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Aerodynamic characteristics of the NACA 8-H-12 airfoil section at six Reynolds numbers from 1.8 x 10(exp 6) to 11.0 x 10(exp 6)
Report presenting an investigation in the two-dimensional low-turbulence pressure tunnel to determine the aerodynamic characteristics of the NACA 8-H-12 airfoil section at four Reynolds numbers. The section lift, drag, and pitching-moment characteristics are presented for smooth and rough surface conditions. Generally, no unusual scale effects are present for either condition.
Date:
December 1949
Creator:
Schaefer, Raymond F. & Smith, Hamilton A.
System:
The UNT Digital Library
Aerodynamic characteristics of the NACA 64-010 and 0010-1.10 40/1.051 airfoil sections at Mach numbers from 0.30 to 0.85 and Reynolds numbers from 4.0 x 10(exp. 6) to 8.0 x 10(exp. 6)
Report presenting an investigation in the low-turbulence pressure tunnel to determine the aerodynamic characteristics of NACA 64-010 and 0010-1.10 airfoil sections. The investigation covered a range of Mach and Reynolds numbers.
Date:
August 1954
Creator:
Loftin, Laurence K., Jr.
System:
The UNT Digital Library
Aerodynamic Characteristics of Three Deep-Step Planing-Tail Flying-Boat Hulls and a Transverse-Step Hull with Extended Afterbody
From Summary: "An investigation was made to determine the aerodynamic characteristics in the presence of a wing of three-step planning-tail flying-boat hulls which differed only in the amount of step fairing. The purpose of comparison, tests were also made of a transverse-step hull with an extended afterbody."
Date:
August 1952
Creator:
Riebe, John M. & Naeseth, Rodger L.
System:
The UNT Digital Library
The aerodynamic characteristics of three tapered airfoils tested in the variable density wind tunnel
From Summary: "This report contains the lift, drag, and moment characteristics of tapered Clark Y, Gottingen 393, and USA 45 airfoils as obtained from tests made in the Variable Density Wind Tunnel of the NACA. The results are given at both low and high Reynolds Numbers to show scale effect and to provide data for use in airplane design."
Date:
February 1931
Creator:
Anderson, Raymond F.
System:
The UNT Digital Library
Aerodynamic coefficients for an oscillating airfoil with hinged flap, with tables for a Mach number of 0.7
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.
System:
The UNT Digital Library
The aerodynamic design and calibration of an asymmetric variable Mach number nozzle with a sliding block for the Mach number range 1.27 to 2.75
From Introduction: "This paper presents the basic design method and experimental results of calibration of a nozzle which was constructed to conform to the analytically determined ordinates."
Date:
April 1953
Creator:
Burbank, Paige B. & Byrne, Robert W.
System:
The UNT Digital Library
The Aerodynamic Design of High Mach Number Nozzles Utilizing Axisymmetric Flow with Application to a Nozzle of Square Test Section
From Introduction: "A method for the design of three-dimensional nozzles based on axi-symmetric flow is presented in this paper. The design method presented in this paper is general; however, as an illustrative example of the design of a Mach number 10 nozzle with square test section is included."
Date:
June 1952
Creator:
Beckwith, Ivan E.; Ridyard, Herbert W. & Cromer, Nancy
System:
The UNT Digital Library
The Aerodynamic Design of Supersonic Propellers from Structural Considerations
From Summary: "The aerodynamic design of propellers from considerations of centrifugal force is presented. By applying a constant minimum value of thickness ratio from root to tip and allowing the distribution of required area to appear in the blade plan form, propellers with good efficiency are realized at high Mach numbers by the method of this paper."
Date:
December 1952
Creator:
Hammack, Jerome B.
System:
The UNT Digital Library
The Aerodynamic Drag of Five Models of Side Floats N.A.C.A. Models 51-E, 51-F, 51-G, 51-H, 51-J
"The drag of five models of side floats was measured in the N.A.C.A. 7- by 10-foot wind tunnel. The most promising method of reducing the drag of floats indicated by these tests is lowering the angle at which the floats are rigged. The addition of a step to a float does not always increase the drag in the flying range, floats with steps sometimes having lower drag than similar floats without steps" (p. 1).
Date:
December 1938
Creator:
House, R. O.
System:
The UNT Digital Library
The Aerodynamic Drag of Flying-Boat Hull Model as Measured in the NACA 20-Foot Wind Tunnel - 1
"The main purpose of this investigation is to make available to the designer useful information with regard to the aerodynamic drag of various types of flying-boat hull models. The present report is the first in a series covering investigation in this field. Through close cooperation between hydrodynamics and aerodynamics divisions it is hoped that results leading to improvements in hull design obtained" (p. 1).
Date:
April 1935
Creator:
Hartman, Edwin P.
System:
The UNT Digital Library
The Aerodynamic Effect of a Retractable Landing Gear
"Tests were conducted in the N.A.C.A. full scale wind tunnel at the request of the Army Air Corps to determine the effect of retractable landing gear openings in the bottom surface of a wing upon the characteristics of a Lockheed Altair airplane. The tests were extended to include the determination of the lift and drag characteristics throughout the angle-of-attack range with the landing gear both retracted and extended. Covering the wheel openings in the wing with sheet metal when the wheels were extended reduced the drag only 2 percent at a lift coefficient of 1.0, which was assumed for the take-off condition" (p. 1).
Date:
March 1933
Creator:
DeFrance, Smith J.
System:
The UNT Digital Library
Aerodynamic Effects Caused by Icing of an Unswept NACA 65A004 Airfoil
From Summary: "The effects of ice formations on the section lift, drag, and pitching-moment coefficients of an unswept NACA 65A004 airfoil section of 6-foot chord were studied.. The magnitude of the aerodynamic penalties was primarily a function of the shape and size of the ice formation near the leading edge of the airfoil. The exact size and shape of the ice formations were determined photographically and found to be complex functions of the operating and icing conditions."
Date:
February 1958
Creator:
Gray, Vernon H. & von Glahn, Uwe H.
System:
The UNT Digital Library
Aerodynamic Effects of a Split Flap on the Spinning Characteristics of a Monoplane Model
From Summary: "The investigation described in this report was made to determine the change in aerodynamic forces and moments produced by split flaps in a steady spin. The test were made with the spinning balance in the NACA 5-foot vertical wind tunnel. A low-wing monoplane model was tested with and without the split flaps in 12 spinning attitudes chosen to cover the probable spinning range. The results obtained indicate that the use of split flaps on an airplane is unlikely, in any case, to have much beneficial effect on a spin, and it might make the spin dangerous."
Date:
December 1934
Creator:
Bamber, M. J.
System:
The UNT Digital Library
The aerodynamic forces and moments on a 1/10-scale model of a fighter airplane in spinning attitudes as measured on a rotary balance in the Langley 20-foot free-spinning tunnel
From Introduction: "This investigation provides general information on the magnitudes and directions of the aerodynamic forces and moments acting on a fighter airplane in fully developed spins. The investigation includes the determination of the effects on the aerodynamic forces and moments of varied rudder setting with and against the spin, of tail modifications, and of deflected flaps and lowered landing gear."
Date:
September 1950
Creator:
Stone, Ralph W., Jr.; Burk, Sanger M., Jr. & Bihrle, William, Jr.
System:
The UNT Digital Library
The Aerodynamic Forces and Moments on a Spinning Model of the F4B-2 Airplane as Measured by the Spinning Balance
"The tests described in this report were made as part of an investigation of the spinning characteristics of the F4B-2 airplane conducted at the request of the Bureau of Aeronautics, Navy Department" (p. 1).
Date:
February 1935
Creator:
Bamber, M. J. & Zimmerman, C. H.
System:
The UNT Digital Library
Aerodynamic forces, moments, and stability derivatives for slender bodies of general cross section
From Introduction: "The present paper employs an approach believed to be novel in slender-body theory and is concerned with developing formulas for the forces and moments as well as the stability derivatives for slender wing-body combinations."
Date:
November 1954
Creator:
Sacks, Alvin H.
System:
The UNT Digital Library
Aerodynamic forces, moments, and stability derivatives for slender bodies of general cross section
From Introduction: "The present paper employs an approach believed to be novel in slender-body theory and is concerned with developing formulas for the forces and moments as well as the stability derivatives for general slender wing-body combinations."
Date:
November 1954
Creator:
Sacks, Alvin H.
System:
The UNT Digital Library
Aerodynamic heating and the deflection of drops by an obstacle in an air stream in relation to aircraft icing
From Summary: "Two topics of interest to persons attempting to apply the heat method of preventing ice formation on aircraft are considered. Surfaces moving through air at high speed are shown, both theoretically and experimentally, to be subject to important aerodynamic heating effects that will materially reduce the heat required to prevent ice. Numerical calculations of the path of water drops in an air stream around a circular cylinder are given. From these calculations, information is obtained on the percentage of the swept area cleared of drops."
Date:
October 1940
Creator:
Kantrowitz, Arthur
System:
The UNT Digital Library
Aerodynamic interference of slender wing-tail combinations
From Introduction: "In the present paper, the emphasis is placed on calculating the variations of total forces and moments with angles of attack and sideslip for a number of slender plane and cruciform wing-tail combinations and for some airplane-type arrangements of a plane wing and a horizontal and vertical tail."
Date:
January 1957
Creator:
Sacks, Alvin H.
System:
The UNT Digital Library
Aerodynamic Investigation of a Cup Anemometer
Results of an investigation wherein the change of the normal force coefficient with Reynolds Number was obtained statically for a 15.5-centimeter hemispherical cup.
Date:
July 1934
Creator:
Hubbard, John D. & Brescoll, George P.
System:
The UNT Digital Library
Aerodynamic investigation of a four-blade propeller operating through an angle-of-attack range from 0 to 180 degrees
Report presenting an investigation of the aerodynamic characteristics of a four-blade rigid model propeller in the full-scale tunnel for a range of angles of attack, blade angles, and advance ratio. It included a preliminary explanation of vertical descent and a comparison with theory. Results regarding the static thrust and forward flight are provided.
Date:
June 1954
Creator:
McLemore, H. Clyde & Cannon, Michael D.
System:
The UNT Digital Library
Aerodynamic investigation of a parabolic body of revolution at Mach number of 1.92 and some effects of an annular supersonic jet exhausting from the base
Report discussing an aerodynamic investigation of a slender pointed parabolic body of revolution was conducted at Mach number of 1.92 with and without the effects of an annular supersonic jet exhausting from the base.
Date:
September 1956
Creator:
Love, Eugene S.
System:
The UNT Digital Library
Aerodynamic loads on a leading-edge flap and a leading-edge slat on the NACA 64A010 airfoil section
From Summary: "The present report presents the chordwise distributions of pressure measured concurrently with the force and moment data of NACA TN 3007."
Date:
June 1954
Creator:
Kelly, John A. & McCullough, George B.
System:
The UNT Digital Library
Aerodynamic mixing downstream from line source of heat in high-intensity sound field
From Summary: "This report describes a theoretical and experimental investigation of the aerodynamic mixing by a standing sound wave downstream from a continuous line source of heat."
Date:
August 1956
Creator:
Mickelsen, William R. & Baldwin, Lionel V.
System:
The UNT Digital Library