National Advisory Committee for Aeronautics (NACA) - 155 Matching Results

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A Comparison of Flight-Measured Carrier- Approach Speeds With Values Predicted by Several Different Criteria for 41 Fighter-Type Airplane Configurations

Description: Memorandum presenting lift and drag characteristics that have been determined in flight in the landing-approach configuration on 41 jet-propelled fighter-type airplane arrangements, including various wing boundary-layer-control installations. Minimum comfortable approach speeds for carrier-type landings were evaluated for these airplanes by four test pilots. Results regarding the presentation of data, methods for the prediction of minimum comfortable approach speed, reasons for limiting approac… more
Date: May 8, 1958
Creator: White, Maurice D.; Schlaff, Bernard A. & Drinkwater, Fred J., III
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Comparison of Flight-Measured Carrier-Approach Speeds With Values Predicted by Several Different Criteria for 41 Fighter-Type Airplane Configurations

Description: Report presenting lift and drag characteristics in the landing-approach configuration on 41 jet-propelled fighter-type airplane arrangements using flight testing. Minimum comfortable approach speeds were evaluated by four test pilots. Suggestions for achieving optimal speeds for approach under various conditions are also provided.
Date: May 8, 1958
Creator: White, Maurice D.; Schlaff, Bernard A. & Drinkwater, Fred J., III
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Heat Transfer for Mach Numbers Up to 2.2 and Pressure Distributions for Mach Numbers Up to 4.7 From Flight Investigations of a Flat-Face-Cone and a Hemisphere-Cone

Description: Report presenting testing of two blunt-nose models, a flat-face-cone and a hemisphere-cone, at Mach numbers up to 4.7. The main purpose was to determine information about heating rates and transition for different blunt nose shapes for long-range ballistic missiles. Information about pressure measurements and heat transfer is provided.
Date: May 8, 1958
Creator: Speegle, Katherine C.; Chauvin, Leo T. & Heberlig, Jack C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of an All-Movable Control Surface at a Mach Number of 6.86 for Possible Flutter

Description: Memorandum presenting results of tests for possible flutter of a dynamically and elastically scaled model of a proposed all-movable horizontal tail surface for the North American X-15 airplane. Tests at Mach number 6.86 were made on the scaled model and on several other configurations with lower stiffnesses.
Date: May 8, 1958
Creator: Lauten, William T., Jr.; Levey, Gilbert M. & Armstrong, William O.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of an All-Moveable Control Surface at a Mach Number of 6.86 for Possible Flutter

Description: "Results of tests for possible flutter of a dynamically and elastically scaled model of a proposed all-movable horizontal tail surface for the North American X-15 airplane are presented herein. Tests at a Mach number of 6.86 were made on the scaled model and on several other configurations having lower stiffness. Flexibility influence coefficients and calculated modes and frequencies for the weakest configuration are presented" (p. 1).
Date: May 8, 1958
Creator: Lauten, William T., Jr.; Levey, Gilbert M. & Armstrong, William O.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Performance of Basic XJ79-GE-1 Turbojet Engine and Its Components

Description: Memorandum presenting an investigation to determine the performance of the XJ79-GE-1 turbojet engine and its components, while operating as integral parts of the engine, conducted in an altitude test chamber. Data were obtained over a range of Reynolds number indices and for various settings of the variable compressor stators and variable-area exhaust nozzle from fully open to fully closed positions. Results regarding the component performance and engine performance are provided.
Date: May 8, 1958
Creator: Campbell, Carl E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tests of Aerodynamically Heated Multiweb Wing Structures in a Free Jet at Mach Number 2: Four Aluminum-Alloy Models of 20-Inch Chord and Span With 0.064-Inch-Thick Skin, 0.025-Inch-Thick Ribs and Webs, and Zero, One, Two, or Three Chordwise Ribs

Description: Report presenting testing of four multiweb wing models were tested at Mach number 2 in a free jet to investigate structural effects of aerodynamic heating and loading. All of the models were the same except for the number of chordwise internal stiffening ribs; each had zero, one, two, or three. Results regarding laboratory vibration tests, jet tests, model behavior, temperatures, stresses, and discussion of failure are provided.
Date: May 8, 1958
Creator: Davidson, John R.; Rosecrans, Richard & Vosteen, Louis F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Supersonic Wave Interference Affecting Stability

Description: Some of the significant interference fields that may affect stability of aircraft at supersonic speeds are briefly summarized. Illustrations and calculations are presented to indicate the importance of interference fields created by wings, bodies, wing-body combinations, jets, and nacelles.
Date: March 8, 1958
Creator: Love, Eugene S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Results of the Flight Test of a 0.13-Scale Rocket-Boosted Model of the McDonnell F4H-1 Airplane Between Mach Numbers of 0.20 and 1.90

Description: Report discussing tests performed with a rocket-boosted model of the McDonnell F4H-1 airplane at transonic and supersonic speeds. Special attention is given to the external drag coefficient at various Mach numbers. Large pitching oscillations were also noted at Mach numbers between 0.20 and 1.17, which made it impossible to determine the drag at that range.
Date: November 8, 1957
Creator: Hastings, Earl C., Jr. & Dickens, Waldo L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Results of the flight test of a 0.13-scale rocket-boosted model of the McDonnell F4H-1 airplane between Mach numbers of 0.20 and 1.90: TED No. NACA AD 3115

Description: From Summary: "A flight test was conducted with a 0.13-scale rocket-boosted model of the McDonnell F4H-1 airplane configuration at transonic and supersonic speeds. The external drag coefficient varied from a value of 0.044 at a Mach number of 1.17 to 0.045 at a Mach number of 1.40 and then decreased to 0.041 at a Mach number of 1.90. The limited oscillatory data available indicate the existence of a coupled longitudinal-lateral motion in the Mach number range from 0.20 to 1.17."
Date: November 8, 1957
Creator: Hastings, Earl C., Jr. & Dickens, Waldo L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tabulated Pressure Data for a Series of Controls on a 40 Degree Sweptback Wing at Mach Numbers of 1.61 and 2.01

Description: "An investigation has been made at Mach numbers of 1.61 and 2.01 and Reynolds numbers of 1.7 x l0(exp 6) and 3.6 x l0(exp 6) to determine the pressure distributions over a swept wing with a series of 14 control configurations. The wing had 40 deg of sweep of the quarter-chord line, an aspect ratio of 3.1, and a taper ratio of 0.4. Measurements were made at angles of attack from 0 deg to +/- 15 deg for control deflections from -60 deg to 60 deg. This report contains tabulated pressure data for t… more
Date: November 8, 1957
Creator: Lord, Douglas R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Chemical igniters for starting jet fuel - nitric acid rockets

Description: Report presenting experiments in a 200-pound-thrust jet fuel-nitric acid rocket with an axial-flow igniter employing the hypergolic alkyl thiosphosphite-nitric acid system. No combustion instability was observed in the igniter, but many of the main-stage runs exhibited low-frequency oscillations.
Date: October 8, 1957
Creator: Morrell, Gerald & Ladanyi, Dezso J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Structural Design and Engine Evaluation of an Air-Cooled Turbine Blade Composed of Corrugation and a Semistrut for Operation at a Tip Speed of 1200 Feet Per Second

Description: Report presenting an investigation of an air-cooled turbine rotor blade consisting of an internal part-span structural strut, corrugated cooling surfaces, and a thin outer shell. The effects on stresses and blade lift of varying strut length, shell thickness, and corrugation dimensions are provided. Testing occurred with the X-40 strut - A-286 shell combination and the S-816 strut - L-605 combination.
Date: October 8, 1957
Creator: Kemp, Richard H.; Meyer, André J., Jr. & Morgan, William C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Synthesis and Hydrolysis-Rate Studies of Decaborane Derivatives

Description: Report discussing a series of experiments involving the reaction of water with decaborane and HEF-3, a boron fuel containing ethyldecaborane. The chemical properties of the hydrolysis reaction are described. Two isomers were also prepared to assist with the syntheses, and their melting points, molecular weights, and solubilities in certain solvents are included.
Date: October 8, 1957
Creator: Lucas, D. & Lipschitz, A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Synthesis and Hydrolysis-Rate Studies of Decaborane Derivatives

Description: "A series of experiments involving the reaction of water with decaborane and HEF-3, a borane fuel consisting mainly of ethyldecaborane, was performed. The results show that the presence of one alkyl group on the decaborane nucleus inhibits the hydrolysis reaction significantly and that the hydrolysis rate can be increased by using an acidic hydrolysis mixture. Two diiododecaborane isomers were prepared for use as intermediates in proposed dimethyldecaborane syntheses, and their melting points, … more
Date: October 8, 1957
Creator: Lucas, D. & Lipschitz, A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A theoretical and experimental study of boric oxide deposition on a surface immersed in an exhaust gas stream from a jet-engine combustor, including a method of calculating deposition rates on surfaces

Description: Report presenting the deposition rate of boric oxide from a stream containing submicron particles, which was found experimentally to fit a molecular diffusion equation. Results regarding boundary-layer studies, deposition studies, deposition tests, and turbojet engine performance are provided.
Date: October 8, 1957
Creator: Setze, Paul C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analytical and experimental investigation of the effects of compressor interstage air bleed on performance characteristics of a 13-stage axial-flow compressor

Description: Air was bled over the fifth-and tenth-stage rotor-blade rows through ports designed to pass 11 and 9 percent of the inlet flow, respectively, at 80 percent speed. Along the rated operating line the maximum speed at which rotating stall was encountered was lowered by either of these bleeds, and the stall patterns below these speeds were altered so that no dangerous resonant rotor-blade bending vibrations were excited. The combination of the two bleeds completely eliminated rotating stall to at l… more
Date: February 8, 1957
Creator: Lucas, James G.; Geye, Richard P. & Calvert, Howard F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental study of the effects of scale on the absolute values of zero-lift drag of aircraft configurations at transonic speeds

Description: Report presenting an investigation at a range of Mach numbers from 0.7 to 1.4 to determine the effect of scale on the zero-lift drag of a fin-stabilized body of revolution and a fighter-type airplane configuration. Results obtained at low values of Reynolds number were compared with larger scale data obtained on geometrically similar models in free flight. Results regarding fin-stabilized body and airplane model are provided.
Date: February 8, 1957
Creator: Howell, Robert R. & Braslow, Albert L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Exploratory Investigation of the Effect of Wing Slots and Leading-Edge Slats on the Longitudinal Stability Characteristics of a 45 Degree Sweptback Wing-Fuselage Configuration

Description: Report presenting an exploratory investigation to determine the effects of wing slots on the longitudinal stability characteristics of a 45 degree sweptback wing-fuselage combination. Results regarding pitching-moment characteristics and lift and drag characteristics are provided.
Date: February 8, 1957
Creator: Critzos, Chris C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Free-Flight Experience of the Lateral Stability Characteristics at Low Lift of a 45 Degree Swept-Wing Rocket-Propelled Model Equipped With a Nonlinear Yaw-Rate Damper System at Mach Numbers From 0.76 to 1.73

Description: Report discussing a low-lift lateral stability investigation with a rocket-propelled model of a 45 degree swept-wing-airplane configuration equipped with an auxiliary yaw-rate damper system at a range of Mach numbers. Results indicated that the system was nonlinear due to a large dead spot in the system. The primary effect of the system was to increase the damping of lateral oscillations.
Date: February 8, 1957
Creator: D'Aiutolo, Charles T.; Willoughby, William W. & Coltrane, Lucille C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Physical and Chemical Properties of HEF-2 (NACA Fuel 56Z4)

Description: Memorandum presenting a study of the chemical and physical properties of the high-energy fuel HEF-2. The properties measured included elemental analysis, heat of combustion, density, freezing point, self-ignition temperature, flash point, viscosity, molecular weight, vapor pressure, refractive index, and the water and oxygen stability.
Date: February 8, 1957
Creator: Spakowski, A. E.; O'Donnell, P. & Buddie, M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Preliminary Investigation of Dynamic Lateral Stability Characteristics of a Configuration of the North American X-15 Research Airplane

Description: Memorandum presenting an investigation to determine the dynamic lateral stability characteristics of a configuration of the North American X-15 research airplane. Of specific concern were characteristic modes, period and damping, airplane response to yaw and roll controls, ratio of roll to sideslip in the Dutch-roll oscillation, and the roll-coupling problem. Results regarding stability-boundary plots, characteristic roots, roll-to-sideslip ratio, and time histories are provided.
Date: February 8, 1957
Creator: Moul, Martin T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary investigation of dynamic lateral stability characteristics of a configuration of the North American X-15 research airplane

Description: Report presenting an investigation to determine the dynamic lateral stability characteristics of a configuration of the North American X-15 research airplane. The characteristic modes, period and damping, airplane responses to yaw and roll controls, ratio of roll to sideslip in the Dutch-roll oscillation, and the roll-coupling problem are the primary focus.
Date: February 8, 1957
Creator: Moul, Martin T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of the Republic F-105 Inlet with Various Modifications at Mach Numbers 1.41, 1.81, and 2.01

Description: "A 1/13-scale Republic F-105 wing-root inlet configuration in which inlet components were varied was tested in the Langley 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1,41, 1.81, and 2,01 corresponding to Reynolds numbers per foot of 4,19 X 10(exp 6) , 3.74 X 10(exp 6) , and 3.46 x 10(exp 6) respectively. Angles of attack ranged from -4 deg to 15 deg and a few configurations were tested in a sideslip range from -8 deg to 4 deg. Inlet performance and engine-face flow distortions a… more
Date: January 8, 1957
Creator: Robins, A. Warner
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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