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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 be… more
Date: February 29, 1956
Creator: Woollett, Richard R. & Connors, James F.
Item Type: Refine your search to only Report
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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
Item Type: Refine your search to only Report
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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.
Item Type: Refine your search to only Report
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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… more
Date: March 16, 1950
Creator: Hall, James R. & Sandahl, Carl A.
Item Type: Refine your search to only Report
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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.
Item Type: Refine your search to only Report
open access

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

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.
Item Type: Refine your search to only Report
open access

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.
Item Type: Refine your search to only Report
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