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Measurements of the effects of finite span on the pressure distribution over double-wedge wings at Mach numbers near shock attachment

Description: Report presenting results of wind-tunnel measurements of the pressure distribution at low supersonic speeds on two rectangular wings of double-wedge section and aspect ratios 2 and 4. The pressure-drag coefficient at zero lift is found to decrease with decrease in aspect ratio at all values of the test Mach number. The effect was found to be most pronounced at Mach numbers at which the shock wave is detached.
Date: September 1955
Creator: Vincenti, Walter G.
Partner: UNT Libraries Government Documents Department

Comparison between theory and experiment for wings at supersonic speeds

Description: Report presenting a critical comparison between experimental and theoretical results for the aerodynamic characteristics of wings at supersonic flight speeds. The lift, pitching moment, and drag characteristics of several families of wings of varying plan form and section in the wind tunnel and compared with values predicted by the three-dimensional linear theory.
Date: June 1950
Creator: Vincenti, Walter G.
Partner: UNT Libraries Government Documents Department

Comparison between theory and experiment for wings at supersonic speeds

Description: This paper presents a critical comparison made between experimental and theoretical results for the aerodynamic characteristics of wings at supersonic flight speeds. As a preliminary, a brief, nonmathematical review is given of the basic assumptions and general findings of supersonic wing theory in two and three dimensions. Published data from two-dimensional pressure-distribution tests are then used to illustrate the effects of fluid viscosity and to assess the accuracy of linear theory as compared with the more exact theories which are available in the two-dimensional case. Finally, an account is presented of an NACA study of the over-all force characteristics of three-dimensional wings at supersonic speed.
Date: May 3, 1950
Creator: Vincenti, Walter G.
Partner: UNT Libraries Government Documents Department

Transonic flow past a wedge profile with detached bow wave

Description: "A theoretical study has been made of the aerodynamic characteristics at zero angle of attack of a thin, doubly symmetrical double-wedge profile in the range of supersonic flight speed in which the bow wave is detached. The analysis utilizes the equations of the transonic small-disturbance theory and involves no assumptions beyond those implicit in this theory. The mixed flow about the front half of the profile is calculated by relaxation solution of boundary conditions along the shock polar and sonic line" (p. 1).
Date: 1952
Creator: Vincenti, Walter G. & Wagoner, Cleo B.
Partner: UNT Libraries Government Documents Department

Transonic flow past a wedge profile with detached bow wave: Details of analysis

Description: Report presenting details of calculations of the flow with detached bow wave past a doubly symmetrical, double-wedge profile at zero angle of attack. The mixed flow over the front of the profile is determined by the solution of a boundary-value problem for the transonic small-disturbance equation in the hodograph plane.
Date: December 1951
Creator: Vincenti, Walter G. & Wagoner, Cleo B.
Partner: UNT Libraries Government Documents Department

Theoretical study of the transonic lift of a double-wedge profile with detached bow wave

Description: Report presenting a theoretical study of the aerodynamic characteristics at small angle of attack of a thin, double-wedge profile in the range of supersonic flight speed in which the bow wave is detached. The calculations provide, for extremely small angles of attack, the following information as a function of the transonic similarity parameter: chordwise lift distribution, lift-curve slope, and position of center of lift.
Date: December 1952
Creator: Vincenti, Walter G. & Wagoner, Cleo B.
Partner: UNT Libraries Government Documents Department

Wall interference in a two-dimensional-flow wind tunnel with consideration of the effect of compressibility

Description: Report presenting tunnel-wall corrections for an airfoil of finite thickness and camber in a two-dimensional-flow wind tunnel. The theory takes account of the effects of the wake of the airfoil and of the compressibility of the fluid and is based on the assumption that the chord of the airfoil is small in comparison with the height of the tunnel. The theoretical results are compared with the small amount of low-speed experimental data available and agreement is seen to be satisfactory, even for relatively large values of the chord-height ratio.
Date: December 1944
Creator: Allen, H. Julian & Vincenti, Walter G.
Partner: UNT Libraries Government Documents Department

Calculation of the supersonic pressure distribution on a single-curved tapered wing in regions not influenced by the root or tip

Description: Report presenting the use of the shock-expansion method for the calculation of the pressure distribution on cylindrical wings in supersonic flow as extended to tapered wings made up of single-curved surfaces. The method applies in regions of the wing where the component of velocity normal to the surface rulings is supersonic and the flow is not influenced by the presence of the root or tip.
Date: June 1955
Creator: Vincenti, Walter G. & Fisher, Newman H., Jr.
Partner: UNT Libraries Government Documents Department

Theoretical study of the transonic lift of a double-wedge profile with detached bow wave

Description: "A theoretical study is described of the aerodynamic characteristics at small angle of attack of a thin, double-wedge profile in the range of supersonic flight speed in which the bow wave is detached. The analysis is carried out within the framework of the transonic (nonlinear) small-disturbance theory, and the effects of angle of attack are regarded as a small perturbation on the flow previously calculated at zero angle. The mixed flow about the front half of the profile is calculated by relaxation solution of a suitably defined boundary-value problem for transonic small-disturbance equation in the hodograph plane (i.e., the Tricomi equation)" (p. 547).
Date: August 1, 1952
Creator: Vincenti, Walter G. & Wagoner, Cleo B.
Partner: UNT Libraries Government Documents Department

Calculations of the flow over an inclined flat plate at free-stream Mach number 1

Description: Report presenting a numerical solution of the complete equations of inviscid compressible flow for the case of an inclined flat plate at free-stream Mach number 1. The results for the flow field show that the large changes of velocity that occur near the leading edge are confined to a surprisingly small part of the field. Results regarding the flow field and pressure distribution are provided.
Date: August 1956
Creator: Vincenti, Walter G.; Wagoner, Cleo B. & Fisher, Newman H., Jr.
Partner: UNT Libraries Government Documents Department

An experimental study of the lift and pressure distribution on a double-wedge profile at Mach numbers near shock attachment

Description: Report presenting an account of wind-tunnel measurements at low supersonic speeds of the pressure distribution on a doubly symmetrical double-wedge profile of approximately 8-percent thickness. The results cover a range of Mach numbers, angles of attack, and a specified Reynolds number. Results regarding the characteristics at zero angle of attack, characteristics at angle of attack, comparison with subsonic results, and some general remarks are provided.
Date: July 1954
Creator: Vincenti, Walter G.; Dugan, Duane W. & Phelps, E. Ray
Partner: UNT Libraries Government Documents Department

The effect of wall interference upon the aerodynamic characteristics of an airfoil spanning a closed-throat circular wind tunnel

Description: "The results of a theoretical and experimental investigation of wall interference for an airfoil spanning a closed-throat circular wind tunnel are presented. Analytical equations are derived which relate the characteristics of an airfoil in the tunnel at subsonic speeds with the characteristics in free air. The analysis takes into consideration the effect of fluid compressibility and is based upon the assumption that the chord of the airfoil is small as compared with the diameter of the tunnel" (p. 225).
Date: 1946
Creator: Vincenti, Walter G. & Graham, Donald J.
Partner: UNT Libraries Government Documents Department

Wall interference in a two-dimensional-flow wind tunnel, with consideration of the effect of compressibility

Description: From Summary: "Theoretical tunnel-wall corrections are derived for an airfoil of finite thickness and camber in a two-dimensional-flow wind tunnel. The theory takes account of the effects of the wake of the airfoil and of the compressibility of the fluid, and is based upon the assumption that the chord of the airfoil is small in comparison with the height of the tunnel. Consideration is given to the phenomenon of choking at high speeds and its relation to the tunnel-wall corrections. The theoretical results are compared with the small amount of low-speed experimental data available and the agreement is seen to be satisfactory, even for relatively large values of the chord-height ratio."
Date: 1944
Creator: Allen, H. Julian & Vincenti, Walter G.
Partner: UNT Libraries Government Documents Department

Investigation of wing characteristics at a Mach number of 1.53 3: unswept wings of differing aspect ratio and taper ratio

Description: Report presenting testing of seven models that from two different wing series: a series of taper ratio 0.5 and differing aspect ratio and a series of aspect ratio 4 and differing taper ratio. Measurements of lift, drag, and pitching moment were made at Mach number 1.53. The aerodynamic parameters generally varied with aspect ratio and taper ratio in the manner indicated by the linear theory.
Date: June 21, 1948
Creator: Nielsen, Jack N.; Matteson, Frederick H. & Vincenti, Walter G.
Partner: UNT Libraries Government Documents Department

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.
Partner: UNT Libraries Government Documents Department

Investigation of wing characteristics at a Mach number of 1.53 1: triangular wings of aspect ratio 2

Description: Report presenting wind-tunnel testing conducted on three sharp-edge wing models with a thickness ratio of 5 percent and a common triangular plan form of aspect ratio 2. Measurements of lift, drag, and pitching moment were made at Mach number 1.53. The experimental lift and moment curves were found to conform essentially with the superposition principle of the linear theory.
Date: December 19, 1947
Creator: Vincenti, Walter G.; Nielsen, Jack N. & Matteson, Frederick H.
Partner: UNT Libraries Government Documents Department