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Experiments on Drag of Revolving Disks, Cylinders and Streamline Rods at High Speeds

Description: Report presenting an experimental investigation concerned primarily with the extension of test data on the drag of revolving disks, cylinders, and streamline rods to high Mach numbers and Reynolds numbers. The tests generally confirm earlier theories and add in some new results. One of the primary findings of interest is that skin friction does not depend on Mach number.
Date: June 1944
Creator: Theodorsen, Theodore & Regier, Arthur
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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Flight Studies of the Horizontal-Tail Loads Experienced by a Fighter Airplane in Abrupt Maneuvers

Description: Report presenting flight measurements made on a modern pursuit airplane to determine the approximate magnitude of the horizontal tail loads in accelerated flight. Pressures at a few points were used as an index of the tail loads by correlating these pressures with complete pressure-distribution data obtained in the NACA full-scale tunnel.
Date: June 1944
Creator: Flight Research Maneuvers Section
Partner: UNT Libraries Government Documents Department
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A general representation for axial-flow fans and turbines

Description: From Summary: "A general representation of fan and turbine arrangements on a single classification chart is presented which is made possible by a particular definition of the stage of an axial-flow fan or turbine. Several unconventional fan and turbine arrangements are indicated and the applications of these arrangements are discussed."
Date: June 1945
Creator: Perl, W. & Tucker, M.
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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A study of the application of data on various types of flap to the design of fighter brakes

Description: Report presenting an approximate method of applying the available data on various types of flaps in the design of fighter brakes together with several examples of its use. The computed effects of flap type, size, location, and deflection as well as the effects of altitude and initial velocities on braking characteristics are also shown in some examples using the method to determine various flap arrangements.
Date: June 1942
Creator: Purser, Paul E.
Partner: UNT Libraries Government Documents Department
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Wind-tunnel investigation of control-surface characteristics 6: a 30-percent-chord plain flap on the NACA 0015 airfoil

Description: Report presenting force-test measurements in two-dimensional flow in the 4- by 6-foot vertical tunnel of the characteristics of an NACA 0015 airfoil equipped with a plain flap with a chord 30 percent of the airfoil chord and a plain tab with a chord 20 percent of the flap chord. Results regarding lift, hinge moment of flap, pitching moment, drag, and tab characteristics are provided.
Date: June 1942
Creator: Sears, Richard I. & Liddell, Robert B.
Partner: UNT Libraries Government Documents Department
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Wind-tunnel investigation of control-surface characteristics 1: effect of gap on the aerodynamic characteristics of an NACA 0009 airfoil with a 30-percent-chord plain flap

Description: From Summary: "Tests have been made to determine the effect of a gap at the flap nose upon the aerodynamic section characteristics of an NACA 0009 airfoil with a plain flap and tab. The results are presented in the form of airfoil and flap section characteristics for several flap deflections, tab deflections, and for four sizes of gap."
Date: June 1941
Creator: Sears, Richard I.
Partner: UNT Libraries Government Documents Department
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Wind-tunnel investigation of an NACA 23012 airfoil with a 30 percent chord Maxwell slate and with trailing-edge flaps

Description: Report presenting an investigation in the 7- by 10-foot wind tunnel of an NACA 23012 airfoil with a 30 percent-chord Maxwell leading-edge slat and a slotted and a split flap. The main purpose was to determine the optimum slot cap of the Maxwell slat for, and the aerodynamic section characteristics of, the airfoil with several deflections for both types of flaps. Curves of lift, drag, and pitching-moment characteristics for optimum arrangements are provided.
Date: June 1941
Creator: Lowry, John G. & McKee, John W.
Partner: UNT Libraries Government Documents Department
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Resume of Hinge-Moment Data for Unshielded Horn- Balanced Control Surfaces

Description: Report summarizes the available hinge-moment data for unshielded horn-balanced control surfaces. The purpose is to correlate the available data to assist with estimating the balance characteristics for use in the design and alteration of control surfaces with horn balances. Plan forms and variation of incremental hinge-moment-coefficient slopes with balance coefficients are presented.
Date: June 1943
Creator: Lowry, John G.
Partner: UNT Libraries Government Documents Department
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Drag measurements at high Reynolds numbers of a 100-inch-chord NACA 23016 practical construction wing section submitted by Chance Vought Aircraft Company

Description: Report presenting drag measurements in the two-dimensional low-turbulence tunnel of an available 100-inch-chord model of the NACA 23016 wing section. Results regarding the curves of section drag coefficient plotted against Reynolds number for various surface conditions and lift coefficients, variation of drag coefficient with lift coefficient, and effects of skin friction are provided.
Date: June 1944
Creator: von Doenhoff, Albert E. & Nuber, Robert J.
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation of a Plain and a Slot-Lip Aileron on a Wing With a Full-Span Flap Consisting of an Inboard Fowler and an Outboard Slotted Flap

Description: Report presenting an investigation of a slot-lip aileron and a plain aileron, singly and in combination, on an NACA 23012 wing with a full-span flap. The characteristics of these lateral-control devices were essentially the same as those of similar devices on the wing with full-span NACA slotted flaps as tested in a previous investigation.
Date: June 1941
Creator: Rogallo, F. M. & Schuldenfrei, Marvin
Partner: UNT Libraries Government Documents Department
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Calculation of Stick Forces for an Elevator With a Spring Tab

Description: "Formulas for the calculation of hinge-moment characteristics of an elevator with a spring tab have been developed in terms of basic aerodynamic parameters, spring stiffness, and airspeed. The formulas have been used in a study of the stick-force gradients on a pursuit airplane equipped with an elevator with a spring tab. Charts are presented showing the variation of stick-force gradient in accelerated flight over a large range of speed and the complete range of spring stiffness for various cen… more
Date: June 1944
Creator: Greenberg, Harry
Partner: UNT Libraries Government Documents Department
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Wind-tunnel tests of ailerons at various speeds 2: ailerons of 0.20 airfoil chord and true contour with 0.60 aileron-chord sealed internal balance on the NACA 66,2-216 airfoil

Description: Report presenting hinge-moment, lift, pressure difference across the balance, and pressure-distribution measurements in the two-dimensional test section of the stability tunnel on a 0.60 aileron-chord sealed internal-balance aileron on a specified NACA airfoil. The primary test objective was to determine the effect of speed on the action of the aileron.
Date: June 1943
Creator: Denaci, H. G. & Bird, J. D.
Partner: UNT Libraries Government Documents Department
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Wind Tunnel Tests of Ailerons at Various Speeds 1: Ailerons of 0.20 Airfoil Chord and True Contour With 0.35 Aileron-Chord Extreme Blunt Nose Balance on the NACA 66,2-216 Airfoil

Description: "Hinge-moment, lift, and pressure-distribution measurements were made in the two-dimensional test section of the NACA stability tunnel on a blunt-nose balance-type aileron on an NACA 66,2-216 airfoil at speeds up to 360 miles per hour corresponding to a Mach number of 0.475. The tests were made primarily to determine the effect of speed on the action of this type of aileron. The balance-nose radii of the aileron were varied from 0 to 0.02 of the airfoil chord and the gap width was varied from 0… more
Date: June 1943
Creator: Letko, W.; Denaci, H. G. & Freed, C.
Partner: UNT Libraries Government Documents Department
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Application of Balancing Tabs to Ailerons

Description: Analysis was made to determine characteristics required of a balancing-tab system for ailerons in order to reduce aileron stick forces to any desired magnitude. Series of calculations based on section data were made to determine balancing-tab systems of various chord tabs and ailerons that will give, for a particular airplane, zero rate of aileron hinge moment with aileron deflection and yet will produce same maximum rate of roll as a plain unbalanced 15-percent chord aileron of same span. Effe… more
Date: June 1942
Creator: Sears, Richard I.
Partner: UNT Libraries Government Documents Department
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Tire friction coefficients and their relation to ground-run distance in landing

Description: Report presenting a summary of published information on braking friction coefficients. Analysis indicates that the magnitude of the friction coefficient available will affect the technique required for obtaining the shortest ground run only under extreme conditions.
Date: June 1942
Creator: Gustafson, F. B.
Partner: UNT Libraries Government Documents Department
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An investigation of aircraft heaters 16: determination of the viscosity of exhaust gases from a gasoline engine

Description: Report presenting an investigation which found that the absolute viscosity of exhaust gases from a gasoline engine was measured at a range of temperatures and compositions. Results regarding preliminary runs, calibration runs at room temperature, check runs at medium temperatures, and exhaust gas measurements are provided.
Date: June 1944
Creator: Boelter, L. M. K. & Sharp, W. H.
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation of Control-Surface Characteristics 22: Medium and Large Aerodynamic Balances of Two Nose Shapes and a Plain Overhang Used With a 0.20-Airfoil-Chord Flap on an NACA 0009 Airfoil

Description: "Blunt-nose and elliptical-nose overhangs of 0.35 and 0.50 flap chord and a plain overhang on a flap having a chord of 0.20 airfoil chord have been tested in two-dimensional flow on an NACA 0009 airfoil. The results of the tests are presented as aerodynamic section characteristics for several flap deflections with the gap at the flap nose sealed or unsealed. Tests were made also to determine the effectiveness of a tab of 0.20 flap chord on the plain sealed flap and on a sealed flap having an el… more
Date: June 1945
Creator: Riebe, John M. & McKinney, Elizabeth G.
Partner: UNT Libraries Government Documents Department
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Wind-tunnel investigation of control-surface characteristics 19: a double flap with an overhang and an internal aerodynamic balance

Description: Report presenting wind-tunnel tests in two-dimensional flow to investigate the aerodynamic characteristics of a double flap with an internal and overhang balance. Three sizes of each type of balance were tested with three relative rates of deflection of the two flaps. Results regarding lift, hinge moment, drag, and pitching moment are provided.
Date: June 1944
Creator: Liddell, Robert B.
Partner: UNT Libraries Government Documents Department
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Effect of fabric deflection at high speeds on the aerodynamic characteristics of the horizontal tail surface of an SB2D-1 airplane

Description: Report presenting an investigation of a full-scale horizontal tail surface to determine the elevator-fabric deflection at high speeds and the aerodynamic effects of the fabric deflection. Two fabric-covered elevators differing only in rib spacing and a solid wooden elevator were tested. Results regarding fabric deflection and aerodynamic characteristics are provided.
Date: June 1945
Creator: Schueller, Carl F.
Partner: UNT Libraries Government Documents Department
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Effect of elevator-profile modifications and trailing-edge strips on elevator hinge-moment and other aerodynamic characteristics of a full-scale horizontal tail surface

Description: Report presenting results of a full-scale horizontal tail surface made to determine the effect of elevator-profile modifications and trailing-edge strips on the elevator hinge-moment characteristics for elevators having fixed plan plan form and constant balance. Results regarding the basic data with the metal elevator, effect of trailing-edge angle, effect of nose shape, and effects of trailing-edge strips are provided.
Date: June 1945
Creator: Schueller, Carl F.; Korycinski, Peter F. & Strass, H. Kurt
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation of Control-Surface Characteristics 14: NACA 0009 Airfoil With a 20-Percent-Chord Double Plain Flap

Description: Report discusses the results of force testing of the aerodynamic characteristics of an NACA 0009 airfoil with a double plain flap; it consisted of a plain forward flap with a chord 20 percent of the airfoil chord and a plan rearward flap with a chord 15 percent of the airfoil chord. Comparisons were made to the characteristics of a 0.50c single plain flap. The lift, hinge moments, drag, and pitching moments are described.
Date: June 1943
Creator: Sears, Richard I. & Purser, Paul E.
Partner: UNT Libraries Government Documents Department
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