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A method for increasing the effectiveness of stabilizing surfaces at high supersonic Mach numbers

Description: Report presenting the use of wedge-shaped airfoil sections to obtain large increases in lift-curve slope at low angles of attack at high supersonic Mach numbers. The use of such sections on the tail surfaces operating at low angles of attack on airplanes or missiles traveling at these speeds can greatly decrease the stabilizing-surface area required.
Date: August 3, 1954
Creator: McLellan, Charles H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tests of Four Racing Type Airfoils in the Twenty-Foot Propeller Research Tunnel

Description: Tests were made on four racing type airfoils, the N-9, N-38, C-62, and N-46, in order to determine the high speed characteristics of the wings. The results indicate that the N-46 has about 12 percent lower minimum drag than the regular C-62 section, and that both the N-38 and N-46 have the same exceptionally low minimum drag coefficient.
Date: September 1929
Creator: Weick, Fred E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Subsonic Aerodynamic Characteristics of Two Double-Wedge Airfoil Sections Suitable for Supersonic Flight

Description: Memorandum presenting high-speed wind-tunnel testing to investigate the aerodynamic characteristics at subsonic speeds of two symmetrical double-wedge airfoil sections of 4- and 6-percent-chord thickness suitable for application to supersonic aircraft. Section coefficients of lift, drag, and quarter-chord pitching moment are presented for a moderate range of angles of attack at Mach numbers up to approximately 0.93. The double-wedge airfoil exhibits no characteristics other than those common to… more
Date: May 12, 1947
Creator: Solomon, Joseph & Henney, Floyd W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Investigation of Flow Characteristics at Mach Number 4.04 Over 6- and 9-Percent-Thick Symmetrical Circular-Arc Airfoils Having 30-Percent-Chord Trailing-Edge Flaps

Description: Section data obtained from wind-tunnel tests at Mach number 4.04 and Reynolds numbers of about 5.0 times 10 to the 6th power and 8.4 times 10 to the 6th power are presented for 6- and 9-percent-thick symmetrical circular-arc airfoils with 30 percent chord trailing-edge flaps. Pressure distributions, Schlieren photographs, and force and moment coefficients are included.
Date: July 19, 1951
Creator: Ulmann, Edward F. & Lord, Douglas R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Forces and Moments on a Yawed Airfoil

Description: "The author elaborates on the flow phenomena, forces and moments on airfoils in yaw. The existing experiments with straight wings (zero dihedral), wings with dihedral, and wings with sweepback are evaluated within the range of sound angles of attack, explained by calculation and generally enlarged" (p. 1).
Date: August 1939
Creator: Hoerner, Sighard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Characteristics of Clark Y airfoils of small aspect ratios

Description: This report presents the results of a series of wind tunnel tests showing the force, moment, and autorotational characteristics of Clark Y airfoils having aspect ratios varying from 0.5 to 3. An airfoil of rectangular plan form was tested with rectangular tips, flared tips, and semicircular tips. Tests were also made on one airfoil of circular plan form and two airfoils of elliptical plan form. The tests revealed a marked delay of the stall and a decided increase in values of maximum lift coeff… more
Date: May 5, 1932
Creator: Zimmerman, C. H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Interdependence of Profile Drag and Lift With Joukowski Type and Related Airfoils

Description: "On the basis of a systematic investigation of Gottingen wind-tunnel data on Joukowski type and related airfoils, it is shown in what manner the profile drag coefficient is dependent on the lift coefficient. The individual factors for the construction of the profile drag polars are given. They afford a more accurate calculation of the performance coefficients of airplane designs than otherwise attainable with the conventional assumption of constant drag coefficient" (p. 1).
Date: March 1935
Creator: Muttray, H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Characteristics of Naca 4400R Series Rectangular and Tapered Airfoils, Including the Effect of Split Flaps

Description: "At the request of the Bureau of Aeronautics, Navy Department, tests were made in the variable-density wind tunnel of a tapered wing of 3-10-18 plan form and based on the NACA 4400R series sections. The wing was also tested with 0.2 chord split flaps, deflected 60 degrees, in the center of the wing and having flat span to wing span ratios of 0.3, 0.5, 0.7, and 1.0, respectively" (p. 1).
Date: January 1941
Creator: Greenberg, Harry
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-tunnel investigation of control-surface characteristics 13: various flap overhangs used with a 30-percent-chord flap in an NACA 66-009 airfoil

Description: Report presenting force tests in two-dimensional flow made on an NACA 66-009 airfoil with a flap having a chord 30 percent of the airfoil chord and a tab having a chord 20 percent of the flap chord. A plain flap and flaps having overhangs of 35 and 50 percent of the flap chord were tested with two gap variations: sealed and unsealed. Results regarding lift, flap hinge moments, pitching moments, drag, and tab characteristics are provided.
Date: July 1943
Creator: Gillis, Clarence L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

S814 and S815 Airfoils: October 1991--July 1992

Description: Two thick laminar-flow airfoils for the root portion of a horizontal-axis wind turbine blade, the S814 and S815, have been designed and analyzed theoretically. For both airfoils, the primary objectives of high maximum lift, insensitive to roughness, and low profile drag have been achieved. The constraints on pitching moment and airfoil thicknesses have been satisfied.
Date: December 1, 2004
Creator: Somers, D. M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of Periodic Changes of Angle of Attack on Behavior of Airfoils

Description: This report presents the results of a series of experiments, which gave some quantitative results on the effect of periodic changes in the direction of the relative air flow against airfoils. The first series of experiments concerned how the angle of attack of the wing model was changed by causing the latter to oscillate about an axis parallel to the span and at right angles to the air flow. The second series embraced all the experiments in which the direction of the air flow itself was periodi… more
Date: October 1922
Creator: Katzmayr, R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Profile-Drag Coefficients of Conventional and Low-Drag Airfoils as Obtained in Flight

Description: "The results of flight investigations of the profile drag of several carefully finished conventional and low-drag airfoils are presented. The results indicated that in all cases lower profile-drag coefficients were obtained with the low-drag than with the conventional airfoils over the range of lift coefficient tested and that, for comparable conditions of lift coefficient and Reynolds number, the low-drag airfoils may have profile-drag coefficients which are at least 27 percent lower than the … more
Date: May 1944
Creator: Zalovcik, John A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Notes on the Effect of Surface Distortions on the Drag and Critical Mach Number of Airfoils

Description: "The effect of two-dimensional bumps and surface waviness on the pressure distribution over airfoils is considered. It is shown that the results of the analysis may be useful in evaluating the effects of accidental or intended surface distortions on the drag and critical Mach number of airfoils" (p. 1).
Date: September 1943
Creator: Allen, H. Julian
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Vorticism in Aeronautics

Description: Since the war there has been a considerable advance in knowledge on the subject of the airfoil and its behavior. The theory is now sufficiently advanced to make it possible to predict and to calculate certain results which previously could only be attained by direct experiment. The vortex theory receives special attention.
Date: August 1923
Creator: Sayers, W. H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic Characteristics of Four NACA Airfoil Sections Designed for Helicopter Rotor Blades

Description: "The purpose of the present work is to extend the previous investigation and to derive additional airfoil sections designed to minimize the undesirable characteristics of the previously tested airfoils. The tests of these additional airfoils were made in the Langley two-dimensional low-turbulence tunnel (LTT)" (p. 2).
Date: February 1946
Creator: Stivers, Louis S., Jr. & Rice, Fred J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Some effects of aileron span, aileron chord, and wing twist on rolling effectiveness as determined by rocket-powered model tests and theoretical estimates

Description: A determination of the variation of rolling effectiveness with spanwise aileron extent for full-chord ailerons on a sweptback wing over a range of Mach numbers. The test wings had NACA 65A006 airfoil sections, an aspect ratio of 4.0, 45 degrees sweepback at the quarter-chord line, and a taper ratio of 0.6. Results regarding ailerons and twisted wings are provided.
Date: September 14, 1954
Creator: Strass, H. Kurt & Tucker, Warren A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Theoretical and experimental data for a number of NACA 6A-series airfoil sections

Description: Report presenting theoretical and experimental data for NACA 6A-series basic thickness airfoils, which were designed to eliminate the trailing-edge cusp present in NACA 6-series sections. Results indicated that the section minimum-drag and maximum-lift characteristics of the 6-series and 6A-series airfoil sections are essentially the same. Drag, lift, pitching-moment characteristics, and aerodynamic center are also provided.
Date: July 1947
Creator: Loftin, Laurence K., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analytical investigation of icing limit for diamond-shaped airfoil in transonic and supersonic flow

Description: From Introduction: "The results presented herein were calculated for a symmetrical diamond airfoil at zero angle of attack for a range of airfoil-thickness ratios from 0.02 to 0.10, pressure altitude from sea level to 45,000 feet, and free-stream static temperatures to -.40^o F."
Date: January 1953
Creator: Callaghan, Edmund E. & Serafini, John S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic coefficients for an oscillating airfoil with hinged flap, with tables for a Mach number of 0.7

Description: From Introduction: "The fundamental integral equation for the pressure distribution on an oscillating thin airfoil moving at subsonic speed has been derived by Possio in reference 1. Collocation procedures have been used by Possio, Frazer, and Skan, and others to obtain lift and moment on an oscillating first plate. An important contribution has been made by Dietze (see reference 2 and 3), who has developed an iterative procedure for numerical solution of Possio's integral equation."
Date: October 1950
Creator: Turner, M. J. & Rabinowitz, S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of leading-edge radius and maximum thickness-chord ratio on the variation with Mach number of the aerodynamic characteristics of several thin NACA airfoil sections

Description: Report presenting a wind-tunnel investigation to determine the effects of leading-edge radius and maximum thickness-chord ratio on the variation with Mach number of the aerodynamic characteristics of several thin symmetrical NACA 4-digit-series airfoil sections. The variations with Mach number of the lift, drag, and pitching moment for a 4-percent-chord-thick airfoil section are not significantly affected by a change of leading-edge radius from 0.18 to 0.53 percent of the chord.
Date: April 14, 1954
Creator: Berggren, Robert E. & Graham, Donald J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Compilation of information on the transonic attachment of flows at the leading edges of airfoils

Description: Schlieren photographs have been compiled of the two-dimensional flow at transonic speeds past 37 airfoils. These airfoils have variously shaped profiles, and some are related in thickness and camber. The data for these airfoils were analyzed to provide basic information on the flow changes involved and to determine factors affecting transonic-flow attachment, which is a transition from separated to unseparated flow at the leading edges of two-dimensional airfoils at fixed angles as the subsonic… more
Date: February 1958
Creator: Lindsey, Walter F. & Landrum, Emma Jean
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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