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Wind-tunnel investigation of profile drag and lift of an intermediate wing section of the XP-51 airplane with beveled trailing-edge and contour ailerons
Report presenting the results of flight investigations showing that a beveled trailing-edge aileron gives as low or a lower profile drag than a contour aileron. Section profile drag and lift coefficients with two different types of ailerons were obtained at 3 different Reynolds numbers.
Date:
January 1943
Creator:
Abbott, Frank T., Jr. & Underwood, William J.
System:
The UNT Digital Library
Airship Model Tests in the Variable Density Wind Tunnel
This report presents the results of wind tunnel tests conducted to determine the aerodynamic characteristics of airship models. Eight Goodyear-Zeppelin airship models were tested in the original closed-throat tunnel. After the tunnel was rebuilt with an open throat a new model was tested, and one of the Goodyear-Zeppelin models was retested. The results indicate that much may be done to determine the drag of airships from evaluations of the pressure and skin-frictional drags on models tested at large Reynolds number.
Date:
January 27, 1931
Creator:
Abbott, Ira H.
System:
The UNT Digital Library
Pressure-Distribution Measurements of a Model of a Davis Wing Section with Fowler Flap Submitted by Consolidated Aircraft Corporation
Wing pressure distribution diagrams for several angles of attack and flap deflections of 0 degrees, 20 degrees, and 40 degrees are presented. The normal force coefficients agree with lift coefficients obtained in previous test of the same model, except for the maximum lifts with flap deflection. Pressure distribution measurements were made at Reynolds Number of about 6,000,000.
Date:
January 1942
Creator:
Abbott, Ira H.
System:
The UNT Digital Library
Pressure-distribution measurements of two airfoil models with Fowler flaps submitted by Consolidated Aircraft Corporation as alternative wing sections of the XB-32 airplane
Report presenting pressure distribution measurements on two 24-inch chord models equipped with Fowler flaps in the two-dimensional low-turbulence pressure tunnel. Results regarding pressure-distribution diagrams and normal-force and moment coefficients are provided.
Date:
January 1942
Creator:
Abbott, Ira H.
System:
The UNT Digital Library
Tests in the variable-density wind tunnel of the NACA 23012 airfoil with plain and split flaps
From Summary: "Section characteristics for use in wing design are presented for the NACA 23012 airfoil with plain and split flaps of 20 percent wing chord at a value of the effective Reynolds number of about 8,000,000. The flap deflections covered a range from 60 degrees upward to 75 degrees downward for the plain flap and from neutral to 90 degrees downward for the split flap. The split flap was aerodynamically superior to the plain flap in producing high maximum lift coefficients and in having lower profile-drag coefficients at high lift coefficients."
Date:
January 21, 1938
Creator:
Abbott, Ira H. & Greenberg, Harry
System:
The UNT Digital Library
Theoretical Investigation of the Performance of Proportional Navigation Guidance Systems: Effect of Missile Configuration on the Speed of Response
Memorandum presenting a comparison of the maximum speed of response that can be attained by three missile configurations, a variable-incidence-wing, a canard, and a tail-control, in combination with a particular proportional navigation guidance system. The configuration that allows the most rapid overall guidance-system response depends on the control-system characteristics. Results regarding the rate-only feedback and rate and normal acceleration feedback are provided.
Date:
January 19, 1953
Creator:
Abramovitz, Marvin
System:
The UNT Digital Library
Removing boundary layer by suction
"Through the utilization of the "Magnus effect" on the Flettner rotor ship, the attention of the public has been directed to the underlying physical principle. It has been found that the Prandtl boundary-layer theory furnishes a satisfactory explanation of the observed phenomena. The present article deals with the prevention of this separation or detachment of the flow by drawing the boundary layer into the inside of a body through a slot or slots in its surface" (p. 1).
Date:
January 1926
Creator:
Ackeret, J.
System:
The UNT Digital Library
Investigations of Compression Shocks and Boundary Layers in Gases Moving at High Speed
The mutual influences of compression shocks and friction boundary layers were investigated by means of high speed wind tunnels.Schlieren optics provided a clear picture of the flow phenomena and were used for determining the location of the compression shocks, measurement of shock angles, and also for Mach angles. Pressure measurement and humidity measurements were also taken into consideration.Results along with a mathematical model are described.
Date:
January 1947
Creator:
Ackeret, J.; Feldmann, F. & Rott, N.
System:
The UNT Digital Library
Turbulence and Mechanism of Resistance on Spheres and Cylinders
The nature of turbulent flow through pipes and around obstacles is analyzed and illustrated by photographs of turbulence on screens and straighteners. It is shown that the reversal of flow and of the resistance law on spheres is not explainable by Prandtl's turbulence in the boundary layer. The investigation of the analogous phenomena on the cylinder yields a reversal of the total field of flow.
Date:
January 1932
Creator:
Ahlborn, F.
System:
The UNT Digital Library
Horizontal-Tail Parameters as Determined From Flight-Test Tail Loads on a Flexible Swept-Wing Jet Bomber
Report presenting an analysis of horizontal-tail loads on a flexible multi-engined jet-propelled swept-wing medium bomber to determine the tail lift-curve slope due to tail angle of attack, tail-lift curve slope due to elevator deflection, tail pitching-moment coefficient due to elevator deflection, downwash factor, and elevator effectiveness factor. The effect of the stabilizer, effects of elevator flexibility, and effects of wing stability are presented.
Date:
January 17, 1957
Creator:
Aiken, William S., Jr. & Fisher, Raymond A.
System:
The UNT Digital Library
Results of Tests to Determine the Effect of a Conical Windshield on the Drag of a Bluff Body at Supersonic Speeds
Tests to evaluate the effect of a conical windshield on the drag of a bluff body at supersonic speeds were performed for the following configurations: a sharp nose fuselage with stabilizing fins,a blunt nose fuselage with a hemispherical shape, and a blunt nose fuselage with a conical point. Results of the drag coefficient are described at Mach 1.0 and the greatest Mach number of 1.37.
Date:
January 14, 1947
Creator:
Alexander, Sidney R.
System:
The UNT Digital Library
Flight Tests to Determine the Effect of Length of a Conical Windshield on the Drag of a Bluff Body at Supersonic Speeds
Flight tests were conducted to determine the effect of length of a conical windshield on the drag of a bluff body moving at supersonic speeds. A comparison is made between results obtained and results of previous drag tests of body-windshield combinations.The effect of increasing the length of the windshield is discussed.
Date:
January 29, 1947
Creator:
Alexander, Sidney R. & Katz, Ellis
System:
The UNT Digital Library
Experimental investigation of flow fields at zero sideslip near swept- and unswept-wing-fuselage combinations at low speed
Report presenting an experimental determination of the flow fields near swept- and unswept-wing-fuselage combinations at zero sideslip as determined experimentally at low speed for various spanwise and vertical locations and angles of attack as variations with chordwise distance. Results regarding the swept-wing-fuselage flow fields, unswept-wing-fuselage flow fields, and a comparison of wing-fuselage and fuselage-alone flow fields are provided.
Date:
January 18, 1957
Creator:
Alford, William J., Jr. & King, Thomas J., Jr.
System:
The UNT Digital Library
Experimental Static Aerodynamic Forces and Moments at High Subsonic Speeds on a Canard Missile During Simulated Launching From the Midsemispan Location of a 45 Degree Sweptback Wing-Fuselage-Pylon Combination at Zero Sideslip
Report presenting an investigation at high subsonic speeds to determine the static aerodynamic forces and moments on a canard missile model during simulated launching from the midsemispan location of a 45 degree sweptback wing-fuselage-pylon combination. Significant variations in all the aerodynamic components were noted with changes in chordwise location of the missile. Results regarding force and moment characteristics and effects of angle of attack and Mach number are provided.
Date:
January 14, 1957
Creator:
Alford, William J., Jr. & King, Thomas J., Jr.
System:
The UNT Digital Library
Experimental Static Aerodynamic Forces and Moments at High Subsonic Speeds on a Missile Model During Simulated Launching From the Midsemispan Location of a 45 Degree Sweptback Wing-Fuselage-Pylon Combination
"An investigation was made at high subsonic speeds in the Langley high-speed 7- by 10-foot tunnel to determine the static aerodynamic forces and moments on a missile model during simulated launching from the midsemispan location of a 45 degree sweptback wing-fuselage-pylon combination. The results indicated significant variations in all the aerodynamic components with changes in chordwise location of the missile. Increasing the angle of attack caused increases in the induced effects on the missile model because of the wing-fuselage-pylon combination" (p. 1).
Date:
January 10, 1957
Creator:
Alford, William J., Jr. & King, Thomas J., Jr.
System:
The UNT Digital Library
Small-scale transonic investigation of a 45 degree sweptback wing of aspect ratio 4 with combinations of nose-flap deflections and wing twist
Report presenting a small-scale transonic investigation of a semispan wing sweptback 45 degrees and of aspect ratio 4 with combinations of nose-flap deflections and wing twist in the high-speed 7- by 10-foot tunnel over a range of Mach numbers. Lift, drag, and pitching-moment data were obtained for several different configurations.
Date:
January 9, 1953
Creator:
Alford, William J., Jr. & Spreemann, Kenneth P.
System:
The UNT Digital Library
The Effect of Compressibility on the Growth of the Laminar Boundary Layer on Low-Drag Wings and Bodies
The development of the laminar boundary layer in a compressible fluid is considered. Formulas are given for determining the boundary-layer thickness and the ratio of the boundary-layer Reynolds number to the body Reynolds number for airfoils and bodies of revolution. It is shown that the effect of compressibility will profoundly alter the Reynolds number corresponding to the upper limit of the range of the low-drag coefficients.
Date:
January 1943
Creator:
Allen, H. Julian & Nitzberg, Gerald E.
System:
The UNT Digital Library
Force and pressure recovery characteristics at supersonic speeds of a conical spike inlet with bypasses discharging in an axial direction
Report presenting an investigation of an axially symmetric nacelle-type conical spike inlet with two bypasses located in the horizontal plane and on opposite sides of the nacelle in the 8- by 6-foot supersonic tunnel at several Mach numbers and angles of attack. Results regarding the performance with open bypasses and with closed bypasses are provided.
Date:
January 30, 1953
Creator:
Allen, J. L. & Beke, Andrew
System:
The UNT Digital Library
Performance of an Inlet Having a Variable-angle Two-dimensional Compression Surface and a Fixed-geometry Subsonic Diffuser for Application to Reduced Engine Rotative Speeds- Mach Numbers 0.66, 1.5, 1.7, and 2.0
Report presenting the performance of a two-dimensional side inlet with a technique of varying compression-surface angle while retaining a fixed-geometry diffuser at several Mach numbers and zero angle of attack. A 12 degree compression ramp was faired into the diffuser contour in this conventional manner. Results regarding the inlet flow field, application to reduced engine speeds, and a inlet performance with a sudden expansion in the diffuser are provided.
Date:
January 30, 1958
Creator:
Allen, John L.
System:
The UNT Digital Library
The Effect of Compression Ratio on Knock Limits of High-Performance Fuels in a CFR Engine 2: Blends of 2,2,3-Trimethylpentane with 28-R
"The knock-limited performance of blends of 0,50; and 100 percent by volume of 2,2,3-trimethylpentane in 28-R fuel determined with a modified F-4 engine at three sets of conditions varying from severe to mild at each of three compression ratios (6.0, 8.0, and 10.0). A comparison of the knock-limited performance of 2,2,3-trimethylpentane with that of triptane (2,2,3-trimethylbutane) is included. The knock-Limited performance of 2,2,3-trimethylpontane was usually more sensitive to either compression ratio or inlet-air temperature than 28-R fuel, but the ratio of the knock-limited indicated mean effective pressure of a given blend containing 2,2,3-trimethypentane and 28-R to the indicated mean effective pressure of 28-R alone was not greatly affected by compression ratio if the engine operating conditions were mild" (p. 1).
Date:
January 1945
Creator:
Alquist, Henry E. & Tower, Leonard K.
System:
The UNT Digital Library
Suitability of ethers as aviation fuel components the knock-limited performance of several ethers blended with AN-F-28 fuel
Report presenting a investigation covering the physical and chemical properties of various ethers as components of aviation fuels. Their antiknock effectiveness and methods of preparation and purification are included. Methyl tert-butyl ether gave the best knock-limited rich mixture response, but isopropyl tert-butyl ether and di-tert-butyl ether gave better results at lean mixtures.
Date:
January 1945
Creator:
Alquist, Henry E. & Tower, Leonard K.
System:
The UNT Digital Library
Wind Tunnel Development of Means to Alleviate Buffeting of the North American XP-82 Airplane at High Speeds
"This report presents the results of wind-tunnel tests of a 0.22-scale model of the North American XP-82 airplane with several modifications designed to reduce the buffeting of the airplane. The effects of various modifications on the air flow over the model are shown by means of photographs of tufts. The drag, lift, and pitching-moment coefficients of the model with several of the modifications are shown" (p. 1).
Date:
January 9, 1947
Creator:
Anderson, Joseph L.
System:
The UNT Digital Library
High-Speed Aerodynamic Characteristics of a Model Tail Plane with Modified NACA 65-010 Sections and 0 Degree and 45 Degrees Sweepback
Memorandum presenting wind-tunnel tests that have been made to determine the aerodynamic characteristics of a model tail plane with modified NACA 65-010 sections and a tapered plan form. Results were obtained with the model tail plane unswept and swept back. The data show the lift, drag, pitching-moment, and hinge-moment coefficient variation with angle of attack and flap deflection at various Mach numbers.
Date:
January 12, 1948
Creator:
Anderson, Joseph L. & Martin, Andrew
System:
The UNT Digital Library
Compressive Crippling of Structural Sections
"A method is presented for calculating crippling stresses of structural sections as a function of material properties and the proportions of the section. The presence of formed or anisotropic material is accounted for by the use of an effective stress-strain curve. The method of analysis applies to many sections for which a procedure for calculating crippling was not previously available" (p. 1).
Date:
January 1956
Creator:
Anderson, Melvin S.
System:
The UNT Digital Library