1945
Creator: Renner, Clark E.
Partner: UNT Libraries Government Documents Department

Laboratory Investigation of Icing in the Carburetor and Supercharger Inlet Elbow of an Aircraft Engine 2: Determination of the Limiting-Icing Conditions

Description: "The carburetor and engine-stage supercharger assembly of a fighter aircraft were laboratory-tested to determine the icing characteristics of the induction system under three simulated engine power conditions with varying carburetor-air temperature, relative humidity, simulated-rain injection, rain and fuel temperature, fuel-air ratio, and fuel of different distillation characteristics" (p. 1).
Date: December 1945
Creator: Essex, Henry A.; Keith, Wayne C. & Mulholland, Donald R.
Partner: UNT Libraries Government Documents Department