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Investigation of translating-double-cone axisymmetric inlets with cowl projected areas 40 and 20 percent of maximum at Mach numbers from 3.0 to 2.0

Description: Report presenting the performance of two translating-double-cone inlets with contrasting rates of turning on the spike shoulder and corresponding cowl projected frontal areas of 40 and 20 percent of maximum compared over a range of Mach numbers. Results regarding internal-flow performance, external-flow performance, inlet airflow patterns, and propulsive-thrust comparison are provided.
Date: May 20, 1957
Creator: Connors, James F.; Wise, George A. & Lovell, J. Calvin
Partner: UNT Libraries Government Documents Department

Investigation of vertical drag and periodic airloads acting on flat panels in a rotor slipstream

Description: Tests have been conducted on the Langley helicopter test tower to determine the vertical drag and pressure distributions on flat panels mounted below a helicopter rotor. Calculations of the vertical drag by use of a strip-analysis procedure outlined in the paper and the assumption of a fully contracted wake agreed well with the experimental results over the range from 0.2 to 0.64 rotor radius beneath the plane of zero flapping. The pressure increase caused by the passage of the blade over the panel is a maximum at about the 0.8 radius spanwise station. At this station, the pressure decreases from 10 times the disk loading per blade at 0.05 radius beneath the rotor plane of zero flapping to one-half of the disk loading per blade at 0.64 radius beneath the plane of zero flapping.
Date: December 1956
Creator: Makofski, Robert A. & Menkick, George F.
Partner: UNT Libraries Government Documents Department

Measurements of the effects of thickness ratio and aspect ratio on the drag of rectangular-plan-form airfoils at transonic speeds

Description: Report presenting testing conducted on two airfoils from a series of rectangular-plan-form airfoils of aspect ratios 7.6 and 5.1 and with NACA 65-006, 65-009, and 65-012 sections using the free-fall method. Results regarding the time histories, ground-velocity data, airfoil drag measurements, and drag coefficients are provided.
Date: June 20, 1947
Creator: Thompson, Jim Rogers & Mathews, Charles W.
Partner: UNT Libraries Government Documents Department

Effect on Drag of Longitudinal Positioning of Half-Submerged and Pylon-Mounted Douglas Aircraft Stores on a Fuselage with and without Cavities between Mach Numbers 0.9 and 1.8

Description: From Summary: "The effect on drag of positioning symmetrically mounted Douglas Aircraft Company, Inc. stores in pairs on a parabolic fuselage of fineness ratio 10.0 has been determined by flight tests of rocket-propelled, zero-lift models through a range of Mach number from 0.9 to 1.8. The stores were mounted in half-submerged positions and on pylons and were tested in three longitudinal locations on the fuselage with the forward position being located at the maximum diameter of the fuselage. The effects on drag of removing the half-submerged stores or extending them outward on pylons also was investigated by tests of models with half-submerged-store cavities on the fuselage. Two pylons differing in airfoil section and thickness were tested at the forward position of the stores on the fuselage with cavities."
Date: July 15, 1954
Creator: Hoffman, Sherwood & Wolff, Austin L.
Partner: UNT Libraries Government Documents Department

Low-lift drag and stability data from rocket models of a modified-delta-wing airplane with and without external stores at Mach numbers from 0.8 to 1.36

Description: Report presenting a flight investigation to determine the drag and stability at low lift coefficients of models of a modified-delta-wing airplane at a range of Mach and Reynolds numbers. A summary of the drag and stability data from the tests is provided.
Date: March 26, 1953
Creator: Mitcham, Grady L. & Blanchard, Willard S., Jr.
Partner: UNT Libraries Government Documents Department

The effect of nacelle combinations and size on the zero-lift drag of a 45 degree sweptback wing and body configuration as determined by free-flight tests at Mach numbers between 0.8 and 1.3

Description: Investigation of the effect on zero-lift drag of varying the size and number of symmetrically mounted nacelles on a 45 degree sweptback wing and body combination as determined by free-flight tests of rocket-propelled models over a range of Mach and Reynolds numbers. The nacelle configuration consisted of a twin-engine nacelle near the fuselage, a combination of single-engine nacelles at the wing tip and fuselage, a large nacelle at the wing tip, and a large nacelle near the fuselage.
Date: June 22, 1953
Creator: Hoffman, Sherwood & Pepper, William B., Jr.
Partner: UNT Libraries Government Documents Department

Drag of conical and circular-arc boattail afterbodies at Mach numbers from 0.6 to 1.3

Description: From Summary: "Drag characteristics of a series of related conical and circular-arc afterbodies are presented for Mach numbers from 0.6 to 1.3. Drag was obtained from pressure measurements on the boattail and solid base. The boattail angles tested ranged from 0 degrees to 45 degrees for ratios of base diameter to maximum body diameter ranging from 0 to 1.0."
Date: January 22, 1957
Creator: Silhan, Frank V. & Cubbage, James M., Jr.
Partner: UNT Libraries Government Documents Department

Comparative drag measurements at transonic speeds of rectangular sweptback NACA 65-009 airfoils mounted on a freely falling body

Description: From Summary: "Directly comparable drag measurements have been made of an airfoil with a conventional rectangular plan form and an airfoil with a sweptback plan form mounted on freely falling bodies. Both airfoils had NACA 65-009 sections and were identical in span, frontal area, and chord perpendicular to the leading edge. The sweptback plan form incorporated a sweepback angle of 45 degrees. The data obtained have been used to establish the relation between the airfoil drag coefficients and the free-stream Mach number over a range of Mach numbers from 0.90 to 1.27. The results of the measurements indicate that the drag of the sweptback plan form is less than 0.3 that of the rectangular plan form at a Mach number of 1.00 and is less than 0.4 that at a Mach number of 1.20."
Date: August 9, 1945
Creator: Mathews, Charles W. & Thompson, Jim Rogers
Partner: UNT Libraries Government Documents Department

Effect of wing sweep, taper, and thickness ratio on the transonic drag characteristics of wing-body combinations

Description: Report presenting the transonic drag characteristics of a series of wing-body combinations and their component parts using the free-fall method. The configurations examined had wings of various sweeps and thickness ratios mounted on identical bodies of fineness ratio 12.
Date: December 31, 1948
Creator: Thompson, Jim Rogers & Mathews, Charles W.
Partner: UNT Libraries Government Documents Department

Drag Measurements at Transonic Speeds of NACA 65-009 Airfoils Mounted on a Freely Falling Body to Determine the Effects of Sweepback and Aspect Ratio

Description: From Summary: "Drag measurements at transonic speeds on rectangular airfoils and on airfoils swept back 450 are reported. These airfoils, which were mounted on cylindrical test bodies, are part of a series being tested in free drops from high altitude to determine the effect of variation of basic airfoil parameters on airfoil drag characteristics at transonic speeds. These rectangular and swept-back airfoils had the same span, airfoil section (NACA 65-009), and chord perpendicular to the leading edge. The tests were made to compare the drag of rectangular and sweptback airfoils at a higher aspect ratio than had been used in a similar comparison reported previously."
Date: January 22, 1947
Creator: Mathews, Charles W. & Thompson, Jim Rogers
Partner: UNT Libraries Government Documents Department

Jet effects on the drag of conical afterbodies for Mach numbers of 0.6 to 1.28

Description: Report presenting an investigation at Mach numbers from 0.6 to 1.28 to determine the drag characteristics of a series of conical afterbodies with a cold sonic jet issuing from the base. Models investigated had boattail angles from 3 to 45 degrees, ratios of jet diameter to base diameter of 0.65 and 0.75, and values of the ratios of the base diameter to maximum diameter of 0.55, 0.70, and 0.85. Results regarding afterbody pressure distributions and afterbody drag are provided.
Date: April 12, 1957
Creator: Cubbage, James M., Jr.
Partner: UNT Libraries Government Documents Department

Some effects of body cross-sectional shape, including sunken-canopy design, on drag as shown by rocket-powered-model tests at Mach numbers from 0.8 to 1.5

Description: Report presenting free-flight tests made with four fin-stabilized bodies of fineness ratio 8.91 to determine the effect of body cross-sectional shape on body drag at a range of Mach and Reynolds numbers. Results regarding the curve of drag coefficients, drag on the nose and body, and body pressure drag are provided.
Date: July 1, 1952
Creator: Stoney, William E., Jr. & Putland, Leonard W.
Partner: UNT Libraries Government Documents Department

Flight measurements of base pressure on bodies of revolution with and without simulated rocket chambers

Description: Base pressures were measured on fin-stabilized bodies of revolution with and without rocket chambers and with and without a converging afterbody. At Mach numbers between 0.7 and 1.2, the results show that the presence of a "cold" rocket chamber increased the pressure (less suction) over the center portion of the bases. The effects of rocket chambers on pressures near the edge of the bases were not as consistent throughout the Mach number range nor as appreciable at most speeds as were the effects of pressures measured on the center line.
Date: April 1955
Creator: Peck, Robert F.
Partner: UNT Libraries Government Documents Department

Comparison of the transonic drag characteristics of two wing-body combinations differing only in the location of the 45 degree sweptback wing

Description: Report presenting the drag of a series of wing-body combinations by the free-fall method in order to provide information on the drag characteristics of promising transonic and supersonic airplane arrangements. Time histories, Mach number variations, and drag coefficients for several areas of the body are provided.
Date: December 8, 1947
Creator: Mathews, Charles W. & Thompson, Jim Rogers
Partner: UNT Libraries Government Documents Department

Experimental investigation of the effects of support interference on the drag of bodies of revolution at a Mach number of 1.5

Description: Testing was conducting to evaluate the effects of support interference on the drag characteristics of two bodies of revolution at zero angle of attack at Mach number 1.5. Drag and base-pressure measurements are made for a variety of Reynolds numbers to determine the effect of varying the length or diameter of the rear support.
Date: May 7, 1948
Creator: Perkins, Edward W.
Partner: UNT Libraries Government Documents Department

Investigation of the drag of various axially symmetric nose shapes of fineness ratio 3 for Mach numbers from 1.24 to 3.67

Description: Report presenting foredrag measurements made at zero angle of attack for a series of fineness ratio 3 nose shapes. The types of noses investigated included theoretically derived minimum drag shapes, hemispherically blunted cones, and other more common profiles. Results regarding hemispherically blunted cones, theoretical minimum drag nose shapes, and comparison of foredrag of all the force models are provided.
Date: November 6, 1952
Creator: Perkins, Edward W. & Jorgensen, Leland H.
Partner: UNT Libraries Government Documents Department

Performance characteristics of axisymmetric two-cone and isentropic nose inlets at Mach number 1.90

Description: Report presenting an experimental investigation at Mach number 1.90 to determine the overall performance capabilities of axisymmetric two-cone and isentropic nose inlets in terms of total-pressure recovery, mass flow, and external drags. At zero angle of attack, the external drag was separated into their components of cowl pressure, friction, and additive drags. Results regarding total-pressure recovery and mass-flow characteristics, total-pressure profiles at diffuser exit, cowl-pressure distributions and drag, zero-angle-of-attack component breakdown of external drag, and overall performance comparison are provided.
Date: September 7, 1955
Creator: Connors, James F. & Meyer, Rudolph C.
Partner: UNT Libraries Government Documents Department

Investigation of translating-spike supersonic inlet as means of mass-flow control at Mach numbers of 1.5, 1.8, and 2.0

Description: Report presenting an investigation in the supersonic wind tunnel on a 50 degree conical-spike inlet at three Mach numbers over a range of angles of attack. The additive-drag penalty associated with inlet mass-flow spillage was significantly reduced by using a translating-spike inlet rather than a fixed-geometry inlet.
Date: October 29, 1953
Creator: Gorton, Gerald C.
Partner: UNT Libraries Government Documents Department

The effect of bluntness on the drag of spherical-tipped truncated cones of fineness ratio 3 at Mach numbers 1.2 to 7.4

Description: Report presenting an investigation of the drag of spherically blunted conical models of fineness ratio 3 at a range of Mach and Reynolds numbers. Results of the tests showed that slightly blunted models had less drag than cones of the same fineness ratio through the Mach number range. Results regarding the total drag, wave drag, and viscous effects are provided.
Date: April 25, 1952
Creator: Sommer, Simon C. & Stark, James A.
Partner: UNT Libraries Government Documents Department

Fuselage-drag tests in the variable-density wind tunnel: streamline bodies of revolution, fineness ratio of 5

Description: From Summary: "Results are presented of the drag tests of six bodies of revolution with systematically varying shapes and with a fineness ratio of 5. The forms were derived from source-sink distributions, and formulas are presented for the calculation of the pressure distribution of the forms. The tests were made in the N.A.C.A. variable-density tunnel over a range of values of Reynolds number from about 1,500,000 to 25,000,000. The results show that the bodies with the sharper noses and tails have the lowest drag coefficients, even when the drag coefficients are based on the two-thirds power of the volume. The data shows the most important single characteristic of the body form to be the tail angle, which must be fine to obtain low drag."
Date: September 1937
Creator: Abbott, Ira H.
Partner: UNT Libraries Government Documents Department

Pressure distribution over a sharp-nose body of revolution at transonic speeds by the NACA wing-flow method

Description: Report presenting an investigation to obtain the pressure distribution over a sharp-nose body of revolution with a circular-arc profile and fineness ratio 6 at transonic speeds using the NACA wing-flow method. Results regarding the variation of pressure coefficient with Mach number, pressure distributions along the body axis, pressure drag, and effects of interference and horizontal gradient are provided.
Date: March 5, 1948
Creator: Danforth, Edward C. B. & Johnston, J. Ford
Partner: UNT Libraries Government Documents Department

The drag of airplane wheels, wheel fairings, and landing gears - 3

Description: The tests reported in this report conclude the investigation of landing-gear drag that has been carried out in the NACA 20-foot wind tunnel. They supplement earlier tests (reported in Technical Report No. 485) made with full-scale dummy wheels, wheel fairings, and landing gears intended for airplanes of 3,000 pounds gross weight and include tests of tail wheels and tail skids.
Date: November 21, 1934
Creator: Herrnstein, William H., Jr. & Biermann, David
Partner: UNT Libraries Government Documents Department

The drag of airplane wheels, wheel fairings, and landing gears 2: nonretractable and partly retractable landing gears

Description: This is the second report giving the results obtained in the NACA 20-foot wind tunnel on the drag due to landing gears. The present report gives the results of tests of nonretractable and partly retractable landing gears intended for heavier low-wing monoplanes of the transport and bomber type.
Date: June 21, 1934
Creator: Biermann, David & Herrnstein, William H., Jr.
Partner: UNT Libraries Government Documents Department