Theodorsen, Theodore
Overview
Works:  42 works in 78 publications in 1 language and 279 library holdings 

Roles:  Author 
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Most widely held works about
Theodore Theodorsen
 A modern view and appreciation of the works of Theodore Theodorsen, physicist and engineer : critical essays by Theodore Theodorsen( Book )
Most widely held works by
Theodore Theodorsen
The theory of propellers by
Theodore Theodorsen(
Book
)
13 editions published between 1944 and 1954 in English and held by 13 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
13 editions published between 1944 and 1954 in English and held by 13 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
A condition on the initial shock by
Theodore Theodorsen(
Book
)
2 editions published between 1945 and 1946 in English and held by 7 WorldCat member libraries worldwide
2 editions published between 1945 and 1946 in English and held by 7 WorldCat member libraries worldwide
The Prevention of ice formation on gasoline tank vents by
Theodore Theodorsen(
Book
)
2 editions published in 1931 in English and held by 7 WorldCat member libraries worldwide
This investigation was conducted in the refrigerated wind tunnel at the Langley Memorial Aeronautical Laboratory to determine a suitable method for preventing the formation of ice on the vents of airplane gasoline tanks
2 editions published in 1931 in English and held by 7 WorldCat member libraries worldwide
This investigation was conducted in the refrigerated wind tunnel at the Langley Memorial Aeronautical Laboratory to determine a suitable method for preventing the formation of ice on the vents of airplane gasoline tanks
Note on the theorems of Bjerknes and Crocco by
Theodore Theodorsen(
Book
)
2 editions published in 1946 in English and held by 6 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 6 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
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 6 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 6 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 5 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 5 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
Experiments on drag of revolving disks, cylinders, and streamline rods at high speeds by
Theodore Theodorsen(
Book
)
6 editions published in 1944 in English and held by 5 WorldCat member libraries worldwide
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 is presented
6 editions published in 1944 in English and held by 5 WorldCat member libraries worldwide
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 is presented
The Problem of noise reduction with reference to light airplanes by
Theodore Theodorsen(
Book
)
2 editions published in 1946 in English and held by 5 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 5 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
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
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
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
Vibration surveys of the P47B rudder and finrudder assembly by
Theodore Theodorsen(
Book
)
2 editions published in 1943 in English and held by 2 WorldCat member libraries worldwide
The present work was conducted in connection with a study of the flutter characteristics of the P47 tail assembly. The original fabriccovered rudder designated by "I" was subsequently replaced by a metalcovered rudder designated by "II." The fin was also somewhat reinforced and the vibration results on the combination of this reinforced fin and the metal rudder is given under III. This combination, which is now in use (April 1943), proved completely satisfactory from a vibration standpoint and has subsequently been tested in flight to a true speed of the order of 600 mile per hour. As a matter of record the vibration survey is therefore given
2 editions published in 1943 in English and held by 2 WorldCat member libraries worldwide
The present work was conducted in connection with a study of the flutter characteristics of the P47 tail assembly. The original fabriccovered rudder designated by "I" was subsequently replaced by a metalcovered rudder designated by "II." The fin was also somewhat reinforced and the vibration results on the combination of this reinforced fin and the metal rudder is given under III. This combination, which is now in use (April 1943), proved completely satisfactory from a vibration standpoint and has subsequently been tested in flight to a true speed of the order of 600 mile per hour. As a matter of record the vibration survey is therefore given
Flutter tests on SB2U model in 16foot tunnel by
Theodore Theodorsen(
Book
)
2 editions published in 1943 in English and held by 2 WorldCat member libraries worldwide
Tests were conducted in the 16foot NACA tunnel at Langley Field to determine the flutter characteristics of the SB2U2 airplane. These tests were originally planned as a desirable check of recommendations based on calculations and submitted to the Navy and the manufacturer subsequent to the occurrence of flutter in highspeed dives. The tests were also, at the time, considered as a useful check on the theory itself. A further purpose of the tests was to study the behavior of the airplane of the tests was to study the behavior of the airplane just below the flutter speed, a problem which has been the subject of much speculation on the practicability of flutter testing in flight. Since the validity of flutter calculations has been very well established since that time, the second object was, at present, considered the primary purpose of the tests
2 editions published in 1943 in English and held by 2 WorldCat member libraries worldwide
Tests were conducted in the 16foot NACA tunnel at Langley Field to determine the flutter characteristics of the SB2U2 airplane. These tests were originally planned as a desirable check of recommendations based on calculations and submitted to the Navy and the manufacturer subsequent to the occurrence of flutter in highspeed dives. The tests were also, at the time, considered as a useful check on the theory itself. A further purpose of the tests was to study the behavior of the airplane of the tests was to study the behavior of the airplane just below the flutter speed, a problem which has been the subject of much speculation on the practicability of flutter testing in flight. Since the validity of flutter calculations has been very well established since that time, the second object was, at present, considered the primary purpose of the tests
On the propagation of large disturbances in a gas. On the combustion of oil. by
Theodore Theodorsen(
Book
)
1 edition published in 1929 in English and held by 2 WorldCat member libraries worldwide
1 edition published in 1929 in English and held by 2 WorldCat member libraries worldwide
Preliminary vibration and flutter studies on P47 tail by
Theodore Theodorsen(
Book
)
2 editions published in 1943 in English and held by 2 WorldCat member libraries worldwide
This paper contains a brief report illustrated by photographs and vibration records on the failure of the P47 rudder in the highspeed tunnel at the LMAL at a true speed of 468 miles per hour and a density corresponding to 9000 feet altitude. The finrudder unit was tested as being at least representative of the tail design of the P47 airplane. It is noted that the rudder was subjected to a speed in excess of 400 miles per hour for less than an hour of total testing time
2 editions published in 1943 in English and held by 2 WorldCat member libraries worldwide
This paper contains a brief report illustrated by photographs and vibration records on the failure of the P47 rudder in the highspeed tunnel at the LMAL at a true speed of 468 miles per hour and a density corresponding to 9000 feet altitude. The finrudder unit was tested as being at least representative of the tail design of the P47 airplane. It is noted that the rudder was subjected to a speed in excess of 400 miles per hour for less than an hour of total testing time
On the theory of wing sections with particular reference to the lift distribution : [in three parts] by
Theodore Theodorsen(
Book
)
2 editions published in 1931 in English and held by 2 WorldCat member libraries worldwide
2 editions published in 1931 in English and held by 2 WorldCat member libraries worldwide
The elimination of fire hazard due to back fires by
Theodore Theodorsen(
Book
)
1 edition published in 1931 in English and held by 2 WorldCat member libraries worldwide
1 edition published in 1931 in English and held by 2 WorldCat member libraries worldwide
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
The Theory of Propellers. 2. Method for Calculating the Axial Interference Velocity(
)
1 edition published in 1944 in English and held by 0 WorldCat member libraries 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
1 edition published in 1944 in English and held by 0 WorldCat member libraries 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
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Related Identities
 Garrick, I. E. (Isadore Edward) 19101981
 Williams, Muriel Theodorsen
 Dowell, E. H.
 United States National Advisory Committee for Aeronautics
 Langley Aeronautical Laboratory
 Regier, Arthur A.
 Smith, N. H.
 NATIONAL AERONAUTICS AND SPACE ADMIN LANGLEY RESEARCH CENTER HAMPTON VA
 Clay, William C.
 Naiman, Irven
Associated Subjects
Aerodynamic load Aerodynamics, Supersonic AerodynamicsResearch Aerofoils AerofoilsTesting Aeronautics AeronauticsResearch Air flow AirplanesControl surfaces AirplanesFuel tanks AirplanesIce prevention AirplanesModelsTesting AirplanesMotorsMufflers AirplanesNoise AirplanesTail surfaces AirplanesTesting Angle of attack (Aerodynamics) Bars (Engineering) Charts, diagrams, etc Cylinders Disks, Rotating Drag (Aerodynamics) Flutter (Aerodynamics) Lift (Aerodynamics) Mathematics Noise control Numerical analysis Oscillating wings (Aerodynamics) Propellers, Aerial Propellers, AerialNoise Shock waves Thunderbolt (Fighter plane) Vibration (Aeronautics) Wind tunnels Wind tunnel testing
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