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  Partner: UNT Libraries Government Documents Department
 Collection: National Advisory Committee for Aeronautics Collection
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

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

Date: December 10, 1947
Creator: Salmi, Reino J & Fitzpatrick, James E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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)

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)

Date: November 8, 1948
Creator: Salmi, Reino J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Yawed-Landing Investigation of a Model of the Convair Y2-2 Airplane, TED No. NACA DE 363

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

Date: January 1, 1950
Creator: Hoffman, Edward L. & Fisher, Lloyd J.
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.
Contributing Partner: UNT Libraries Government Documents Department
Zero-angle-of-attack performance of two-dimensional inlets near Mach number 3

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

Date: February 29, 1956
Creator: Woollett, Richard R & Connors, James F
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.
Contributing Partner: UNT Libraries Government Documents Department
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

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

Date: April 1, 1954
Creator: Piland, Robert O
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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

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

Date: February 26, 1957
Creator: Hoffman, Sherwood
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Zero-lift drag of a series of bomb shapes at Mach numbers from 0.60 to 1.10

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

Date: July 26, 1956
Creator: Stoney, William E, Jr & Royall, John F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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

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

Date: January 1, 1954
Creator: Evans, Albert J
Description: 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. Comparison of the data obtained in the several wind tunnels for the body alone (without fins) shows good agreement between the different facilities. There are unexplained differences however between the wind-tunnel results with fins attached and flight results, as well as differences between full-scale and half-scale flight models, which cannot be explained as an effect of Reynolds number.
Contributing Partner: UNT Libraries Government Documents Department
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

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

Date: April 1, 1953
Creator: Evans, Albert J
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.
Contributing Partner: UNT Libraries Government Documents Department
The Zero-Lift Drag of Several Configurations of the XAAM-N-2 Pilotless Aircraft. TED No. NACA DE332

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

Date: March 16, 1950
Creator: Hall, James R. & Sandahl, Carl A.
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.
Contributing Partner: UNT Libraries Government Documents Department