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in creator/contributor: "Van Dyke, Milton D"  
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Second-Order Subsonic Airfoil Theory Including Edge Effects

Description: "Several recent advances in plane subsonic flow theory are combined into a unified second-order theory for airfoil sections of arbitrary shape. The solution is reached in three steps: the incompressible result is found by integration, it is converted into the corresponding subsonic compressible result by means of the second-order compressibility rule, and it is rendered uniformly valid near stagnation points by further rules. Solutions for a number of airfoils are given and are compared with th… more
Date: 1956
Creator: Van Dyke, Milton D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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On Stokes' Stream Function in Compressible Small-Disturbance Theory

Description: Note presenting a study of Stokes' stream function for subsonic or supersonic flow past axisymmetric bodies of small slope. The first-order equation is found to be nonlinear. It can be linearized if one seeks only the formal order of accuracy of the slender-body approximation.
Date: February 1957
Creator: Van Dyke, Milton D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Similarity Rules for Second-Order Subsonic and Supersonic Flow

Description: "The similarity rules for linearized compressible flow theory (Göthert's rule and its supersonic counterpart) are extended to second order. It is shown that any second-order subsonic flow can be related to "nearly incompressible" flow past the same body, which can be calculated by the Janzen-Rayleigh method" (p. 1).
Date: January 1957
Creator: Van Dyke, Milton D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Supersonic Flow Past Oscillating Airfoils Including Nonlinear Thickness Effects

Description: Note presenting a solution to second order in thickness derived for harmonically oscillating two-dimensional airfoils in supersonic flow. For slow oscillations of an arbitrary profile, the result is found as a series including the third power of frequency.
Date: July 1953
Creator: Van Dyke, Milton D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Second Order Subsonic Airfoil-Section Theory and Its Practical Application

Description: Note presenting several recent advances in plane subsonic flow theory combined into a unified second-order theory for airfoils of arbitrary shape. The solution is reached in three steps. Solutions for a number of airfoils are given and are compared with the results of other theories and of the experiment.
Date: March 1955
Creator: Van Dyke, Milton D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Practical Calculation of Second-Order Supersonic Flow Past Nonlifting Bodies of Revolution

Description: "Calculation of second-order supersonic flow past bodies of revolution at zero angle of attack is described in detail, and reduced to routine computation. Use of an approximate tangency condition is shown to increase the accuracy for bodies with corners. Tables of basic functions and standard computing forms are presented. The procedure is summarized so that one can apply it without necessarily understanding the details of the theory" (p. 1).
Date: July 1952
Creator: Van Dyke, Milton D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Second-Order Slender-Body Theory: Axisymmetric Flow

Description: "Slender-body theory for subsonic and supersonic flow past bodies of revolution is extended to a second approximation. Methods are developed for handling the difficulties that arise at round ends. Comparison is made with experiment and with other theories for several simple shapes" (p. 1).
Date: September 1958
Creator: Van Dyke, Milton D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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High-Speed Subsonic Characteristics of 16 NACA 6-Series Airfoil Sections

Description: Note presenting a wind-tunnel investigation to determine the high-speed subsonic aerodynamic characteristics of NACA 63-, 64-, 65-, and 66-series airfoil sections with four thickness ratios and an ideal lift coefficient with the uniform-load type of mean camber line. For each thickness ratio, only a slightly impairment of high-speed section drag characteristics results from forward movement of position of minimum base-profile pressure up to 40 percent of the chord.
Date: March 1952
Creator: Van Dyke, Milton D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Subsonic Edges in Thin-Wing and Slender-Body Theory

Description: Note presenting a simple technique for correcting the results of thin-wing theory near round or sharp edges at which the normal component of free-stream velocity is subsonic. The flow in planes normal to such edges is actually brought to rest, but thin-wing theory instead predicts infinite velocities.
Date: November 1954
Creator: Van Dyke, Milton D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Similarity Rules for Second-Order Subsonic and Supersonic Flow

Description: "The similarity rules for linearized compressible flow theory (Gothert's rule and its supersonic counterpart) are extended to second order. It is shown that any second-order subsonic flow can be related to "nearly incompressible" flow past the same body, which can be calculated by the Janzen-Rayleigh method" (p. 925).
Date: October 18, 1956
Creator: Van Dyke, Milton D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Study of Hypersonic Small-Disturbance Theory

Description: "A systematic study is made of the approximate inviscid theory of thin bodies moving at such high supersonic speeds that nonlinearity is an essential feature of the equations of flow. The first-order small-disturbance equations are derived for three-dimensional motions involving shock waves, and estimates are obtained for the order of error involved in the approximation. The hypersonic similarity rule of Tsien and Hayes, and Hayes' unsteady analogy appear in the course of the development" (p. 1… more
Date: 1954
Creator: Van Dyke, Milton D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Supersonic Flow Past Oscillating Airfoils Including Nonlinear Thickness Effects

Description: "A solution to second order in thickness is derived for harmonically oscillating two-dimensional airfoils in supersonic flow. For slow oscillations of an arbitrary profile, the result is found as a series including the third power of frequency. For arbitrary frequencies, the method of solution for any specific profile is indicated, and the explicit solution derived for a single wedge" (p. 611).
Date: April 20, 1953
Creator: Van Dyke, Milton D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Study of Second-Order Supersonic Flow Theory

Description: Second-order solutions of supersonic-flow problems are sought by iteration, using the linearized solution as the first step. For plane and axially symmetric flows, particular solutions of the iteration equation are discovered which reduce the second-order problem to an equivalent linearized problem. Comparison of second-order solutions with exact and numerical results shows great improvement over linearized theory.
Date: April 2, 1952
Creator: Van Dyke, Milton D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Study of Second-Order Supersonic-Flow Theory

Description: Note presenting an attempt to develop a second approximation to the solution of problems of supersonic flow which can be solved by existing first-order theory. The method of attack adopted is an iteration process using the linearized solution as the first step.
Date: January 1951
Creator: Van Dyke, Milton D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of wing characteristics at a Mach number of 1.53 2: swept wings of taper ratio 0.5

Description: Measured values of lift, drag, and pitching moment at M(sub o) = 1.53 are presented for seven wings varying in sweep angle from 60 degrees sweepforward to 60 degrees sweepback. All wings had a cambered, double-wedge section 5-percent thick and a common taper ratio of 0.5. The experimental results are compared with the predictions of the linear theory.
Date: June 28, 1948
Creator: Vincenti, Walter G.; Van Dyke, Milton D. & Matteson, Frederick H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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