National Advisory Committee for Aeronautics (NACA) - 13 Matching Results

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Dynamic Response of Turbine-Blade Temperature to Exhaust-Gas Temperature for Gas-Turbine Engines

Description: "The frequency of blade temperature to exhaust gas temperature is presented for two locations in the blade and at several operating conditions. The frequency response was determined by Fourier analysis of transient data. Two analytical methods are presented, and results are compared with experimental data. Dynamic response of turbine-blade temperature to exhaust-gas temperature exhibited the form of an approximate first-order lag" (p. 1).
Date: February 20, 1952
Creator: Hood, Richard & Phillips, William E., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effects of systematically varying the spanwise and vertical location of an external store on the aerodynamic characteristics of an unswept tapered wing of aspect ratio 4 at Mach numbers of 1.41, 1.62, and 1.96

Description: Report presenting an investigation in the supersonic blowdown tunnel to determine the effects of an external store on the lift, drag, and pitching-moment characteristics of an unswept wing of aspect ratio 4 at Mach numbers of 1.41, 1.62, and 1.96.
Date: August 20, 1952
Creator: Jacobsen, Carl R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The effects on dynamic lateral stability and control of large artificial variations in the rotary stability derivatives

Description: This report presents the results of an investigation conducted in the Langley free-flight tunnel to determine the effects of large artificial variations of several rotary lateral-stability derivatives on the dynamic lateral stability and control characteristics of a 45 degree sweptback-wing airplane model. Calculations of the period and damping of the lateral motions and of the response to roll and yaw disturbances were made for correlation with the experimental results. The calculated results … more
Date: June 20, 1952
Creator: Schade, Robert O. & Hassell, James L., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Investigation From Mach Number 0.8 to 2.0 to Determine Some Effects of Wing-to-Tail Distance on the Longitudinal Stability and Control Characteristics of a 60 Degree Delta-Wing-Canard Missile

Description: Report presenting a flight investigation using rocket-powered models to determine some of the effects of wing-to-tail distance on the stability and control characteristics of a canard-missile configuration with 60 degree delta wings and control surfaces. Both models were tested over a range of Mach numbers from 0.8 to 2.0, and canard hinge moment and model drag data are presented. Testing indicated that additional fuselage length increases the lift-curve slope slightly and has very little effec… more
Date: June 20, 1952
Creator: Brown, Clarence A., Jr. & Lundstrom, Reginald R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Friction and surface damage of several corrosion-resistant materials

Description: Friction and surface damage of several materials that are resistant to corrosion due to liquid metals was studied in air. The values of kinetic friction coefficient at low sliding velocities and photomicrographs of surface damage were obtained. Appreciable surface damage was evident for all materials tested. The friction coefficients for the combinations of steel, stainless steel, and monel sliding against steel, stainless steel, nickel, Iconel, and Nichrome ranged from 0.55 for the monel-Incon… more
Date: February 20, 1952
Creator: Peterson, Marshall B. & Johnson, Robert L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation at Transonic Speeds of the Effect of a Positive-Lift Balancing Tab on the Hinge-Moment and Lift-Characteristics of a Full-Span Flap 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 tab and flap. The control device consisted of an auxiliary lifting surface (tab) mounted on the end of a boom which was linked to a full-span flap. The tab was found to be capable of reducing the flap hinge moment to zero through the angle of attack and Mach number range tested.
Date: November 20, 1952
Creator: Lockwood, Vernard E. & Fikes, Joseph E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary Free-Flight Investigation of the Effects of Rivets and Lap Joints on the Drag of Bodies at Zero Lift at Supersonic Mach Numbers to 2.1

Description: Memorandum presenting the effects of rivets and lap joints on the drag of bodies at zero lift at supersonic Mach numbers to 2.1 in free flight with rocket-propelled models. Four forward-facing lap joints 0.064 inch high, four similar lap joints facing rearward, and four double rows of 1/8-inch-diameter brazier head rivets were tested on a 5-inch-diameter body 56 inches long.
Date: August 20, 1952
Creator: Hopko, Russell N.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Preliminary Investigation of the Low-Amplitude Damping in Pitch of Tailless Delta- and Swept-Wing Configurations at Mach Numbers From 0.7 to 1.35

Description: Report presenting a flight investigation using four rocket-propelled models of low-aspect-ratio tailless configurations between Mach numbers 0.7 and 1.35. The configurations investigated were a 45 degree delta model with NACA 63A010 airfoil sections parallel to free stream, a 45 degree delta-wing model with NACA 63A006 airfoil sections parallel to free stream, a 37.5 degree swept-tapered wing model with NACA 64(sub 1)A012 sections perpendicular to quarter chord, and a 39 degree swept-tapered-wi… more
Date: August 20, 1952
Creator: D'Aiutolo, Charles T. & Parker, Robert N.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Skin-friction drag and boundary-layer transition on a parabolic body of revolution (NACA RM-10)at a Mach number of 1.6 in the Langley 4-by-4 foot supersonic pressure tunnel

Description: Report presenting an investigation at Mach number 1.6 and a range of Reynolds number of the skin-friction drag and boundary-layer transition of a body of revolution. The body had a parabolic-arc profile, a blunt base, and a fineness ratio of 12.2 (NACA RM-10). Results regarding the effect of surface condition, drag breakdown, and results of boundary-layer surveys are provided.
Date: May 20, 1952
Creator: Czarnecki, K. R. & Marte, Jack E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Temperature response of turbine-blade metal covered with oxide coatings supplied by fuel additives

Description: Report presenting an investigation to determine the effects of turbine-blade coatings, supplied by fuel additives, on heat transfer with combustor exhaust gases to an S-816 alloy blade. Two fuel additives were used. The results indicated that the fuel additives provided an oxide coating on the combustor-liner wall and other metal parts, including the blade, exposed to the exhaust gas.
Date: August 20, 1952
Creator: McCafferty, Richard J. & Butze, Helmut F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Theoretical performance of liquid ammonia, hydrazine and mixture of liquid ammonia and hydrazine as fuels with liquid oxygen biflouride as oxidant for rocket engines 1: mixture of liquid ammonia and hydrazine

Description: Theoretical performance for mixture of 36.3 percent liquid ammonia and 63.7 percent hydrazine with liquid oxygen bifluoride as rocket propellant was calculated on assumption of equilibrium composition during expansion for a wide range of fuel-oxidant and expansios ratios. Parameters included were specific impulse, combustion-chamber temperature, nozzle exit temperature, composition mean molecular weight, characteristic velocity, coefficient of thrust and ratio of nozzle-exit area to throat area… more
Date: February 20, 1952
Creator: Huff, Vearl N. & Gordon, Sanford
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Total-Pressure and Schlieren Studies of the Wakes of Various Canard Control Surfaces Mounted on a Missile Body at a Mach Number of 1.93

Description: Report presenting wind-tunnel studies of the wake behind eight types of canard control surfaces of equal span mounted on a missile body at Mach number 1.93. The effect of simulated external rocket boosters on the pressure field was also determined for three control-surface plan forms. The investigation also included the effect of end plates attached to the tips of one of the controls surfaces.
Date: November 20, 1952
Creator: Boatright, William B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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