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Aerodynamic Characteristics of NACA 23012 and 23021 Airfoils With 20-Percent-Chord External-Airfoil Flaps of NACA 23012 Section

Description: Report presents the results of an investigation of the general aerodynamic characteristics of the NACA 23012 and 23021 airfoils, each equipped with a 0.20c external flap of NACA 23012 section. The tests were made in the NACA 7 by 10-foot and variable-density wind tunnels and covered a range of Reynolds numbers that included values corresponding to those for landing conditions of a wide range of airplanes. Besides a determination of the variation of lift and drag characteristics with position of… more
Date: 1937~
Creator: Platt, Robert C. & Abbott, Ira H.
Item Type: Refine your search to only Report
open access

Air propellers in yaw

Description: Report presents the results of tests conducted at Stanford University of a 3-foot model propeller at four pitch settings and at 0 degree, 10 degrees, 20 degrees, and 30 degrees yaw.
Date: 1937
Creator: Lesley, E. P.; Worley, George F. & Moy, Stanley
Item Type: Refine your search to only Report
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Alternating-current equipment for the measurement of fluctuations of air speed in turbulent flow

Description: From Summary: "Recent electrical and mechanical improvements have been made in the equipment developed at the National Bureau of Standards for measurement of fluctuations of air speed in turbulent flow. Data useful in the design of similar equipment are presented. The design of rectified alternating-current power supplies for such apparatus is treated briefly, and the effect of the power supplies on the performance of the equipment is discussed."
Date: March 1937
Creator: Mock, W. C., Jr.
Item Type: Refine your search to only Report
open access

An analysis of the factors that determine the periodic twist of an autogiro rotor blade, with a comparison of predicted and measured results

Description: Report presents an analysis of the factors that determine the periodic twist of a rotor blade under the action of the air forces on it. The results of the analysis show that the Fourier coefficients of the twist are linear expressions involving only the tip-speed ratio, the pitch setting, the inflow coefficient, the pitching-moment coefficient of the blade airfoil section, and the physical characteristics of the rotor blade and machine.
Date: April 14, 1937
Creator: Wheatley, John B.
Item Type: Refine your search to only Report
open access

An Analytical and Experimental Study of the Effect of Periodic Blade Twist on the Thrust, Torque, and Flapping Motion of an Autogiro Rotor

Description: From Summary: "An analysis is made of the influence on autogiro rotor characteristics of a periodic blade twist that varies with the azimuth position of the rotor blade and the results are compared with experimental data. The analysis expresses the influence of this type of twist upon the thrust, torque, and flapping motion of the rotor. The check against experimental data shows that the periodic twist has a pronounced influence on the flapping motion and that this influence is accurately predi… more
Date: January 28, 1937
Creator: Wheatley, John B.
Item Type: Refine your search to only Report
open access

Auto-Ignition and Combustion of Diesel Fuel in a Constant-Volume Bomb

Description: Report presents the results of a study of variations in ignition lag and combustion associated with changes in air temperature and density for a diesel fuel in a constant-volume bomb. The test results have been discussed in terms of engine performance wherever comparisons could be drawn. The most important conclusions drawn from this investigation are: the ignition lag was essentially independent of the injected fuel quantity. Extrapolation of the curves for the fuel used shows that the lag cou… more
Date: October 5, 1937
Creator: Selden, Robert F.
Item Type: Refine your search to only Report
open access

Column Strength of Tubes Elastically Restrained Against Rotation at the Ends

Description: Report presents the results of a study made of the effects of known end restraint on commercially available round and streamline tubing of chromium-molybdenum steel, duralumin, stainless steel, and heat-treated chromium-molybdenum steel; and a more accurate method than any previously available, but still a practical method, was developed for designing compression members in riveted or welded structures, particularly aircraft. Two hundred specimens were tested as short, medium-length, and long c… more
Date: September 9, 1937
Creator: Osgood, William R.
Item Type: Refine your search to only Report
open access

Comparative Flight and Full-Scale Wind-Tunnel Measurements of the Maximum Lift of an Airplane

Description: "Determinations of the power-off maximum lift of a Fairchild 22 airplane were made in the NACA full-scale wind tunnel and in flight. The results from the two types of test were in satisfactory agreement. It was found that, when the airplane was rotated positively in pitch through the angle of stall at rates of the order of 0.1 degree per second, the maximum lift coefficient was considerably higher than that obtained in the standard tests, in which the forces are measured with the angles of atta… more
Date: October 26, 1937
Creator: Silverstein, Abe; Katzoff, S. & Hootman, James A.
Item Type: Refine your search to only Report
open access

Compressible Flow About Symmetrical Joukowski Profiles

Description: "The method of Poggi is employed for the determination of the effects of compressibility upon the flow past an obstacle. A general expression for the velocity increment due to compressibility is obtained. The general result holds whatever the shape of the obstacle; but, in order to obtain the complete solution, it is necessary to know a certain Fourier expansion of the square of the velocity of flow past the obstacle. An application is made to the case flow of a symmetrical Joukowski profile wi… more
Date: November 19, 1937
Creator: Kaplan, Carl
Item Type: Refine your search to only Report
open access

A discussion of certain problems connected with the design of hulls of flying boats and the use of general test data

Description: Report presents the results of a survey of problems encountered in applying general test data to the design of flying-boat hulls. It is shown how basic design features may be readily determined from special plots of test data. A study of the effect of the size of a flying boat on the probable limits to be covered by the general test data is included and recommendations for special tests and new methods of presenting test data for direct use in design are given.
Date: November 1937
Creator: Diehl, Walter S.
Item Type: Refine your search to only Report
open access

Drag of Cylinders of Simple Shapes

Description: "In order to determine the effect of shape, compressibility, and Reynolds number on the drag and critical speed for simple forms, the drag forces on models of various simple geometric cross sections were measured in the NACA 11-inch high-speed wind tunnel. The models were circular, semitubular, elliptical, square, and triangular (isosceles) cylinders. They were tested over a speed range from 5 percent of the speed of sound to a value in excess of the critical speed, corresponding, for each mode… more
Date: October 27, 1937
Creator: Lindsey, W. F.
Item Type: Refine your search to only Report
open access

The experimental and calculated characteristics of 22 tapered wings

Description: From Summary: "The experimental and calculated aerodynamic characteristics of 22 tapered wings are compared, using tests made in the variable-density wind tunnel. The wings had aspect ratios from 6 to 12 and taper ratios from 1:6:1 and 5:1. The compared characteristics are the pitching moment, the aerodynamic-center position, the lift-curve slope, the maximum lift coefficient, and the curves of drag. The method of obtaining the calculated values is based on the use of wing theory and experiment… more
Date: November 17, 1937
Creator: Anderson, Raymond F.
Item Type: Refine your search to only Report
open access

Experimental Investigation of Wind-Tunnel Interference on the Downwash Behind an Airfoil

Description: "The interference of the wind-tunnel boundaries on the downwash behind an airfoil has been experimentally investigated and the results have been compared with the available theoretical results for open-throat wind tunnels. As in previous studies, the simplified theoretical treatment that assumes the test section to be an infinite free jet has been shown to be satisfactory at the lifting line. The experimental results, however, show that this assumption may lead to erroneous conclusions regardin… more
Date: June 4, 1937
Creator: Silverstein, Abe & Katzoff, S.
Item Type: Refine your search to only Report
open access

A Flight Comparison of Conventional Ailerons on a Rectangular Wing and of Conventional and Floating Wing-Tip Ailerons on a Tapered Wing

Description: Report presents the results of flight tests comparing the relative effectiveness of conventional ailerons of the same size on wings of rectangular and tapered plan forms made with a Fairchild 22 airplane. Information is included comparing conventional and floating wing-tip ailerons on a tapered wing. The results showed that the conventional ailerons were somewhat more effective on the tapered than on the rectangular wing. The difference, however, was so small as to be imperceptible to the pilot… more
Date: October 27, 1937
Creator: Soulé, H. A. & Gracey, W.
Item Type: Refine your search to only Report
open access

Full-Scale Tests of a New Type NACA Nose-Slot Cowling

Description: "An extended experimental study has been made in regard to the various refinements in the design of engine cowlings as related to the propeller-nacelle unit as a whole, under conditions corresponding to take-off, climb, and normal flight. The tests were all conducted at full scale in the 20-foot wind tunnel. This report presents the results of a novel type of engine cowling, characterized by the fact that the exit opening discharging the cooling air is not, as usual, located behind the engine b… more
Date: 1937
Creator: Theodorsen, Theodore; Brevoort, M. J.; Stickle, George W. & Gough, M. N.
Item Type: Refine your search to only Report
open access

General Airplane Performance

Description: "Equations have been developed for the analysis of the performance of the ideal airplane, leading to an approximate physical interpretation of the performance problem. The basic sea-level airplane parameters have been generalized to altitude parameters and a new parameter has been introduced and physically interpreted. The performance analysis for actual airplanes has been obtained in terms of the equivalent ideal airplane in order that the charts developed for use in practical calculations wil… more
Date: June 1, 1937
Creator: Rockfeller, W. C.
Item Type: Refine your search to only Report
open access

Interrelation of Exhaust-Gas Constituents

Description: This report presents the results of an investigation conducted to determine the interrelation of the constituents of the exhaust gases of internal-combustion engines and the effect of engine performance on these relations. Six single-cylinder, liquid-cooled tests engines and one 9-cylinder radial air-cooled engine were tested. Various types of combustion chambers were used and the engines were operated at compression ratios from 5.1 to 7.0 using spark ignition and from 13.5 to 15.6 using compre… more
Date: September 7, 1937
Creator: Gerrish, Harold C. & Voss, Fred
Item Type: Refine your search to only Report
open access

Measurements of Intensity and Scale of Wind-Tunnel Turbulence and Their Relation to the Critical Reynolds Number of Spheres

Description: The investigation of wind-tunnel turbulence, conducted at the National Bureau of Standards with the cooperation of the National Advisory Committee for Aeronautics, has been extended to include a new variable, namely, the scale of the turbulence. This report presents the results of a study of this new variable together with the intensity of the turbulence, and the effect of both on the critical Reynolds number of spheres.
Date: 1937
Creator: Dryden, Hugh L.; Schubauer, G. B.; Mock, W. C., Jr. & Skramstad, H. K.
Item Type: Refine your search to only Report
open access

A photographic study of combustion and knock in a spark-ignition engine

Description: Report presents the results of a photographic study of the combustion in a spark-ignition engine using both Schlieren and flame photographs taken at high rates of speed. Although shock waves are present after knock occurs, there was no evidence of any type of sonic or supersonic compression waves existing in the combustion gases prior to the occurrence of knock. Artificially induced shock waves in the engine did not in themselves cause knock.
Date: December 6, 1937
Creator: Rothrock, A. M. & Spencer, R. C.
Item Type: Refine your search to only Report
open access

Pressure-distribution measurements at large angles of pitch on fins of different span-chord ratio on a 1/40-scale model of the U. S. Airship "Akron"

Description: Report presents the results of pressure-distribution measurements on a 1/40-scale model of the U. S. Airship "Akron" conducted in the NACA 20-foot wind tunnel. The measurements were made on the starboard fin of each of four sets of horizontal tail surfaces, all of approximately the same area but differing in span-chord ratio, for five angles of pitch varying from 11.6 degrees to 34 degrees, for four elevator angles, and at air speeds ranging from 56 to 77 miles per hour. Pressures were also mea… more
Date: April 4, 1937
Creator: McHugh, James G.
Item Type: Refine your search to only Report
open access

Pressure distribution over a rectangular airfoil with a partial-span split flap

Description: This report presents the results of pressure-distribution tests of a Clark y wing model with a partial-span split flap made to determine the distribution of air loads over both the wing and the flap. The model was used in conjunction with a reflection plane in the NACA 7 by 10 foot wind tunnel. The 20-percent-chord split flap extended over the inboard 60 percent of the semispan. The tests were made at various flap deflections up to 45 degrees and covered a range of angles of attack from zero li… more
Date: April 28, 1937
Creator: Wenzinger, Carl J. & Harris, Thomas A.
Item Type: Refine your search to only Report
open access

Pressure Distribution Over Airfoils With Fowler Flaps

Description: Report presents the results of tests made of a Clark y airfoil with a Clark y Fowler flap and of an NACA 23012 airfoil with NACA Fowler flaps. Some of the tests were made in the 7 by 10-foot wind tunnel and others in the 5-foot vertical wind tunnel. The pressures were measured on the upper and lower surfaces at one chord section both on the main airfoils and on the flaps for several angles of attack with the flaps located at the maximum-lift settings.
Date: November 24, 1937
Creator: Wenzinger, Carl J. & Anderson, Walter B.
Item Type: Refine your search to only Report
open access

Resume and analysis of NACA lateral control research

Description: "An analysis of the principal results of recent NACA lateral control research is made by utilizing the experience and progress gained during the course of the investigation. Two things are considered of primary importance in judging the effectiveness of different control devices: the (calculated) banking and yawing motion of a typical small airplane caused by a deflection of the control, and the stick force required to produce this deflection. The report includes a table in which a number of di… more
Date: April 20, 1937
Creator: Weick, Fred E. & Jones, Robert T.
Item Type: Refine your search to only Report
open access

Spinning characteristics of the XN2Y-1 airplane obtained from the spinning balance and compared with results from the spinning tunnel and from flight tests

Description: Report presents the results of tests of a 1/10-scale model of the XN2Y-1 airplane tested in the NACA 5-foot vertical wind tunnel in which the six components of forces and moments were measured. The model was tested in 17 attitudes in which the full-scale airplane had been observed to spin, in order to determine the effects of scale, tunnel, and interference. In addition, a series of tests was made to cover the range of angles of attack, angles of sideslip, rates of rotation, and control setting… more
Date: April 16, 1937
Creator: Bamber, M. J. & House, R. O.
Item Type: Refine your search to only Report
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