Theodorsen, Theodore
Overview
Works:  53 works in 86 publications in 1 language and 169 library holdings 

Roles:  Author 
Classifications:  TL501, 
Publication Timeline
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Most widely held works by
Theodore Theodorsen
Investigation of the diaphragmtype pressure cell by
Theodore Theodorsen(
Book
)
3 editions published in 1931 in English and held by 5 WorldCat member libraries worldwide
3 editions published in 1931 in English and held by 5 WorldCat member libraries worldwide
Mechanism of flutter : a theoretical and experimental investigation of the flutter problem by
Theodore Theodorsen(
Book
)
2 editions published in 1940 in English and held by 5 WorldCat member libraries worldwide
2 editions published in 1940 in English and held by 5 WorldCat member libraries worldwide
A condition on the initial shock by
Theodore Theodorsen(
Book
)
2 editions published between 1945 and 1946 in English and held by 4 WorldCat member libraries worldwide
2 editions published between 1945 and 1946 in English and held by 4 WorldCat member libraries worldwide
Propeller vibrations and the effect of the centrifugal force by
Theodore Theodorsen(
Book
)
1 edition published in 1935 in English and held by 4 WorldCat member libraries worldwide
1 edition published in 1935 in English and held by 4 WorldCat member libraries worldwide
Note on the theorems of Bjerknes and Crocco by
Theodore Theodorsen(
Book
)
2 editions published in 1946 in English and held by 4 WorldCat member libraries worldwide
The theorem of Bjerknes and Crocco are of great interest in the theory of flow around airfoils at Mach numbers near and above unity. A brief note shows how both theorems are developed by short vector transformations
2 editions published in 1946 in English and held by 4 WorldCat member libraries worldwide
The theorem of Bjerknes and Crocco are of great interest in the theory of flow around airfoils at Mach numbers near and above unity. A brief note shows how both theorems are developed by short vector transformations
The Problem of noise reduction with reference to light airplanes by
Theodore Theodorsen(
Book
)
2 editions published in 1946 in English and held by 4 WorldCat member libraries worldwide
Results of this study show that propeller noise dominates engine exhaust noise even though the exhaust noise has a relatively high intensity. It is concluded, therefore, that in order to reduce the outside sound level of an airplane materially, it will be necessary to modify the propeller to operate at low tip speeds and to have a large number of blades. The practical use of this conclusion is a matter of considerable technical complexity involving many compromises. An effective engine exhaust muffler will also be required
2 editions published in 1946 in English and held by 4 WorldCat member libraries worldwide
Results of this study show that propeller noise dominates engine exhaust noise even though the exhaust noise has a relatively high intensity. It is concluded, therefore, that in order to reduce the outside sound level of an airplane materially, it will be necessary to modify the propeller to operate at low tip speeds and to have a large number of blades. The practical use of this conclusion is a matter of considerable technical complexity involving many compromises. An effective engine exhaust muffler will also be required
Extension of the Chaplygin proofs on the existence of compressibleflow solutions to the supersonic region by
Theodore Theodorsen(
Book
)
2 editions published between 1945 and 1946 in English and held by 4 WorldCat member libraries worldwide
It has been known for some time that the velocity of sound is not the upper limit for potential flow. S. A. Chaplygin in his paper "On Gas Jets" (NACA TM No. 1063) carried out some interesting proofs on the existence of solutions and gave proofs relating to maxima and minima of certain functions. In the present paper these proofs are extended to include the supersonic potentialflow field adjacent to the subsonic region treated by Chaplygin
2 editions published between 1945 and 1946 in English and held by 4 WorldCat member libraries worldwide
It has been known for some time that the velocity of sound is not the upper limit for potential flow. S. A. Chaplygin in his paper "On Gas Jets" (NACA TM No. 1063) carried out some interesting proofs on the existence of solutions and gave proofs relating to maxima and minima of certain functions. In the present paper these proofs are extended to include the supersonic potentialflow field adjacent to the subsonic region treated by Chaplygin
Pressure distributions for representative airfoils and related profiles by
Theodore Theodorsen(
Book
)
2 editions published between 1945 and 1946 in English and held by 4 WorldCat member libraries worldwide
Selected pressuredistribution diagrams for a number of conventional and special airfoils are presented. The conventional airfoils include the NACA 22, 44, and 230series airfoils and the Clark Y family. The special airfoils consist of circulararc family. The special airfoils consists of circulararc sections of several thicknesses and curvatures and a number of synthetic airfoils , including several with zero moment coefficient. The pressure distributions are in most cases given for several lift coefficients including that at the ideal angle of attack
2 editions published between 1945 and 1946 in English and held by 4 WorldCat member libraries worldwide
Selected pressuredistribution diagrams for a number of conventional and special airfoils are presented. The conventional airfoils include the NACA 22, 44, and 230series airfoils and the Clark Y family. The special airfoils consist of circulararc family. The special airfoils consists of circulararc sections of several thicknesses and curvatures and a number of synthetic airfoils , including several with zero moment coefficient. The pressure distributions are in most cases given for several lift coefficients including that at the ideal angle of attack
General theory of aerodynamic instability and the mechanism of flutter by
Theodore Theodorsen(
Book
)
3 editions published between 1935 and 1940 in English and held by 3 WorldCat member libraries worldwide
3 editions published between 1935 and 1940 in English and held by 3 WorldCat member libraries worldwide
Flutter tests of modified SB2U model in 16foot tunnel by
Theodore Theodorsen(
Book
)
2 editions published in 1943 in English and held by 3 WorldCat member libraries worldwide
Test tests on the flutter characteristics of the SB2U model were conducted after the model had been modified so as to lower its flutter speed. This was done in order to insure the occurrence of normal flutter before anticipated skin failures. Such skin failure appeared imminent near top speed in the previous test series already reported. For this reason the wing torsion frequency was lowered from 1575 cycles per minute to 1330 cycles per minute. This latter value is closer to the originally intended model value and so also the flutter speed, predicted at about 125 miles per hour
2 editions published in 1943 in English and held by 3 WorldCat member libraries worldwide
Test tests on the flutter characteristics of the SB2U model were conducted after the model had been modified so as to lower its flutter speed. This was done in order to insure the occurrence of normal flutter before anticipated skin failures. Such skin failure appeared imminent near top speed in the previous test series already reported. For this reason the wing torsion frequency was lowered from 1575 cycles per minute to 1330 cycles per minute. This latter value is closer to the originally intended model value and so also the flutter speed, predicted at about 125 miles per hour
Experimental verification of the theory of windtunnel boundary interference by
Theodore Theodorsen(
Book
)
2 editions published in 1934 in English and held by 3 WorldCat member libraries worldwide
2 editions published in 1934 in English and held by 3 WorldCat member libraries worldwide
The theory of propellers. 3  The slipstream contraction with numerical values for twoblade and fourblade propellers by
Theodore Theodorsen(
Book
)
4 editions published between 1944 and 1947 in English and held by 3 WorldCat member libraries worldwide
As the conditions of the ultimate wake are of concern both theoretically and practically, the magnitude of the slipstream contraction has been calculated. It will be noted that the contraction in a representative case is of the order of only 1 percent of the propeller diameter. In consequence, all calculations need involve only firstorder effects. Curves and tables are given for the contraction coefficient of twoblade and fourblade propellers for various values of the advance ratio; the contraction coefficient is defined as the contraction in the diameter of the wake helix in terms of the wake diameter at infinity. The contour lines of the wake helix are also shown at four values of the advance ratio in comparison with the contour lines for an infinite number of blades
4 editions published between 1944 and 1947 in English and held by 3 WorldCat member libraries worldwide
As the conditions of the ultimate wake are of concern both theoretically and practically, the magnitude of the slipstream contraction has been calculated. It will be noted that the contraction in a representative case is of the order of only 1 percent of the propeller diameter. In consequence, all calculations need involve only firstorder effects. Curves and tables are given for the contraction coefficient of twoblade and fourblade propellers for various values of the advance ratio; the contraction coefficient is defined as the contraction in the diameter of the wake helix in terms of the wake diameter at infinity. The contour lines of the wake helix are also shown at four values of the advance ratio in comparison with the contour lines for an infinite number of blades
Effect of the lift coefficient on propeller flutter by
Theodore Theodorsen(
Book
)
4 editions published in 1945 in English and held by 3 WorldCat member libraries worldwide
Flutter of propellers at high angles of attack is discussed, and flutter data obtained in connection with tests of models of large windtunnel propellers are analyzed and results presented. It is shown that in the high angleofattack range flutter of a propeller invariably occurs at a speed substantially below the classical flutter speed. The angle of attack at which flutter occurs appears to be nearly constant and independent of the initial blade setting. Thus, the blade simply twists to the critical position and flutter starts. Formulas have been developed which give an operating angle in terms of the design angle and other associated parameters, and these relations are presented in the form of graphs. It is seen that the flutter speed is lowered as the initial design lift coefficient is increased. It is further shown that by use of a proper camber of the propeller section the flutter speed may approach the classical value. A camber for which the blade will not twist is found to exist, and the corresponding lift coefficient is shown to be of special significance
4 editions published in 1945 in English and held by 3 WorldCat member libraries worldwide
Flutter of propellers at high angles of attack is discussed, and flutter data obtained in connection with tests of models of large windtunnel propellers are analyzed and results presented. It is shown that in the high angleofattack range flutter of a propeller invariably occurs at a speed substantially below the classical flutter speed. The angle of attack at which flutter occurs appears to be nearly constant and independent of the initial blade setting. Thus, the blade simply twists to the critical position and flutter starts. Formulas have been developed which give an operating angle in terms of the design angle and other associated parameters, and these relations are presented in the form of graphs. It is seen that the flutter speed is lowered as the initial design lift coefficient is increased. It is further shown that by use of a proper camber of the propeller section the flutter speed may approach the classical value. A camber for which the blade will not twist is found to exist, and the corresponding lift coefficient is shown to be of special significance
Vibrationresponse tests of a 1/5scale model of the Grumman F6F airplane in the Langley 16foot highspeed tunnel by
Theodore Theodorsen(
Book
)
2 editions published in 1944 in English and held by 3 WorldCat member libraries worldwide
A series of vibration experiments was conducted in the Langley 16foot highspeed tunnel on a 1/5scale model on the Grumman F6F airplane. These tests were conducted to study the vibration responses of the model at airspeeds within the range of the tunnel, or up to approximately 500 miles per hour. Within this range, there was no indication of actual flutter either by shift of frequencies or by decreasing damping. The response curves are given in a series of graphs
2 editions published in 1944 in English and held by 3 WorldCat member libraries worldwide
A series of vibration experiments was conducted in the Langley 16foot highspeed tunnel on a 1/5scale model on the Grumman F6F airplane. These tests were conducted to study the vibration responses of the model at airspeeds within the range of the tunnel, or up to approximately 500 miles per hour. Within this range, there was no indication of actual flutter either by shift of frequencies or by decreasing damping. The response curves are given in a series of graphs
The Theory of Propellers. 3  The Slipstream Contraction with Numerical Values for TwoBlade and FourBlade Propellers(
Book
)
2 editions published in 1944 in English and held by 3 WorldCat member libraries worldwide
2 editions published in 1944 in English and held by 3 WorldCat member libraries worldwide
Nonstationary flow about a wingailerontab combination including aerodynamic balance by
Theodore Theodorsen(
Book
)
1 edition published in 1942 in English and held by 3 WorldCat member libraries worldwide
1 edition published in 1942 in English and held by 3 WorldCat member libraries worldwide
Airfoilcontour modifications based on (epsilon)curve method of calculating pressure distribution by
Theodore Theodorsen(
Book
)
1 edition published in 1944 in English and held by 2 WorldCat member libraries worldwide
A method, based directly on the socalled epsiloncurve method published originally in 1931 in NACA Report No. 411, is presented for use in making modifications to the shape and pressure distribution of a given airfoil. In particular, it may be desirable to remove excessive irregularities or local peaks in the distribution. In this process it may be required that certain parameters of the airfoil be kept unchanged; for instance, the angle of zero lift, the ideal lift coefficient, or the moment coefficient. From and academic viewpoint, an altered distribution cannot be "prescribed" because compliance with the requirement of maintaining a Laplacian flow field is involved. A prescribed distribution can therefore not be obtained by iteration. The process, however adequate, is necessarily one of qualitative modifications. Several numerical samples illustrating the use of the method are given in the appendix
1 edition published in 1944 in English and held by 2 WorldCat member libraries worldwide
A method, based directly on the socalled epsiloncurve method published originally in 1931 in NACA Report No. 411, is presented for use in making modifications to the shape and pressure distribution of a given airfoil. In particular, it may be desirable to remove excessive irregularities or local peaks in the distribution. In this process it may be required that certain parameters of the airfoil be kept unchanged; for instance, the angle of zero lift, the ideal lift coefficient, or the moment coefficient. From and academic viewpoint, an altered distribution cannot be "prescribed" because compliance with the requirement of maintaining a Laplacian flow field is involved. A prescribed distribution can therefore not be obtained by iteration. The process, however adequate, is necessarily one of qualitative modifications. Several numerical samples illustrating the use of the method are given in the appendix
The theory of propellers. 1  Determination of the circulation function and the mass coefficient for dualrotating propellers by
Theodore Theodorsen(
Book
)
3 editions published in 1944 in English and held by 2 WorldCat member libraries worldwide
Values of the circulation function have been obtained for dualrotating propellers. Numerical values are given for four, eight, and twelveblade dualrotating propellers and for advance ratios from 2 to about 6. In addition, the circulation function has been determined for singlerotating propellers for the higher values of the advance ratio. The mass coefficient, another quantity of significance in propeller theory, has been introduced. This mass coefficient, which is actually the mean value of the circulation coefficient, expresses the effective area of the column of the medium acted upon by the propeller in terms of the propellerdisk area. Values of the mass coefficient, which have been determined directly by special measurements and also by integration of the circulation function, are given for the four, eight, and twelveblade dualrotating propellers. The mass coefficient has also been determined for several cases of singlerotating propellers, partly for the purpose of comparing such experimental values with theoretical results in the known range of low advance ratios and partly to extend the results to include a range of high advance ratios. The effect of stationary countervanes on the mass coefficient has also been determined for several cases of practical interest
3 editions published in 1944 in English and held by 2 WorldCat member libraries worldwide
Values of the circulation function have been obtained for dualrotating propellers. Numerical values are given for four, eight, and twelveblade dualrotating propellers and for advance ratios from 2 to about 6. In addition, the circulation function has been determined for singlerotating propellers for the higher values of the advance ratio. The mass coefficient, another quantity of significance in propeller theory, has been introduced. This mass coefficient, which is actually the mean value of the circulation coefficient, expresses the effective area of the column of the medium acted upon by the propeller in terms of the propellerdisk area. Values of the mass coefficient, which have been determined directly by special measurements and also by integration of the circulation function, are given for the four, eight, and twelveblade dualrotating propellers. The mass coefficient has also been determined for several cases of singlerotating propellers, partly for the purpose of comparing such experimental values with theoretical results in the known range of low advance ratios and partly to extend the results to include a range of high advance ratios. The effect of stationary countervanes on the mass coefficient has also been determined for several cases of practical interest
The theory of propellers by
Theodore Theodorsen(
Book
)
2 editions published in 1944 in English and held by 1 WorldCat member library worldwide
A technical method is given for calculating the axial interference velocity of a propeller. The method involves the use of certain weight functions P, Q, and F. Numerical values for the weight functions are given for twoblade, threeblade, and sixblade propellers
2 editions published in 1944 in English and held by 1 WorldCat member library worldwide
A technical method is given for calculating the axial interference velocity of a propeller. The method involves the use of certain weight functions P, Q, and F. Numerical values for the weight functions are given for twoblade, threeblade, and sixblade propellers
Airfoilcontour modifications based on [epsilon]curve method of calculating pressure distribution by
Theodore Theodorsen(
Book
)
2 editions published in 1944 in English and held by 1 WorldCat member library worldwide
A method, based directly on the socalled [epsilon]curve method published originally in 1931 in NACA Report No. 411, is presented for use in making modifications to the shape and pressure distribution of a given airfoil. In particular, it may be desirable to remove excessive irregularities or local peaks in the distribution. In this process it may be required that certain parameters of the airfoil be kept unchanged; for instance, the angle of zero lift, the ideal lift coefficient, or the moment coefficient. From an academic viewpoint, an altered distribution cannot be "prescribed" because compliance with the requirement of maintaining a Laplacian flow field is involved. A prescribed distribution can therefore not be obtained by iteration. The process, however adequate, is necessarily one of qualitative modifications. Several numerical examples illustrating the use of the method are given in the appendix
2 editions published in 1944 in English and held by 1 WorldCat member library worldwide
A method, based directly on the socalled [epsilon]curve method published originally in 1931 in NACA Report No. 411, is presented for use in making modifications to the shape and pressure distribution of a given airfoil. In particular, it may be desirable to remove excessive irregularities or local peaks in the distribution. In this process it may be required that certain parameters of the airfoil be kept unchanged; for instance, the angle of zero lift, the ideal lift coefficient, or the moment coefficient. From an academic viewpoint, an altered distribution cannot be "prescribed" because compliance with the requirement of maintaining a Laplacian flow field is involved. A prescribed distribution can therefore not be obtained by iteration. The process, however adequate, is necessarily one of qualitative modifications. Several numerical examples illustrating the use of the method are given in the appendix
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Aerodynamic load Aerodynamics, Supersonic AerodynamicsResearch Aerofoils AeronauticsResearch Ailerons Air flow AirplanesDesign and construction AirplanesModelsTesting AirplanesMotorsMufflers AirplanesNoise AirplanesTesting Angle of attack (Aerodynamics) Charts, diagrams, etc Flutter (Aerodynamics) Lift (Aerodynamics) Mathematics Noise control Numerical analysis Oscillating wings (Aerodynamics) Propellers Propellers, Aerial Propellers, AerialNoise Shock waves Vibration (Aeronautics) Wind tunnels Wind tunnel testing
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