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The effects of a small jet of air exhausting from the nose of a body of revolution in supersonic flow

Description: Report presenting the results of an investigation to determine the effects of a small jet of air exhausting from the nose of an elliptical body of revolution upon boundary-layer transition and the viscous, pressure, and total drag of the forebody at three body stations at Mach number 1.62. The jet effects on body pressure, pressure variations, boundary-layer transition, and total drag are provided.
Date: November 12, 1952
Creator: Love, Eugene S.

Control characteristics at transonic speeds of a linked flap and spoiler on a tapered 45 degrees sweptback wing of aspect ratio 3

Description: Report presenting an investigation at transonic speeds to determine the control characteristics of a linked flap and spoiler. The control consisted of a linked combination of a quarter-span inboard plug-type spoiler and a full-span flap. Results regarding the hinge-moment, pitching-moment, lift, and rolling-moment are provided.
Date: July 11, 1952
Creator: Lockwood, Vernard E. & Fikes, Joseph E.

Investigation of flutter characteristics of three low-aspect-ratio all-movable half-span control surfaces at Mach numbers from 1.49 to 2.87

Description: Report presenting the results of a supersonic flutter investigation of three low-aspect-ratio control surfaces, two which had all-movable controls and one with a fixed cutout. Experimental results are provided and compared to calculations using the piston theory for plan form 2. Modifications for improving the flutter of the various control surfaces are also described.
Date: May 2, 1958
Creator: Morgan, Homer G.; Figge, Irving E. & Presnell, John G., Jr.

Investigation of engine performance and high-temperature properties of precision-cast turbine blades of high carbon Stellite 21 and controlled grain-size-Stellite 21

Description: Report presenting an investigation to determine the effect of controlled grain size and increased carbon content on engine performance and high-temperature properties of precision-cast Stellite 21 turbine blades. Results regarding blade stresses, engine operation, and metallurgical examination are provided.
Date: June 23, 1952
Creator: Yaker, Charles; Garrett, Floyd B. & Sikora, Paul F.

Investigation of equilibrium temperatures and average laminar heat-transfer coefficients for the front half of swept circular cylinders at a Mach number of 6.9

Description: Report presenting the average heat-transfer coefficients and equilibrium temperatures for the front half of an isothermal cylinder with a laminar boundary layer as determined by wind tunnel testing at Mach number 6.9 and a range of Reynolds numbers and sweep angles.
Date: August 18, 1955
Creator: Feller, William V.

Force, moment, and pressure-distribution characteristics of rectangular wings at high angles of attack and supersonic speeds

Description: Report presenting experimental force and moment data for rectangular wings of aspect ratios 1, 2, and 3 at a range of angles of attack and Mach numbers. Shock-expansion theory was found to adequately predict the span load distribution in the two-dimensional flow region below the shock-detachment angle. Results regarding basic physical data, the attached regime, and the detached regime are provided.
Date: February 13, 1956
Creator: Pitts, William C.

Aerodynamic characteristics at transonic speeds of a tapered 45 degree sweptback wing of aspect ratio 3 having a full-span flap type of control with overhang balance : transonic-bump method

Description: From Introduction: "This paper presents the aerodynamic characteristics of low-aspect-ratio sweptback wing having a full-span flap type of control employing an overhanging balance of 50 percent of the flap chord.The main purpose of this investigation was to determine if overhang balances are an effective means of reducing the hinge moments of flap type of controls at transonic speeds."
Date: January 25, 1952
Creator: Lockwood, Vernard E. & Hagerman, John R.

High-Speed Drag and Opening Characteristics of a Kaman Rotochute Model

Description: Report presenting an experimental investigation in the 7- by 10-foot tunnel in a range of Mach numbers to determine the drag and opening characteristics of a model of a Kaman Aircraft Corporation Rotochute. The Rotochute is a two-bladed flapping rotor with governor-controlled blades designed for lowering cargo containers from high-speed aircraft tested at various Mach numbers simulating constant rates of descent.
Date: June 10, 1954
Creator: Lockwood, Vernard E.

Vapor pressures and calculated heats of vaporization of concentrated nitric acid solutions in the composition range 71 to 89 percent nitrogen dioxide, 1 to 10 percent water, and in the temperature range 10 to 60 degrees C

Description: From Summary: "Total vapor pressures were measured for 16 acid mixtures of the ternary system nitric acid, nitrogen dioxide, and water within the temperature range 10 degrees to 60 degrees Celsius, and with the composition range 71 to 89 weight percent nitric acid, 7 to 20 weight percent nitrogen dioxide, and 1 to 10 weight percent water. Heats of vaporization were calculated from the vapor pressure measurements for each sample for the temperatures 25, 40, and 60 degrees Celsius. The ullage of the apparatus used for the measurements was 0.46. Ternary diagrams showing isobars as a function of composition of the system were constructed from experimental and interpolated data for the temperatures 25, 40, 45, and 60 degrees C and are presented herein."
Date: February 5, 1954
Creator: McKeown, A. B. & Belles, Frank E.

Flame quenching by a variable-width rectangular-slot burner as a function of pressure for various propane-oxygen-nitrogen mixtures

Description: Flame quenching by a variable-width rectangular-slot burner as a function of pressure for various propane-oxygen-nitrogen mixtures was investigated. It was found that for cold gas temperatures of 27 degrees C, pressures of 0.1 ro 1.0 atmosphere, and volumetric oxygen reactions of the oxidant of 0.17, 0.21, 0.30, 0.50, and 0.70, the relation between pressure p and quenching distance d is approximately given by d (unity) p (superscript -r) with r = 1, for equivalence ratios approximately equal to one. The quenching equation of Simon and Belles was tested. For equivalence ratios less than or equal to unity, this equation may by used, together with one empirical constant, to predict the observed quenching distance within 4.2 percent. The equation in it's present form does not appear to be suitable for values of the equivalence ratio greater than unity. A quantitative theoretical investigation has also been made of the error implicit in the assumption that flame quenching by plane parallel plates of infinite extent is equivalent to that of a rectangular burner. A curve is presented which relates the magnitude of this error to the length-to-width ratio of the rectangular burner.
Date: January 28, 1954
Creator: Berlad, Abraham L

An exploratory investigation at Mach numbers of 2.50 and 2.87 of a canard bomber-type configuration designed for supersonic cruise flight

Description: Report presenting results for a canard bomber-type configuration designed for supersonic cruise flight at Mach numbers 2.50 and 2.87 and over a range of angles of attack and angles of sideslip. Results regarding longitudinal characteristics and lateral stability are provided. The original configuration was directionally unstable at low angles of attack, but satisfactory directional stability could be obtained using upper-surface vertical fins.
Date: April 15, 1958
Creator: Kelly, Thomas C.; Carmel, Melvin M. & Gregory, Donald T.

Exploratory investigation of external stores in the aerodynamic characteristics of a 1/16-scale model of the Douglas D-558-II research airplane at a Mach number of 2.01

Description: Report presenting an investigation of stores on the Douglas D-558-II research airplane in the wind tunnel and in flight using various store configurations. The drag measured for all store configurations was high, from two to three times the free-air drag estimated for the store and pylon. Results regarding longitudinal characteristics and lateral characteristics are provided.
Date: August 25, 1954
Creator: Smith, Norman F.

Exploratory investigation of static- and base-pressure increases resulting from combustion of aluminum borohydride adjacent to body of revolution in supersonic wing tunnel

Description: Report presenting pressure distribution associated with the stable combustion of aluminum borohydride about a body of revolution in a wind tunnel at Mach number 2.47. Pressure increases on the cylindrical and base surfaces of the model were measured. Results regarding the burning and associated flow phenomena, axial and meridional static-pressure data obtained during combustion, and base-pressure data during combustion are provided.
Date: October 2, 1957
Creator: Serafini, John S.; Dorsch, Robert G. & Fletcher, Edward A.

Exploratory investigation at high and low subsonic Mach numbers of two experimental 6-percent-thick airfoil sections designed to have high maximum lift coefficients

Description: Report presenting an investigation to determine if thin airfoils with increased values of low-speed maximum lift coefficient but also retain the basic advantages of thin sections at high Mach numbers can be developed. Several experimental thin airfoil sections were developed from an analysis of airfoil data and two of them were investigated at high and low subsonic Mach numbers. Results regarding the low-speed characteristics and high-speed characteristics are provided.
Date: December 14, 1951
Creator: Loftin, Laurence K., Jr. & von Doenhoff, Albert E.

Flight determination of the pressure recovery and drag characteristics of a twin side-inlet model at transonic speeds

Description: Report presenting free-flight and free-jet testing of a twin side-inlet configuration, including a pilot's canopy and a wheel-well fairing, between a range of Mach numbers from 0.8 to 1.55. Using side inlets provides two important advantages: the inlet can be located closer to the engine and it frees up the nose for other uses. Results regarding the effects of oscillating flow, external-drag coefficient, and total-pressure recovery are provided.
Date: July 30, 1953
Creator: Carter, Howard S. & Merlet, Charles F.