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XC-35 gust research project: Preliminary analysis of the lateral distribution of gust velocity along the span of an airplane

Description: Report presenting measurements of the lateral distribution of effective gust velocity along the span of the XC-35 airplane in a variety of weather conditions. Six standard shapes were determined from the distributions: triangular, rectangular, first trapezoidal, second trapezoidal, unsymmetrical, and double triangular.
Date: March 1943
Creator: Moskovitz, A. I.

Yaw characteristics and sidewash angles of a 42 degree sweptback circular-arc wing with a fuselage and with leading-edge and split flaps at a Reynolds number of 5,300,000

Description: Report presenting testing of the low-speed aerodynamic characteristics in yaw of a 42 degree sweptback wing of circular-arc airfoil sections in the pressure tunnel. The wing had an aspect ratio of 3.94, taper ratio of 0.625, and no dihedral or twist. Results regarding lateral-stability parameters of plain wing, effect of wing flaps on lateral-stability parameters, effect of fuselage on lateral-stability parameters, a comparison with the NACA 64(sub 1)-112 wing, characteristics in the extended yaw range, and airflow characteristics in the region of a vertical tail are provided.
Date: December 10, 1947
Creator: Salmi, Reino J. & Fitzpatrick, James E.

Yaw characteristics of a 52 degree sweptback wing of NACA 64(sub 1)-112 section with a fuselage and with leading-edge and split flaps at Reynolds numbers from 1.93 x 10(exp 6) to 6.00 x 10(exp 6)

Description: Report presenting low-speed testing in the pressure tunnel to determine the aerodynamic characteristics in yaw of a 52 degree sweptback wing with aspect ratio 2.88 and taper ratio 0.625 with NACA 64(sub 1)-112 airfoil sections. Testing included an investigation of the effects on the lateral stability of a fuselage and leading-edge and split flaps. Results regarding the lateral stability parameters of a plain wing, effect of flaps on the lateral stability parameters, effect of scale, and airflow characteristics in the region of a vertical tail are provided.
Date: November 8, 1948
Creator: Salmi, Reino J.

Yawed-Landing Investigation of a Model of the Convair Y2-2 Airplane, TED No. NACA DE 363

Description: A model of the Convair Y2-2 airplane was tested in Langley tank no. 2 to determine whether satisfactory stability in yawed landings was possible with a certain ventral fin. Free-body landings were made in smooth and rough water at two speeds and two rates of descent with the model yawed 15deg. The behavior of the model was determined by visual observations and from motion-picture re.cords. It was concluded that satisfactory stability was possible with the ventral fin as tested but that the characteristics of the model shock absorbers and the settings of the elevon control surfaces had an appreciable influence on behavior.
Date: 1951
Creator: Hoffman, Edward L. & Fisher, Lloyd J.

Zero-angle-of-attack performance of two-dimensional inlets near Mach number 3

Description: An extensive program was undertaken to investigate the effect of several geometric variables on the performance of two-dimensional inlets. This investigation included inlets having single-wedge, double-wedge, and isentropic compression ramps with various side-plate configurations and subsonic diffusers. The tests were conducted over a range of Reynolds number based on inlet height from 0.50 to 2.67(sup x)10(sup 6). Generally, the performance levels of the two-dimensional inlets were somewhat below those obtained previously with comparable axisymmetric models. At Mach number 3.05 the optimum total-pressure recovery was obtained with an isentropic inlet which compressed the external flow to a Mach number of 1.88. Rectangular side plates and a long high-exit-Mach-number subsonic diffuser with filleted corners were used with this inlet. A critical total-pressure recovery of 0.71 was realized with a corresponding mass-flow ratio of 0.965. Subcritical stability to a mass-flow ratio of 0.60 was obtained.
Date: February 29, 1956
Creator: Woollett, Richard R. & Connors, James F.

The zero-lift drag of a 60 degree delta-wing-body combination (AGARD model 2) obtained from free-flight tests between Mach numbers of 0.8 and 1.7

Description: From Summary: "The zero-lift drag of a 60 degree delta-wing-body combination (designated AGARD model 2) has been determined by free-flight tests of two models between Mach numbers of 0.8 and 1.7. These Mach numbers correspond to Reynolds numbers, based on body length, of 4 x 10(exp 6) and 12 x 10(exp 6), respectively. An estimate of the drag of the configuration was made by summing the estimates of the drag of the various components. The agreement between measured and estimated drag is good."
Date: April 1954
Creator: Piland, Robert O.

Zero-lift drag of a large fuselage cavity and a partially submerged store on a 52.5 degree sweptback-wing-body configuration as determined from free-flight tests at Mach numbers of 0.7 to 1.53

Description: Report presenting a free-flight investigation of a rocket-propelled model at a range of Mach numbers from 0.7 to 1.53 to determine the drag at zero lift of a configuration with a large fuselage cavity and partially submerged store. Testing was performed out of a desire to determine if large stores can be attached to aircraft wings without negatively affecting the aerodynamic properties. Results regarding total drag and pressure drag are provided.
Date: February 26, 1957
Creator: Hoffman, Sherwood

Zero-lift drag of a series of bomb shapes at Mach numbers from 0.60 to 1.10

Description: Report presenting zero-lift drag data obtained on a series of six bomb shapes. Five configurations had the same body shape with different body-surface conditions and profile and plan form of fins, and the sixth had a different and longer body shape. Results regarding the effect of blunt trailing edge, blunt leading edge, fin thickness, and body surface are provided.
Date: July 26, 1956
Creator: Stoney, William E., Jr. & Royall, John F.

The zero-lift drag of a slender body of revolution (NACA RM-10 research model) as determined from tests in several wind tunnels and in flight at supersonic speeds

Description: From Summary: "The results of tests of a slender body of revolution designated the NACA rm-10 have been compiled from various NACA test facilities. Zero-lift drag data are presented for a Reynolds number range from about 1 x 10(6) to 40 x 10(6) from several wind tunnels and from about 12 x 10(6) to 140 x 10(6) from free-flight tests. The Mach numbers covered include 1.5 to 2.4 for the wind-tunnel data and 0.85 to 2.5 for the flight results. The wind tunnel models were tested with and without 60 degree sweptback stabilizing fins and the flight models were tested with stabilizing fins."
Date: April 16, 1953
Creator: Evans, Albert J.

The zero-lift drag of a slender body of revolution (NACA RM-10 research model) as determined from tests in several wind tunnels and in flight at supersonic speeds

Description: Presents zero-lift drag data of an NACA RM-10 slender body of revolution with and without stabilizing fins attached. The results from several wind tunnels and in flight are compared. The results cover a Reynolds number range from about 1 time 10 to the 6th power to 40 times 10 to the 6th power for the flight models. The Mach numbers covered include 1.5 to 2.4 in the wind tunnels and 0.85 to 2.5 in flight.
Date: April 1953
Creator: Evans, Albert J.

The Zero-Lift Drag of Several Configurations of the XAAM-N-2 Pilotless Aircraft. TED No. NACA DE332

Description: Free-flight tests have been made to determine the zero-lift drag of several configurations of the XAAM-N-2 pilotless aircraft. Base-pressure measurements were also obtained for some of the configurations. The results show that increasing the wing-thickness ratio from 4 to 6 percent increased the wing drag by about 100 percent at M = 1.3 and by about 30 percent at M = 1.8. Increasing the nose fineness ratio from 5.00 to 6.25 reduced the drag coefficient of the wingless models a maximum of about 0.030 (10 percent) at M = 2.0. A corresponding change in nose shape for the winged models decreased the drag coefficient by about 0.05 in the Mach number range from 1.1 to 1.4; at Mach numbers greater than 1.6 no measurable reduction in drag coefficient was obtained. The drag of the present Sparrow fuselage is less than that of a parabolic fuselage which could contain the same equipment.
Date: March 16, 1950
Creator: Hall, James R. & Sandahl, Carl A.

Zero-lift drag of several conical and blunt nose shapes obtained in free flight at Mach numbers of 0.7 to 1.3

Description: Report presenting the zero-lift drag characteristics of seven nose shapes on a slender body of revolution in free flight between the Mach numbers of 0.7 and 1.3. Some of the nose shapes included a spherical segment, flat face with a sharp shoulder, flat face with a rounded shoulder, 30 degree and 40 degree total-angle cones, and a spherical segment with two different length spikes. Results regarding drag coefficients and performance for the various shapes are provided.
Date: March 23, 1954
Creator: Piland, Robert O. & Putland, Leonard W.

Zero-lift drag of the Chance Vought Regulus II missile at Mach numbers between 0.8 and 2.2 as determined from the flight tests of two 0.12-scale models: TED No. NACA AD 398

Description: Report presenting testing of two scale models of the Chance Vought Regulus II missile to investigate its drag characteristics for a range of Mach numbers from 0.8 to 2.2. Due to some of the differences between the observed drag values and previous testing, the exact drag level of the configuration tested is still in question. Results regarding total drag and external drag are provided.
Date: July 27, 1954
Creator: Church, James D.

Zero-lift drag of the chance vought regulus it missile at mach numbers between 0.8 and 2.2 as determined from the flight tests of two 0.12-scale models

Description: Report discussing testing of two models of the Chance Vought Regulus II missile to determine its drag characteristics for a range of Mach numbers. The measured total-drag-coefficient data was extrapolated to external-drag-coefficient data and presented.
Date: July 15, 1954
Creator: Church, James D.

The zero-lift wave drag of a particular family of unswept, tapered wings with linearly varying thickness ratio

Description: Report presenting the zero-lift wave drag of a particular family of unswept, tapered wings with linearly varying thickness ratio and symmetrical parabolic-arc sections. It is found that the variable-thickness-ratio wings can be used to advantage with no serious structural penalties if the wings have the same given root thickness ratio or internal volume. Results regarding the given frontal area and given volume are provided.
Date: May 1955
Creator: Henderson, Arthur, Jr. & Goodwin, Julia M.