National Advisory Committee for Aeronautics (NACA) - 92 Matching Results

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Effect of Propeller Operation on the Pitching Moments of Single-Engine Monoplanes

Description: Report presenting an investigation of the effects of propeller operation on pitching moments with particular reference to the effect of propeller forces, the field of flow in the slipstream, and the increments of lift on the wing and the tail. A procedure, directly applicable only to single-engine monoplanes without flaps, has been set up for predicting the effect of propeller operation on pitching moments as well.
Date: May 1941
Creator: Goett, Harry J. & Pass, H. R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Effect of Six Aromatic Amines on the Preignition-Limited Performance of 28-R Aviation Fuel in a CFR Engine

Description: Report discussing the results of testing on the suitability of six aromatic amines as fuel additives. Antiknock effectiveness, availability, physical properties, and chemical properties for knock tests were explored. The six aromatic amines were xylidines, cumidines, N-methylxylidines, N-methylcumidines, N-methylaniline, and N-methyltoluidine in 28-R aviation fuel.
Date: May 12, 1945
Creator: Male, Donald W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Electromagnetic-Analogy Method of Solving Lifting-Surface-Theory Problems

Description: Report presenting a method for making lifting-surface calculations by means of magnetic measurements of an electromagnetic-analogy model. The method is based on the perfect analogy between the strength of the magnetic field around a conductor and the strength of the induced-velocity field around a vortex.
Date: May 1945
Creator: Swanson, Robert S. & Crandall, Stewart M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Emergency Measures for Increasing the Range of Fighter Airplanes

Description: "An analysis was made to show the relative effectiveness of streamline external fuel tanks, a fuel tank in the form of a wing mounted in a biplane position, and auxiliary wing panels attached at the wing tips to increase the span as temporary means for increasing the range of a fighter-type airplane. Figures and charts for the various devices considered show the results of calculations of range, duration of flight, and take-off distance for both land-base and carrier operation. The results indi… more
Date: May 1943
Creator: Jones, Robert T. & Wetmore, Joseph W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Engine Tests of Pressurized Shunt-Type Cooling Systems for a Liquid-Cooled Engine

Description: Report presenting tests conducted to determine the performance of two pressurized shunt-type cooling systems for liquid-cooled aircraft engines using a mixture of 30 percent AN-E-2 ethylene glycol and 70 percent water as the coolant. Results regarding effect of engine speed on coolant-flow rate, effect of expansion-tank pressure on coolant-flow rate, relation between pump-inlet pressure and expansion-tank pressure, variation of coolant-flow rate with pump-inlet pressure, flow rate through the s… more
Date: May 1945
Creator: Manganiello, Eugene J.; Lundin, Bruce T. & Povolny, John H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Estimation of Pressures on Cockpit Canopies, Gun Turrets, Blisters, and Similar Protuberances

Description: Report presenting methods for estimating pressure distributions over protuberances such as cockpit canopies, gun turrets, blisters, scoops, and sighting domes. The methods are applied to the estimation of the pressure distributions over spherical segment and faired gun turrets and over the protuberances on the Brewster SB2A-1 airplane. The effects of compressibility, interference, and flow separation are discussed.
Date: May 1944
Creator: Wright, Ray H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Experimental Investigation of Rectangular Exhaust-Gas Ejectors Applicable for Engine Cooling

Description: Report presenting an experimental investigation of rectangular exhaust-gas ejector pump to provide data that would serve as a guide to the design of ejector applications for aircraft engines with marginal cooling. With a decrease in the quantity of air pumped and an increase in the length of an ejector, the ejector pressure rise increases to optimum values. Results regarding straight ejectors, diffuser ejectors, curved ejectors, ejector aspect ratio, divided ejectors, multistage ejectors, and n… more
Date: May 1945
Creator: Manganiello, Eugene J. & Bogatsky, Donald
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Fatigue strength and related characteristics of joints in 24S-T Alclad sheet

Description: Report includes tension fatigue test results on the following types of samples of 0.040-inch alclad 24s-t: (1) monoblock sheet samples as received and after a post-aging heat treatment, (2) "sheet efficiency" samples (two equally stressed sheets joined by a single transverse row of spot welds) both as received and after post-aging, (3) spot-welded lap-joint samples as received and after post-aging, and (4) roll-welded lap-joint samples. (author).
Date: May 1944
Creator: Russell, H. W.; Jackson, L. R.; Grover, H. J. & Beaver, W. W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A flight investigation of internally balanced sealed ailerons in the presence of a balanced split flap

Description: Report presenting flight tests made with a modified Ryan ST airplane to determine the effect on aileron characteristics of various arrangements of balanced split flaps covering that portion of the wing span occupied by the ailerons. With the flaps fully extended, the aileron effectiveness was reduced by approximately 18 percent of the effectiveness measured with ailerons alone.
Date: May 1942
Creator: Williams, W. C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A flight investigation of short-period longitudinal oscillations of an airplane with free elevator

Description: Report presenting a flight investigation to check the results of a theoretical analysis of longitudinal stability of an airplane with free controls. Tests used a Fairchild XR2K-1 airplane on which the weight moment and the aerodynamic balance of the elevator were varied to bring it into a condition where unstable short-period oscillations were encountered.
Date: May 1942
Creator: Phillips, William H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A flight investigation of the boundary-layer characteristics and profile drag of the NACA 35-215 laminar-flow airfoil at high Reynolds numbers

Description: Report presenting testing to determine the boundary layer characteristics and profile drag of the NACA 35-215 airfoil section at high Reynolds numbers. The results indicated that a forward movement of the transition point occurred at about 3 percent of the chord due to operation of the engines and propellers.
Date: May 1941
Creator: Platt, Robert C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Tests of an SB2C-3 Airplane With a Production and Tilted Propeller Axis

Description: Report discussing the changes in static longitudinal stability due to tilting the propeller axis of an SB2C-3 airplane downward. Tilting the propeller was found to be beneficial for stability, but only if the pilot was in a forward center-of-gravity position with a tilted engine. Installing a tilted engine reduced trim forces due to the changes in power up to 25 percent.
Date: May 1945
Creator: Goranson, R. Fabian
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Tests of Dive-Recovery Flaps on an XP-51 Airplane

Description: Report presenting a flight investigation made to determine the effectiveness of dive-recovery flaps installed on the XP-51 airplane as a safety device for recovery from contemplated terminal-velocity dives. The flap installation is described and results are presented of measurements obtained during stick-free pull-ups and pull-outs made by deflecting the dive-recovery flaps to two selected values of flap angle .
Date: May 1945
Creator: Beeler, De E. & Williams, Walter C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Formulas for propellers in yaw and charts of the side-force derivative

Description: Report presenting formulas for propellers for the rate of change of side-force coefficient with angle of yaw and for the rate of change of pitching-moment coefficient with angle of yaw. Charts of side-force derivatives are given for two propellers of different plan forms.
Date: May 1943
Creator: Ribner, Herbert S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Free-spinning-tunnel tests of a model of a canard airplane

Description: Report presenting a series of tests made in the 15-foot free-spinning tunnel to study the spin characteristics of a model of a hypothetical canard airplane, which was designed to be about the same size and have the same general aerodynamic characteristics as a Boeing B-247 airplane. The model spun normally and had excellent recovery characteristics.
Date: May 1943
Creator: Pepoon, Philip W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Fuel-Evaporation Loss as Determined by the Change in the Specific Gravity of the Fuel in an Aircraft Fuel Tank

Description: Report discusses the results of an investigation to determine the feasibility of using the change in the specific gravity of fuels in aircraft fuel tanks to measure fuel-vaporization loss. Six fuels were tested via fuel-distillation tests and simulated-flight tests. An equation based on the specific gravity of the fuel is also described.
Date: May 1945
Creator: Stone, Charles S. & Kramer, Walter E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Full-scale tunnel investigation of the pressure distribution over the tail of the P-47B airplane

Description: Report presenting measurements made of the pressures of the tail surfaces of the Republic Aviation Corporation P-47B airplane in the full-scale tunnel. Pressures were measured over the horizontal and vertical tail surfaces for several angles of attack and angles of yaw with numerous control-surface deflections to provide a check on the design loads. Results regarding the normal-force coefficients and predictions of forces on horizontal tail surfaces are provided.
Date: May 1943
Creator: Dingeldein, Richard C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Generalized selection charts for bombers with four 2000-horsepower engines

Description: Report presenting a study of the performance of bombers powered by four 2000-horsepower engines supercharged to 25,000 feet. A series of charts is provided with the coordinates of power loading and wing loading in order to simplify the selection of the best airplane for a given purpose.
Date: May 1942
Creator: Brevoort, Maurice J.; Stickle, George W. & Hill, Paul R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Heat-Capacity Lag in Turbine-Working Fluids

Description: Report discusses measurements of the relaxation time of steam and nitrogen due to their importance as turbine-working fluids. Additional calculations regarding different nozzle lengths are included.
Date: May 1944
Creator: Kantrowitz, Arthur & Huber, Paul W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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High-Speed Tests of a Ducted Body with Various Air-Outlet Openings

Description: Test of a ducted body with Internal flow were made in the 8-foot high-speed wind tunnel for the purpose of studying the effects on external drag and an critical speed of the addition of efficient inlet and outlet openings to a basic streamline shape. Drag tests of a 13.6- inch-diameter streamline body of fineness ratio 6.14 were made at Mach numbers ranging from 0.20 to 0.75. The model was centrally mounted on a 9-percent-thick airfoil and was designed to have an efficient airfoil-body juncture… more
Date: May 1942
Creator: Becker, John V. & Baals, Donald D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

High-speed tests of radial-engine nacelles on a thick low-drag wing

Description: Report presenting testing in the high-speed wind tunnel to determine the drag characteristics of several types of radial-engine nacelle on a low-drag airfoil. The drag coefficients of nacelles incorporating cowling-nose shapes shown by previous tests to be efficient and afterbodies of adequate length were about the same magnitude as commonly obtained for comparable installations on conventional wings. Results regarding the reduction of data, effect of nacelles on lift, and pressures at wing-nac… more
Date: May 1942
Creator: Becker, John V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Hydraulic Characteristics of the NACA Injection Impeller

Description: Report discussing a mock-up injection impeller created to investigate the hydraulic characteristics and limitations of the NACA injection impeller currently in use. Information about the form and magnitude of critical factors of fuel-transfer leakage and peripheral fuel distribution is provided as well as the effects of design variations of components on hydraulic characteristics. Several revisions in portions of the impeller are suggested to improve its fuel-transfer, fuel-pumping, and fuel-eq… more
Date: May 1946
Creator: Ritter, William K.; Johnsen, Irving A. & Lieblein, Seymour
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Influence of Bulkhead Spacing on Bending Stresses Due to Torsion

Description: Report presenting the reasons for the existence of bending stresses due to torsion and the theoretical formulas applying to rectangular boxes with finite bulkhead spacing. Tests are described which were made to verify the theory, strains being measured on a rectangular torsion box with four bulkhead spacings. Results regarding normal stresses are provided.
Date: May 1942
Creator: Kuhn, Paul
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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