National Advisory Committee for Aeronautics (NACA) - 231 Matching Results

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The Theory of Propellers 2: Method for Calculating the Axial Interference Velocity

Description: "A technical method is given for calculating the axial interference velocity of a propeller. The method involves the use of certain weight functions P, Q, and F. Numerical values for the weight functions are given for two-blade, three-blade, and six-blade propellers" (p. 53).
Date: September 19, 1944
Creator: Theodorsen, Theodore
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Thermal Stability of Pentaborane in the Range 329 to 419 Degrees F

Description: "The thermal stability of pentaborane has been determined in the temperature range 329 degrees to 419 degrees Fahrenheit by measuring the increase with time in the formation of nonvolatile residue. A relationship was established between the thermal stability and the temperature. The expression permitted extrapolation to obtain the stability of pentaborane at either high temperatures and short times or at ambient temperatures and long times" (p. 1).
Date: December 19, 1956
Creator: McDonald, Glen E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Transonic Aerodynamic Characteristics of a 1/15-Scale Model of the Convair B-58 Airplane

Description: Report presenting an investigation of a model of the Convair B-58 airplane weapons system in the transonic tunnel for a range of Mach and Reynolds numbers. Results regarding drag characteristics, lift-curve slope, and longitudinal stability parameter are provided.
Date: October 19, 1956
Creator: Swihart, John M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Transonic Aerodynamic Characteristics of a 1/15-Scale Model of the Convair B-58 Airplane

Description: Report presenting an investigation of a model of the Convair B-58 airplane weapons system, including under conditions of long-range subsonic cruise and a supersonic dash. Results regarding drag characteristics, lift-curve slope, and longitudinal stability parameter are provided.
Date: October 19, 1956
Creator: Swihart, John M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A transonic wind-tunnel investigation of the characteristics of a twisted and cambered 45 degree sweptback wing-fuselage configuration

Description: Report presenting an investigation in the 8-foot transonic tunnel to determine the effects of twist and camber on the aerodynamic characteristics of a sweptback wing-fuselage configuration. The wing had 45 degrees sweepback of the 0.25 chord, an aspect ratio of 4, a taper ratio of 0.6, and NACA 65A-series airfoil sections with 6-percent thickness distribution parallel to the plane of symmetry. Results regarding the lift characteristics, drag characteristics, and pitching-moment characteristics … more
Date: December 19, 1952
Creator: Harrison, Daniel E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Turbojet engine investigation of effect of thermal shock induced by external water-spray cooling on turbine blades of five high-temperature alloys

Description: Report presenting an investigation of the thermal-shock effect of water-spray impingement upon turbine rotor blades subjected to rated engine operating conditions using external water-spray cooling. Turbine-blade cooling water was turned on and off in cycles which employed either sudden or gradual injection of cooling water. Results regarding blades modified and unmodified for rotating injection are provided.
Date: December 19, 1955
Creator: Freche, John C. & Hickel, Robert O.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Two-dimensional transonic investigation of flows and forces on a 9-percent-thick airfoil with 30-percent-chord flap

Description: Report presenting an investigation to measure the pressures on and observe by schileren photography the flow about an NACA 65A009 airfoil with a 30-percent-chord trailing-edge flap in transonic flow. The results indicate that the flows over the flap are subject to changes from subsonic to supersonic values, which are dependent on combinations and variations in Mach number, angle of attack, and flap deflection.
Date: February 19, 1957
Creator: Lindsey, Walter F. & Pitts, Robert G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Two-Dimensional Wind-Tunnel Investigation of Two NACA 6-Series Airfoils With Leading-Edge Slats

Description: Report presenting an investigation of two NACA 6-series airfoils, the NACA 64(sub)1-212 and NACA 65A109 with leading edge slats and split flaps deflected 60 degrees. Information about optimum slat positions, airfoil section lift characteristics, pitching-moment characteristics, and effect of roughness on the lift characteristics was obtained.
Date: January 19, 1949
Creator: Gottlieb, Stanley M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Use of an Aerodynamically Pulsed All-Movable Horizontal Tail to Obtain Longitudinal Characteristics of Rocket-Powered Models in Free Flight and Some Initial Results From an Arrow-Wing-Body-Tail Configuration

Description: Report presenting the application of an aerodynamically pulsed horizontal tail to determine experimentally the longitudinal aerodynamic characteristics of a rocket-powered model in free flight. Results regarding time history, lift and drag, and tail effectiveness and downwash are provided.
Date: May 19, 1952
Creator: Gillespie, Warren, Jr. & Dietz, Albert E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-tunnel investigation at low speed of static and yawing characteristics of a 0.085-scale model of the Chance Vought XF8U-1 airplane: TED No. NACA DE 392

Description: Report presenting an investigation in the stability tunnel to determine the low-speed yawing derivatives of a 0.085-scale model of the Chance Vought XF8U-1 airplane and to determine the static longitudinal and static lateral stability characteristics in order to provide a basis for comparison with other data sources.
Date: January 19, 1954
Creator: Jaquet, Byron M. & Williams, James L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-tunnel investigation at low speed to determine aerodynamic properties of a jettisonable nose section with circular cross section

Description: Report presenting the aerodynamic properties of a model of a jettisonable nose section with a circular cross section as determined at low speed from an investigation in the 20-foot free-spinning tunnel. The results indicated that the aerodynamic characteristics of the nose were greatly affected by proximity to the fuselage. Even for a stabilized nose, it may be necessary to eject the nose forward forcibly in order to prevent high accelerations along the backbone of the pilot.
Date: May 19, 1950
Creator: Goodwin, Roscoe H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Wind-Tunnel Investigation at Low Speeds of the Aerodynamic Characteristics of Various Spoiler Configurations on a Thin 60 Degrees Delta Wing

Description: Report presenting an investigation in the 300 mph tunnel to determine the applicability of spoilers as lateral-control devices on thin delta wings. The wing used in testing had a thickness ratio of 1.5 percent at the root and a maximum ratio of 4.5 percent at 66.7 percent wing semispan, 60 degree sweepback at the leading edge, 0 degree sweep of the trailing edge, an aspect ratio of 2.31, and a taper ratio of 0. Results regarding the effect of spoiler location and angular placement, effect of sp… more
Date: November 19, 1952
Creator: Wiley, Harleth G. & Solomon, Martin
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Wind-Tunnel Investigation of Bomb Release at a Mach Number of 1.62

Description: Memorandum presenting a model bomb-release investigation conducted in the 9-inch supersonic tunnel at a Mach number of 1.62 to determine what first-order interference effects are involved in making releases at supersonic speeds and, in some cases, to ascertain what modifications might be made to obtain near-level drops. The results of these tests indicate that the interference effects of the fuselage or wing-pylon upon the bomb release are, in most cases, adverse.
Date: March 19, 1954
Creator: Rainey, Robert W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation of Static Lateral and Longitudinal Stability Characteristics of a 1/62-Scale Model of the X-1E Airplane at Combined Angles of Attack and Sideslip at Supersonic Speeds

Description: Report presenting an investigation to determine the static longitudinal and lateral stability characteristics of a model of X-1E airplane at combined angles of attack and sideslip. Results regarding the static longitudinal and lateral force and moment characteristics and stability derivatives are provided.
Date: September 19, 1957
Creator: Henderson, Arthur, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation of the Descent Characteristics of Bodies of Revolution Simulating Anti-Personnel Bombs

Description: "An investigation has been conducted in the Langley 20-foot free spinning tunnel to study the relative behavior in descent of a number of homogeneous balsa bodies of revolution simulating anti-personnel bombs with a small cylindrical exploding device suspended approximately 10 feet below the bomb. The bodies of revolution included hemispherical, near-hemispherical, and near-paraboloid shapes. The ordinates of one near-paraboloid shape were specified by the Office of the Chief of Ordnance, U. S.… more
Date: December 19, 1951
Creator: Scher, Stanley H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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