Langley Aeronautical Laboratory
Overview
Works:  1,480 works in 2,092 publications in 1 language and 5,437 library holdings 

Classifications:  TL574.F6, 629.1 
Publication Timeline
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Most widely held works about
Langley Aeronautical Laboratory
 Engineer in charge a history of the Langley Aeronautical Laboratory, 19171958 by James R Hansen( Book )
 Historical perspectives on thermostructural research at the NACA Langley Aeronautical Laboratory from 1948 to 1958 by Richard R Heldenfels( Book )
 Subcommittee hearing on H.R. 6336, to promote the national defense by authorizing the construction of aeronautical research facilities by the National Advisory Committee for Aeronautics necessary to the effective prosecution of aeronautical research by United States( Book )
 Full committee hearing on H.R. 6319, H.R. 5990, H.R. 6203, H.R. 6336, H.R. 4511 by United States( Book )
 From biplanes to Apollo : the NASA Langley Historic District by Joseph R Chambers( Book )
 by Melvin N Gough( )
 by Robert R Gilruth( )
 by Blake W Corson( )
 by Christopher C Kraft( )
 Status of NACA research applicable to personal aircraft by United States( Book )
 Papers by Christopher C Kraft( )
 NACALMAL and you by Langley Aeronautical Laboratory( Book )
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Most widely held works by
Langley Aeronautical Laboratory
Aerodynamic theory and its application to flutter by
Langley Aeronautical Laboratory(
Book
)
1 edition published in 1956 in English and held by 28 WorldCat member libraries worldwide
1 edition published in 1956 in English and held by 28 WorldCat member libraries worldwide
Recent research on the determination of natural modes and frequencies of aircraft wing structures by
Langley Aeronautical Laboratory(
Book
)
2 editions published in 1956 in English and held by 27 WorldCat member libraries worldwide
2 editions published in 1956 in English and held by 27 WorldCat member libraries worldwide
Analysis of factors affecting net lift increment attainable with trailingedge split flaps on tailless airplanes by
Marvin Pitkin(
Book
)
in English and held by 4 WorldCat member libraries worldwide
An analysis has been made of factors affecting the net lift increment attainable with trailingedge split flaps on tailless airplanes. The flaps investigated in the analysis were designed to contribute zero pitching moments about the wing aerodynamic center when deflected. Calculations were made of the lift and pitchingmoment characteristics of flaps of this type over a range of design conditions in which sweepback angle, aspect ratio, taper ratio, flap chord, and flap deflection were widely varied. In addition, calculations were made to determine the effect of the various parameters upon the loss in lift incurred in trimming the stability moments of a tailless airplane. A method is given for roughly estimating the maximum lift coefficient of tailless airplanes
in English and held by 4 WorldCat member libraries worldwide
An analysis has been made of factors affecting the net lift increment attainable with trailingedge split flaps on tailless airplanes. The flaps investigated in the analysis were designed to contribute zero pitching moments about the wing aerodynamic center when deflected. Calculations were made of the lift and pitchingmoment characteristics of flaps of this type over a range of design conditions in which sweepback angle, aspect ratio, taper ratio, flap chord, and flap deflection were widely varied. In addition, calculations were made to determine the effect of the various parameters upon the loss in lift incurred in trimming the stability moments of a tailless airplane. A method is given for roughly estimating the maximum lift coefficient of tailless airplanes
An electromagneticanalogy method of solving liftingsurfacetheory problems by
Robert S Swanson(
Book
)
3 editions published in 1945 in English and held by 4 WorldCat member libraries worldwide
A method is suggested for making liftingsurface calculations by means of magnetic measurements of an electromagneticanalogy model. The method is based on the perfect analogy between the strength of the magnetic field around a conductor and the strength of the inducedvelocity field around a vortex. Electric conductors are arranged to represent the vortex sheet. The magneticfield string is determined by measuring, with an electronic voltmeter, the voltage induced in a small search coil by the alternating current in the wires representing the vortex sheet
3 editions published in 1945 in English and held by 4 WorldCat member libraries worldwide
A method is suggested for making liftingsurface calculations by means of magnetic measurements of an electromagneticanalogy model. The method is based on the perfect analogy between the strength of the magnetic field around a conductor and the strength of the inducedvelocity field around a vortex. Electric conductors are arranged to represent the vortex sheet. The magneticfield string is determined by measuring, with an electronic voltmeter, the voltage induced in a small search coil by the alternating current in the wires representing the vortex sheet
Note on the importance of imperfectgas effects and variation of heat capacities on the isentropic flow of gases by
Coleman duP Donaldson(
Book
)
2 editions published in 1948 in English and held by 4 WorldCat member libraries worldwide
Abstract: The errors involved in using the perfectgas law pv=RT and the assumption of constant heat capacities are evaluated. The basic equations of gas flows taking into account these phenomena separately and at the same time are presented
2 editions published in 1948 in English and held by 4 WorldCat member libraries worldwide
Abstract: The errors involved in using the perfectgas law pv=RT and the assumption of constant heat capacities are evaluated. The basic equations of gas flows taking into account these phenomena separately and at the same time are presented
Heat transfer and skin friction for turbulent boundary layers on heated or cooled surfaces at high speeds by
Coleman duP Donaldson(
Book
)
2 editions published in 1952 in English and held by 4 WorldCat member libraries worldwide
Abstract: The method presented in NACA TN 2692 for evaluating the skin friction of a turbulent boundary layer in compressible flow on an insulated surface is extended to evaluate the turbulent skin friction and heat transfer in compressible flow on a surface which is heated or cooled. The results of this analysis are in good agreement with the heat transfers measured in flight on the NACA RM10 missile up to Mach number of 3.8
2 editions published in 1952 in English and held by 4 WorldCat member libraries worldwide
Abstract: The method presented in NACA TN 2692 for evaluating the skin friction of a turbulent boundary layer in compressible flow on an insulated surface is extended to evaluate the turbulent skin friction and heat transfer in compressible flow on a surface which is heated or cooled. The results of this analysis are in good agreement with the heat transfers measured in flight on the NACA RM10 missile up to Mach number of 3.8
Comparison of yaw characteristics of a singleengine airplane model with singlerotating and dualrotating propellers by R. H Neely(
Book
)
3 editions published in 1944 in English and held by 4 WorldCat member libraries worldwide
Tests were made n the NACA 29foot pressure tunnel to determine the yaw characteristics of a 0.32scale model of a singleengine, fightertype airplane with sixblade singlerotating and dualrotating propellers. The propellers used in the investigation were of the same solidity and plan form. Force and moment characteristics of the model, with the exception of the rollingmoment characteristics, are presented for several model and power conditions. Curves are given that show estimated ruddercontrol characteristics of the design airplane in steady sideslips
3 editions published in 1944 in English and held by 4 WorldCat member libraries worldwide
Tests were made n the NACA 29foot pressure tunnel to determine the yaw characteristics of a 0.32scale model of a singleengine, fightertype airplane with sixblade singlerotating and dualrotating propellers. The propellers used in the investigation were of the same solidity and plan form. Force and moment characteristics of the model, with the exception of the rollingmoment characteristics, are presented for several model and power conditions. Curves are given that show estimated ruddercontrol characteristics of the design airplane in steady sideslips
Tables and charts for the evaluation of profile drag from wake surveys at high subsonic speeds by
Myron J Block(
Book
)
3 editions published in 1945 in English and held by 3 WorldCat member libraries worldwide
Tables and charts for the evaluation of profile drag from wake surveys at high subsonic speeds are presented. These tables and charts are for use with two methods of evaluation, an exact method that may be applied to wakes of any shape and a simple approximate method that may be applied when the variation of totalpressure loss across the wake has the typical form (resembling a cycle of a cosinesquared curve)
3 editions published in 1945 in English and held by 3 WorldCat member libraries worldwide
Tables and charts for the evaluation of profile drag from wake surveys at high subsonic speeds are presented. These tables and charts are for use with two methods of evaluation, an exact method that may be applied to wakes of any shape and a simple approximate method that may be applied when the variation of totalpressure loss across the wake has the typical form (resembling a cycle of a cosinesquared curve)
Propellers in yaw by
H. S Ribner(
Book
)
3 editions published in 1943 in English and held by 3 WorldCat member libraries worldwide
It was realized as early as 1909 that a propeller in yaw develops a side force like that of a fin. In 1917, R.G. Harris expressed this force in terms of the torque coefficient for the unyawed propeller. Of several attempts to express the side force directly in terms of the shape of the blades, however, none has been completely satisfactory. An analysis that incorporates induction effects not adequately covered in previous work and that gives good agreement with experiment over a wide range of operating conditions is presented herein. The present analysis shows that the fin analogy may be extended to the form of the sideforce expression and that the effective fin area may be taken as the projected side area of the propeller. The effective aspect ratio is of the order of 8 and the appropriate dynamic pressure is roughly that at the propeller disk as augmented by the inflow. The variation of the inflow velocity, for a fixedpitch propeller, accounts for most of the variation of side force with advancediameter ration V/nD
3 editions published in 1943 in English and held by 3 WorldCat member libraries worldwide
It was realized as early as 1909 that a propeller in yaw develops a side force like that of a fin. In 1917, R.G. Harris expressed this force in terms of the torque coefficient for the unyawed propeller. Of several attempts to express the side force directly in terms of the shape of the blades, however, none has been completely satisfactory. An analysis that incorporates induction effects not adequately covered in previous work and that gives good agreement with experiment over a wide range of operating conditions is presented herein. The present analysis shows that the fin analogy may be extended to the form of the sideforce expression and that the effective fin area may be taken as the projected side area of the propeller. The effective aspect ratio is of the order of 8 and the appropriate dynamic pressure is roughly that at the propeller disk as augmented by the inflow. The variation of the inflow velocity, for a fixedpitch propeller, accounts for most of the variation of side force with advancediameter ration V/nD
Windtunnel investigation of effects of a pusher propeller on lift, profile drag, pressure distribution, and boundarylayer
transition of a flapped wing by
Carl A Sandahl(
Book
)
4 editions published in 1945 in English and held by 3 WorldCat member libraries worldwide
Some of the effects of pusherpropeller operation on the aerodynamic characteristics of a flapped wing were measured in the Langley propellerresearch tunnel. The effects of propeller operation on the lift and profile drag of the wing, on pressure distribution, and on the position of boundarylayer transition were obtained. The results indicated that, at fixed angles of attack and with flaps deflected, the wing lift increased appreciably with increasing thrust coefficient. With flaps retracted, no appreciable increase in lift with increases of thrust coefficient was measured. Chordwise pressure distributions at several spanwise stations indicated that the effect of propeller operation was greatest in the region immediately ahead of the propeller and that the effect extended outboard from the propeller axis for about 2.5 propeller radii. Measurements of boundarylayer velocity on the forward part of the upper surface of the wing showed no appreciable shift of transition in the range of thrust coefficients investigated
4 editions published in 1945 in English and held by 3 WorldCat member libraries worldwide
Some of the effects of pusherpropeller operation on the aerodynamic characteristics of a flapped wing were measured in the Langley propellerresearch tunnel. The effects of propeller operation on the lift and profile drag of the wing, on pressure distribution, and on the position of boundarylayer transition were obtained. The results indicated that, at fixed angles of attack and with flaps deflected, the wing lift increased appreciably with increasing thrust coefficient. With flaps retracted, no appreciable increase in lift with increases of thrust coefficient was measured. Chordwise pressure distributions at several spanwise stations indicated that the effect of propeller operation was greatest in the region immediately ahead of the propeller and that the effect extended outboard from the propeller axis for about 2.5 propeller radii. Measurements of boundarylayer velocity on the forward part of the upper surface of the wing showed no appreciable shift of transition in the range of thrust coefficients investigated
Langley fullscale tunnel investigation of the factors affecting the directional stability and trim characteristics of a fightertype
airplane by
Harold H Sweberg(
Book
)
3 editions published in 1945 in English and held by 3 WorldCat member libraries worldwide
Tests were made in the Langley fullscale tunnel of the Grumman XF6f4 airplane in order to investigate the factors that affect the directional stability and trim characteristics of a typical fightertype airplane. Eight representative flight conditions were investigated in detail. The separate contributions of the wingfuselage combination, the vertical tail, and the propeller to the directional stability of the airplane in each condition were determined. Extensive airflow surveys of sidewash angle and dynamicpressure ratio along a line coincident with the rudder hinge line were made for each condition investigated to air evaluating the slipstream effects. The data obtained from the airflow surveys were also used to investigate methods for calculating the contribution of the vertical tail to the airplane directional stability
3 editions published in 1945 in English and held by 3 WorldCat member libraries worldwide
Tests were made in the Langley fullscale tunnel of the Grumman XF6f4 airplane in order to investigate the factors that affect the directional stability and trim characteristics of a typical fightertype airplane. Eight representative flight conditions were investigated in detail. The separate contributions of the wingfuselage combination, the vertical tail, and the propeller to the directional stability of the airplane in each condition were determined. Extensive airflow surveys of sidewash angle and dynamicpressure ratio along a line coincident with the rudder hinge line were made for each condition investigated to air evaluating the slipstream effects. The data obtained from the airflow surveys were also used to investigate methods for calculating the contribution of the vertical tail to the airplane directional stability
Windtunnel tests of a bluntnose aileron with beveled trailing edge on an NACA 66(215)216 airfoil with several modification
of aileron nose and adjacent airfoil contour by
J. D Bird(
Book
)
3 editions published in 1945 in English and held by 3 WorldCat member libraries worldwide
Ailerons having a beveled trailing edge and a bluntnose overhang of 35 percent aileron chord on an NACA 66(215)216 airfoil have been tested in the twodimensionalflow test section of the Langley stability tunnel. Five configurations of the model were tested with various modifications of the aileron nose and adjacent airfoil contour to determine the effect of these modifications on the lift and the aileron hingemoment characteristics
3 editions published in 1945 in English and held by 3 WorldCat member libraries worldwide
Ailerons having a beveled trailing edge and a bluntnose overhang of 35 percent aileron chord on an NACA 66(215)216 airfoil have been tested in the twodimensionalflow test section of the Langley stability tunnel. Five configurations of the model were tested with various modifications of the aileron nose and adjacent airfoil contour to determine the effect of these modifications on the lift and the aileron hingemoment characteristics
Formulas for propellers in yaw and charts on the sideforce derivative by
H. S Ribner(
Book
)
3 editions published in 1943 in English and held by 3 WorldCat member libraries worldwide
General formulas are given for propellers for the rate of change of sideforce coefficient with angle of yaw and for the rate of change of pitchingmoment coefficient with angle of yaw. Charts of the sideforce derivative are given for two propellers of different plan form. The charts cover solidities of two to six blades and single and dual rotation. The blade angles range from 15 or 20 to 60. The equations, and the charts computed from the equations, are based on an unpublished analysis, which incorporates factors not adequately covered in previously published work and gives good agreement with experiment over a wide range of operating conditions. A study of the equations indicates that they are consistent with the following physical interpretation: In developing side force, the propeller acts like a fin of which the area is the projected side area of the propeller, the effective aspect ratio is of the order of 8, and the effective dynamic pressure is roughly that at the propeller disk as augmented by the inflow. The variation of the inflow velocity, for a fixedpitch propeller, accounts for most of the variation of side force with advancediameter ratio. The charts may be applied to obtain the rate of change of normalforce coefficient with angle of attack of the axis of rotation if proper account is taken of the upwash or downwash from the wing
3 editions published in 1943 in English and held by 3 WorldCat member libraries worldwide
General formulas are given for propellers for the rate of change of sideforce coefficient with angle of yaw and for the rate of change of pitchingmoment coefficient with angle of yaw. Charts of the sideforce derivative are given for two propellers of different plan form. The charts cover solidities of two to six blades and single and dual rotation. The blade angles range from 15 or 20 to 60. The equations, and the charts computed from the equations, are based on an unpublished analysis, which incorporates factors not adequately covered in previously published work and gives good agreement with experiment over a wide range of operating conditions. A study of the equations indicates that they are consistent with the following physical interpretation: In developing side force, the propeller acts like a fin of which the area is the projected side area of the propeller, the effective aspect ratio is of the order of 8, and the effective dynamic pressure is roughly that at the propeller disk as augmented by the inflow. The variation of the inflow velocity, for a fixedpitch propeller, accounts for most of the variation of side force with advancediameter ratio. The charts may be applied to obtain the rate of change of normalforce coefficient with angle of attack of the axis of rotation if proper account is taken of the upwash or downwash from the wing
Windtunnel tests of dualrotating propellers with systematic differences in number of blades, blade setting, and rotational
speed of front and rear propellers by
W. H Gray(
Book
)
3 editions published in 1944 in English and held by 3 WorldCat member libraries worldwide
The advent of dualrotating propellers has created a need for information concerning the effect of the number of blades of the front and rear propellers, relative rotational speeds, and small changes in the blade angles of the rear propeller. Results of aerodynamic tests of sevenblade propellers, which were considered as a possible arrangement to avoid vibration difficulties, are presented herein. Variations of relative blade angle and rotational speeds of the front and rear components of a sixblade dualrotating propeller were also investigated. The test program was an extension also investigated. The test program was an extension of previous work on dualrotating propellers at the NACA propellerresearch tunnel; the propeller blades and test body were those used in the previous tests
3 editions published in 1944 in English and held by 3 WorldCat member libraries worldwide
The advent of dualrotating propellers has created a need for information concerning the effect of the number of blades of the front and rear propellers, relative rotational speeds, and small changes in the blade angles of the rear propeller. Results of aerodynamic tests of sevenblade propellers, which were considered as a possible arrangement to avoid vibration difficulties, are presented herein. Variations of relative blade angle and rotational speeds of the front and rear components of a sixblade dualrotating propeller were also investigated. The test program was an extension also investigated. The test program was an extension of previous work on dualrotating propellers at the NACA propellerresearch tunnel; the propeller blades and test body were those used in the previous tests
Windtunnel investigation of an NACA 23021 airfoil with a 0.23airfoilchord double slotted flap by
Jack Fischel(
Book
)
3 editions published in 1944 in English and held by 3 WorldCat member libraries worldwide
An investigation was made in the LMAL 7 by 10foot wind tunnel of an NACA 23021 airfoil with a double slotted flap having a chord 32 percent of the airfoil chord (0.32c) to determine the aerodynamic section characteristics with the flaps deflected at various positions. The effects of moving the fore flap and rear flap as a unit and of deflecting or removing the lower lip of the slot were also determined
3 editions published in 1944 in English and held by 3 WorldCat member libraries worldwide
An investigation was made in the LMAL 7 by 10foot wind tunnel of an NACA 23021 airfoil with a double slotted flap having a chord 32 percent of the airfoil chord (0.32c) to determine the aerodynamic section characteristics with the flaps deflected at various positions. The effects of moving the fore flap and rear flap as a unit and of deflecting or removing the lower lip of the slot were also determined
A flight investigation of internally balanced sealed ailerons in the presence of a balanced split flap by
William Carlos Williams(
Book
)
4 editions published in 1942 in English and held by 3 WorldCat member libraries worldwide
Flight tests were made with a modified Eyan ST airplane to determine the effect of aileron characteristics of various arrangements of balanced split flaps covering that portion of the wing span occupied by the ailerons. NACA recording instruments were used to determine the aileron effectiveness
4 editions published in 1942 in English and held by 3 WorldCat member libraries worldwide
Flight tests were made with a modified Eyan ST airplane to determine the effect of aileron characteristics of various arrangements of balanced split flaps covering that portion of the wing span occupied by the ailerons. NACA recording instruments were used to determine the aileron effectiveness
Preliminary flight research on an allmovable horizontal tail as a longitudinal control for flight at high mach numbers by
Harold F Kleckner(
Book
)
3 editions published in 1945 in English and held by 3 WorldCat member libraries worldwide
The NACA is conducting flight tests of an allmovable horizontal tail installed on a Curtiss XP42 airplane because of its possible advantages as a longitudinal control for flight at high Mach numbers. The results are presented for some preliminary tests in the lowspeed range for which the tail was very closely balanced aerodynamically and a bobweight was used to obtain stable stickforce variations with speed and acceleration. For these tests, the tail was hinged at 0.24 chord and was tried with two arrangements of servotab control. The elevator control was found to be unsatisfactory with the control arrangements tested. Although there were sufficient variation of stick force with acceleration in steady turns and a stable stickforce variation with speed, the nearzero variation of stick force with stick deflection resulted in an extremely sensitive control that required continuous attention in order to avoid motions of the airplane due to inadvertent movements of the control stick. For subsequent tests, the servotabs are being connected as geared unbalancing tabs in order that more conventional elevator hingemoment characteristics may be obtained. The expected advantages of the allmovable tail with a control system utilizing tabs would of course be limited to flight at Mach numbers below those for which severe compressibility effects are encountered on the tail itself. For higher Mach numbers, the allmovable tail would require an irreversible powerboost control in order to handle the large hingemoment increases that are expected
3 editions published in 1945 in English and held by 3 WorldCat member libraries worldwide
The NACA is conducting flight tests of an allmovable horizontal tail installed on a Curtiss XP42 airplane because of its possible advantages as a longitudinal control for flight at high Mach numbers. The results are presented for some preliminary tests in the lowspeed range for which the tail was very closely balanced aerodynamically and a bobweight was used to obtain stable stickforce variations with speed and acceleration. For these tests, the tail was hinged at 0.24 chord and was tried with two arrangements of servotab control. The elevator control was found to be unsatisfactory with the control arrangements tested. Although there were sufficient variation of stick force with acceleration in steady turns and a stable stickforce variation with speed, the nearzero variation of stick force with stick deflection resulted in an extremely sensitive control that required continuous attention in order to avoid motions of the airplane due to inadvertent movements of the control stick. For subsequent tests, the servotabs are being connected as geared unbalancing tabs in order that more conventional elevator hingemoment characteristics may be obtained. The expected advantages of the allmovable tail with a control system utilizing tabs would of course be limited to flight at Mach numbers below those for which severe compressibility effects are encountered on the tail itself. For higher Mach numbers, the allmovable tail would require an irreversible powerboost control in order to handle the large hingemoment increases that are expected
Liftingsurfacetheory values of the damping in roll and of the parameter used in estimating aileron stick forces by
Robert S Swanson(
Book
)
3 editions published in 1945 in English and held by 3 WorldCat member libraries worldwide
An investigation was made by liftingsurface theory of a thin elliptic wing of aspect ratio 6 in a steady roll by means of the electromagneticanalogy method. From the results, aspectratio corrections for the damping in roll and aileron hinge moments for a wing in steady roll were obtained that are considerably more accurate than those given by liftingline theory. Firstorder effects of the compressibility were included in the computations
3 editions published in 1945 in English and held by 3 WorldCat member libraries worldwide
An investigation was made by liftingsurface theory of a thin elliptic wing of aspect ratio 6 in a steady roll by means of the electromagneticanalogy method. From the results, aspectratio corrections for the damping in roll and aileron hinge moments for a wing in steady roll were obtained that are considerably more accurate than those given by liftingline theory. Firstorder effects of the compressibility were included in the computations
Numerical evaluation by harmonic analysis of the epsilonfunction of the Theodorsen arbitraryairfoil potential theory by
Irven Naiman(
Book
)
3 editions published in 1945 in English and held by 3 WorldCat member libraries worldwide
Finite trigonometric series is fitted by harmonic analysis as an approximation function to the psi function of the Theodorsen arbitraryairfoil potential theory. By harmonic synthesis, the corresponding conjugate trigonometric series is used as an approximation to the epsilon function. A set of coefficients of particularly simple form is obtained algebraically for direct calculation of the epsilon values from the corresponding set of psi values. Complete derivation of this process is presented
3 editions published in 1945 in English and held by 3 WorldCat member libraries worldwide
Finite trigonometric series is fitted by harmonic analysis as an approximation function to the psi function of the Theodorsen arbitraryairfoil potential theory. By harmonic synthesis, the corresponding conjugate trigonometric series is used as an approximation to the epsilon function. A set of coefficients of particularly simple form is obtained algebraically for direct calculation of the epsilon values from the corresponding set of psi values. Complete derivation of this process is presented
Effect of compressibility on the hovering performance of two 10footdiameter helicopter rotors tested in the Langley fullscale
tunnel by
Joseph W Jewel(
Book
)
2 editions published in 1958 in English and held by 2 WorldCat member libraries worldwide
An investigation of the effects of compressibility on the hoveringperformance characteristics of two 10footdiameter helicopter rotors having solidities of approximately 10 percent has been conducted in the Langley fullscale tunnel. One rotor, having NACA 0012 airfoil sections, a planform taper ratio of 3/1, and 8 of twist, was tested to a tip Mach number of 0.95 and a disk loading of 16 pounds per square foot. The other rotor had NACA 64series airfoil sections, tapering to a 6centthick tip, a planform taper ration of 3/1, 16 of twist, and was tested to a tip Mach number of 1.0 and a disk loading of 20 pounds per square foot
2 editions published in 1958 in English and held by 2 WorldCat member libraries worldwide
An investigation of the effects of compressibility on the hoveringperformance characteristics of two 10footdiameter helicopter rotors having solidities of approximately 10 percent has been conducted in the Langley fullscale tunnel. One rotor, having NACA 0012 airfoil sections, a planform taper ratio of 3/1, and 8 of twist, was tested to a tip Mach number of 0.95 and a disk loading of 16 pounds per square foot. The other rotor had NACA 64series airfoil sections, tapering to a 6centthick tip, a planform taper ration of 3/1, 16 of twist, and was tested to a tip Mach number of 1.0 and a disk loading of 20 pounds per square foot
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Related Identities
 United States National Advisory Committee for Aeronautics
 United States National Aeronautics and Space Administration Scientific and Technical Information Office
 Hansen, James R. Author
 Langley Research Center
 Heldenfels, Richard R. Author
 Theodorsen, Theodore Author
 Zalovcik, John A. Author
 Donaldson, Coleman duP Author
 Pitkin, Marvin Author
 Garrick, I. E. (Isadore Edward) 19101981 Author
Associated Subjects
Acquisition of property AerodynamicsResearch Aerofoils Aeronautical laboratories Aeronautics Aeronautics, MilitaryResearch AeronauticsResearch Ailerons AirplanesWings Armed Forces (United States) Armed ForcesAppointments and retirements Armed ForcesOfficials and employees CaliforniaSan FranciscoPresidio of San Francisco Charts, diagrams, etc Civil defense Cleveland (Ohio) Compressibility Conveyancing Drag (Aerodynamics) Engineers Fighter planes Flaps (Airplanes) Flutter (Aerodynamics) Hampton (Va.) Hancock, Joy Bright, Kahului (Hawaii) Land titlesRegistration and transfer Langley Aeronautical Laboratory Lift (Aerodynamics) Manned Spacecraft Center (U.S.) Military research Outer space Project Mercury (U.S.) Propellers, Aerial Propellers, AerialTesting Propulsion Laboratory (U.S.) Research San Francisco (Calif.) Schenectady (N.Y.) Thermal stressesResearch United States United States.National Advisory Committee for Aeronautics United States.National Aeronautics and Space Administration United States.Naval Reserve.Women's Reserve United States.Navy United States.Navy Department Vibration (Aeronautics) Virginia Wind tunnel testing Yawing (Aerodynamics)
Alternative Names
Hampton (Va.). Langley Aeronautical Laboratory
Langley Air Force Base (Va.). Langley Aeronautical Laboratory
Langley Memorial Aeronautical Laboratory
National Aeronautics and Space Administration Langley Aeronautical Laboratory
United States. Langley Aeronautical Laboratory
United States. Langley Aeronautical Laboratory, Hampton, Va.
United States. Langley Memorial Aeronautical Laboratory
United States. National Advisory Committee for Aeronautics. Langley Aeronautical Laboratory
United States National Aeronautics and Space Administration Langley Aeronautical Laboratory
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