551 Matching Results

Search Results

Advanced search parameters have been applied.

Ovalization of tubes under bending and compression

Description: An empirical equation has been developed that gives the approximate amount of ovalization for tubes under bending loads. Tests were made on tubes in the d/t range from 6 to 14, the latter d/t ratio being in the normal landing gear range. Within the range of the series of tests conducted, the increase in ovalization due to a compression load in combination with a bending load was very small. The bending load, being the principal factor in producing the ovalization, is a rather complex function of the bending moment, d/t ratio, cantilever length, and distance between opposite bearing faces. (author).
Date: March 1944
Creator: Demer, L. J. & Kavanaugh, E. S.
Partner: UNT Libraries Government Documents Department

Performance of axial-flow fan and compressor blades designed for high loadings

Description: Report presenting an investigation to determine the effects of loading on the performance of axial-flow fan and compressor blades in a test blower. Results regarding verification of the two-dimensional design data and effects of blade roughness are provided.
Date: February 1947
Creator: Bogdonoff, Seymour M. & Herrig, L. Joseph
Partner: UNT Libraries Government Documents Department

A warning concerning the take-off with heavy load

Description: "A successful take-off can be made with an airplane so heavily loaded that it cannot climb to a height greater than the span of its wings. The explanation is that the power required to maintain level flight at an altitude of the order of the wing span may be as much as 50 per cent greater than that necessary when the airplane is just clear of the ground. The failure of heavily loaded airplanes to continue climbing at the rate attained immediately after the actual take-off is a grave hazard and has resulted in great risk or catastrophe in three notable cases which are cited" (p. 1).
Date: July 1927
Creator: Reid, Elliott G. & Carroll, Thomas
Partner: UNT Libraries Government Documents Department

Researches on ailerons and especially on the test loads to which they should be subjected

Description: Aileron calculations have hitherto given greatly differing results according to different authors. It seems to be the general opinion that it is only necessary to give the ailerons such dimensions that the airplane can maneuver well, that the stresses they must undergo are relatively small, and that they are strong enough if their framework is of the order of strength as the wings to which they are attached. This article will show that the problem is really quite complex and that it should receive more attention.
Date: February 1927
Creator: Sabatier, J.
Partner: UNT Libraries Government Documents Department

A summary of ground-loads statistics

Description: From Summary: "This paper briefly summaries the more important statistical data obtained by the NACA on the subject of ground loads. The information presented relates primarily to landing-impact and taxiing loads; however, some limited data are also presented on one phase of ground-handling loads, namely, braking friction. A number of experimental and theoretical papers dealing with various aspects of the subject are listed in the bibliography."
Date: May 1957
Creator: Westfall, John R.; Milwitzky, Benjamin; Silsby, Norman S. & Dreher, Robert C.
Partner: UNT Libraries Government Documents Department

Derivation of charts for determining the horizontal tail load variation with any elevator motion

Description: From Summary: "The equations relating the wing and tail loads are derived for a unit elevator displacement. These equations are then converted into a nondimensional form and charts are given by which the wing- and tail-load-increment variation may be determined under dynamic conditions for any type of elevator motion and for various degrees of airplane stability. In order to illustrate the use of the charts, several examples are included in which the wing and tail loads are evaluated for a number of types of elevator motion. Methods are given for determining the necessary derivatives from results of wind-tunnel tests when such tests are available."
Date: November 23, 1942
Creator: Pearson, Henry A.
Partner: UNT Libraries Government Documents Department

A comparison of three theoretical methods of calculating span load distribution on swept wings

Description: From Summary: "Three methods for calculating span load distribution, those developed by V.M Falkner, Wm. Mutterperl, and J. Weissinger, have been applied to five swept wings. The angles of sweep ranged from -45 degrees to +45 degrees. These methods were examined to establish their relative accuracy and case of application. Experimentally determined loadings were used as a basis for judging accuracy. For the convenience of the readers the computing forms and all information requisite to their application are included in appendixes. From the analysis it was found that the Weissinger method would be best suited to an over-all study of the effects of plan form on the span loading and associated characteristics of wings."
Date: June 9, 1947
Creator: Van Dorn, Nicholas H. & DeYoung, John
Partner: UNT Libraries Government Documents Department

Theoretical symmetric span loading at subsonic speeds for wings having arbitrary plan form

Description: From Summary: "A method is shown by which the symmetric span loading for a certain class of wings can be simply found. The geometry of these wings is limited only to the extent that they must have symmetry about the root chord, must have a straight quarter-chord line over the semispan, and must have no discontinuities in twist. A procedure is shown for finding the lift-curve slope, pitching moment, center of lift, and induced drag from the span load distribution. A method of accounting for the effects of Mach number and for changes in section lift-curve slope is also given."
Date: 1948
Creator: DeYoung, John & Harper, Charles W.
Partner: UNT Libraries Government Documents Department

Theoretical antisymmetric span loading for wings of arbitrary plan form at subsonic speeds

Description: A simplified lifting-surface theory that includes effects of compressibility and spanwise variation of section lift-curve slope is used to provide charts with which antisymmetric loading due to arbitrary antisymmetric angle of attack can be found for wings having symmetric plan forms with a constant spanwise sweep angle of the quarter-chord line. Consideration is given to the flexible wing in roll. Aerodynamic characteristics due to rolling, deflected ailerons, and sideslip of wings with dihedral are considered. Solutions are presented for straight-tapered wings for a range of swept plan forms.
Date: December 22, 1949
Creator: DeYoung, John
Partner: UNT Libraries Government Documents Department

A method for computing leading-edge loads

Description: From Summary: "In this report a formula is developed that enables the determination of the proper design load for the portion of the wing forward of the front spar. The formula is inherently rational in concept, as it takes into account the most important variables that affect the leading-edge load, although theoretical rigor has been sacrificed for simplicity and ease of application. Some empirical corrections, based on pressure distribution measurements on the PW-9 and M-3 airplanes have been introduced to provide properly for biplanes. Results from the formula check experimental values in a variety of cases with good accuracy in the critical loading conditions. The use of the method for design purposes is therefore felt to be justified and is recommended."
Date: January 16, 1931
Creator: Rhode, Richard V. & Pearson, Henry A.
Partner: UNT Libraries Government Documents Department

Relative loading on biplane wings

Description: Recent improvements in stress analysis methods have made it necessary to revise and to extend the loading curves to cover all conditions of flight. This report is concerned with a study of existing biplane data by combining the experimental and theoretical data to derive a series of curves from which the lift curves of the individual wings of a biplane may be obtained.
Date: February 15, 1933
Creator: Diehl, Walter S.
Partner: UNT Libraries Government Documents Department

Critical stress of plate columns

Description: Report presenting solutions for the elastic buckling stress of flat rectangular plates with simply supported or fixed ends when loaded as columns. The procedure for determining the critical stress of plate columns with intermediate end fixities is also given.
Date: August 1950
Creator: Houbolt, John C. & Stowell, Elbridge Z.
Partner: UNT Libraries Government Documents Department

Two-dimensional chord-wise load distributions at transonic speeds

Description: Report presenting testing on the NACA 16-009 airfoil and on eight airfoils of the NACA 6A series, which shows that the chordwise loading due to lift at a Mach number of 1.0 is insignificantly affected by thickness distribution within the range of airfoil shapes presented and only slightly affected by thickness. Results regarding the experimental loading on symmetrical airfoils, method of estimating pressure distribution, experimental loadings on cambered airfoils, and scope of method are provided.
Date: February 18, 1952
Creator: Lindsey, Walter F. & Dick, Richard S.
Partner: UNT Libraries Government Documents Department

Effect of horizontal-tail span and vertical location on the aerodynamic characteristics of an unswept tail assembly in sideslip

Description: "An investigation has been conducted in the Langley stability tunnel on a vertical-tail model with a stub fuselage in combination with various horizontal tails to determine the effect of horizontal-tail span and vertical location of the horizontal tail relative to the vertical tail on the aerodynamic characteristics of an unswept tail assembly in sideslip. The results of the investigation indicated that the induced loading carried by the horizontal tail produced a rolling moment about the point of attachment to the vertical tail which was strongly influenced by horizontal-tail span and vertical locations. The greatest effect of horizontal-tail span on the rolling-moment derivative of the complete tail assembly was obtained for horizontal-tail locations near the top of the vertical tail" (p. 351).
Date: December 24, 1952
Creator: Riley, Donald R.
Partner: UNT Libraries Government Documents Department

Theoretical basic span loading characteristics of wings with arbitrary sweep, aspect ratio, and taper ratio

Description: Note presenting a procedure based on the Weissinger method so that the basic span loading and associated aerodynamic characteristics can be rapidly predicted for wings having arbitrary values of sweep, aspect ratio, taper ratio, and twist. A method for correcting for the effects of compressibility is given. Results regarding the evaluation of the method, effect of plan-form variation on the basic loading characteristics, and a consideration of twist in swept-wing design are provided.
Date: December 1948
Creator: Stevens, Victor I.
Partner: UNT Libraries Government Documents Department

The effects of compressibility on the upwash at the propeller planes of a four-engine tractor airplane configuration having a wing with 40 degrees of sweepback and an aspect ratio of 10

Description: Report presenting an investigation in which upflow angles were measured along the horizontal center lines of the propeller planes of a semispan model representing a multiengine airplane with tractor propellers. Testing occurred at a range of Mach and Reynolds numbers. Results regarding the theoretical methods and a comparison of experimental and theoretical results are provided.
Date: July 1956
Creator: Lopez, Armendo E. & Dickson, Jerald K.
Partner: UNT Libraries Government Documents Department

A method for deflection analysis of thin low-aspect-ratio wings

Description: Report presenting a method for obtaining influence coefficients for thin low-aspect-ratio wings of built-up construction. Symmetric and anti-symmetric load-support conditions are considered. A simple method is given for taking account of attachment to a flexible fuselage.
Date: June 1956
Creator: Stein, Manuel & Sanders, J. Lyell, Jr.
Partner: UNT Libraries Government Documents Department

Generalized performance selection charts for single-engine pursuit airplanes

Description: Report presenting an investigation of the effect of wing loading, power loading, and aspect ratio on the performance of pursuit airplanes. The study is based on data combined from specifications, wind-tunnel, and flight tests of various airplanes and presented in graphs.
Date: February 1943
Creator: Ivey, H. Reese; Stickle, George W. & Brevoort, Maurice J.
Partner: UNT Libraries Government Documents Department

Flight measurements and calculations of wing loads and load distributions at subsonic, transonic, and supersonic speeds

Description: From Summary: "Presented in this report is a summary of local and net angle-of-attack wing-panel loads measured in flight on six airplanes. In addition, a comparison of these loads measured in flight with calculations based on simple theory is presented."
Date: July 2, 1957
Creator: Malvestudo, Frank S.; Cooney, Thomas V. & Keener, Earl R.
Partner: UNT Libraries Government Documents Department

The effect of spanwise mass distribution upon the spin characteristics of airplanes as determined by model tests conducted in the free-spinning wind tunnel

Description: Report presenting an investigation to determine whether the difference in the spanwise loading of the two types of aircraft were responsible for the differences in spin characteristics, particularly in regards to angle of attack.
Date: August 1942
Creator: Kamm, Robert W.
Partner: UNT Libraries Government Documents Department

Theory of aircraft structural models subject to aerodynamic heating and external loads

Description: Report examining the problem of investigating the simultaneous effects of transient aerodynamic heating and external loads on aircraft structures for the purpose of determining the ability of the structure to withstand flight to supersonic speeds.
Date: September 1957
Creator: O'Sullivan, William J., Jr.
Partner: UNT Libraries Government Documents Department

Aerodynamic problems in the design of efficient propellers

Description: From General Analysis: "The purpose of part I of this paper is to show how the loading that gives the minimum induced energy loss can be obtained from rather elementary considerations and to present design charts from which such a plan form can be quickly obtained for any set of design conditions."
Date: August 1942
Creator: Feldman, Lewis
Partner: UNT Libraries Government Documents Department

Torsion of wing trusses at diving speeds

Description: The purpose of this report is to indicate what effect the distortion of a typical loaded wing truss will have upon the load distribution. The case of high angle of incidence may be dismissed immediately from consideration as the loads on the front and rear trusses are balanced, and consequently there will be little angular distortion. A given angular distortion will have the maximum effect upon load distribution in the region of the angle of no-lift, because the slope of the lift curve is highest here, and it is here that the greatest angular distortion will occur, because the load on the front truss acts downward while the load on the rear truss acts upward.
Date: 1921
Creator: Miller, Roy G.
Partner: UNT Libraries Government Documents Department

Low-speed yawed-rolling characteristics and other elastic properties of a pair of 26-inch-diameter, 12-ply-rating, type VII aircraft tires

Description: Report presenting an investigation of the low-speed cornering characteristics of two 26 x 6.6, type VII, 12-ply-rating tires under straight-yawed rolling over a range of inflation pressures and yaw angles for two vertical loads. Static testing and vibration testing were also carried out. The quantities measured included lateral or cornering force, drag force, torsional moment or self-alining torque, pneumatic caster, vertical tire deflection, lateral tire deflection, wheel torsion or yaw angle, rolling radius, and relaxation length.
Date: May 1956
Creator: Horne, Walter B.; Smiley, Robert F. & Stephenson, Bertrand H.
Partner: UNT Libraries Government Documents Department