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Adaptation of a Cascade Impactor to Flight Measurement of Droplet Size in Clouds

Description: "A cascade impactor, an instrument for obtaining the size distribution of droplets borne in a low-velocity air stream, was adapted for flight cloud droplet-size studies. The air containing the droplets was slowed down from flight speed by a diffuser to the inlet-air velocity of the impactor" (p. 1).
Date: September 18, 1951
Creator: Levine, Joseph & Kleinknecht, Kenneth S.
Partner: UNT Libraries Government Documents Department
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Additional Studies of the Stability and Controllability of an Unswept-Wing Vertically Rising Airplane Model in Hovering Flight Including Studies of Various Tethered Landing Techniques

Description: Report discussing the results of an investigation to determine the stability and control characteristics of a flying model of an unswept-wing vertically rising airplane. Information about stabilization, maneuverability, rolling motions, and landings is provided.
Date: November 6, 1951
Creator: Bates, William R.; Lovell, Powell M., Jr. & Smith, Charles C., Jr.
Partner: UNT Libraries Government Documents Department
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Aerodynamic characteristics at transonic speeds of a 69 degree delta wing with a triangular plan-form control having a skewed hinge axis and an overhang balance: transonic-bump method

Description: From Introduction: "Presented in this paper are the results of an investigation of a semispan model of a delta wing with 60^o sweepback at the leading edge which was equipped with a large triangular control having an overhang balance mounted on a skewed hinge axis. The purpose of this investigation was to determine the aerodynamic characteristics of a delta wing with a control which was designed to provide aerodynamic balance at zero control deflection based on the span load distribution of ref… more
Date: February 6, 1951
Creator: Wiley, Harleth G.
Partner: UNT Libraries Government Documents Department
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Aerodynamic characteristics including pressure distribution of a fuselage and three combinations of the fuselage with swept-back wings at high subsonic speeds

Description: From Introduction: "The wings were tested in combination with fuselage similar to the one used in the 7- by 10-foot wind-tunnel investigations. The results are reported herein and are compared with results for three similar model wings on the transonic bump (references 1, 2, and 3)."
Date: February 6, 1951
Creator: Sutton, Fred B. & Martin, Andrew
Partner: UNT Libraries Government Documents Department
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Aerodynamic Characteristics of a Flying-Boat Hull Having a Length-Beam Ratio of 15, TED No. NACA 2206

Description: "An investigation was made in the Langley 300 MPH 7- by 10-foot tunnel to determine the aerodynamic characteristics of a flying-boat hull of a length-beam ratio of 15 in the presence of a wing. The investigation was an extension of previous tests made on hulls of length-beam ratios of 6, 9, and 12; these hulls were designed to have approximately the same hydrodynamic performance with respect to spray and resistance characteristics. Comparison with the previous investigation at lower length-beam… more
Date: January 23, 1951
Creator: Riebe, John M. & Naeseth, Rodger L.
Partner: UNT Libraries Government Documents Department
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Aerodynamic characteristics of a slender cone-cylinder body of revolution at a Mach number of 3.85

Description: "An experimental investigation of the aerodynamics of a slender cone-cylinder body of revolution was conducted at a Mach number of 3.85 for angles of attack of 0 degree to 10 degrees and a Reynolds number of 3.85x10(exp 6). Boundary-layer measurements at zero angle of attack are compared with the compressible-flow formulations for predicting laminar boundary-layer characteristics. Comparison of experimental pressure and force values with theoretical values showed relatively good agreement for s… more
Date: November 5, 1951
Creator: Jack, John R.
Partner: UNT Libraries Government Documents Department
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Aerodynamic Characteristics of Bodies at Supersonic Speeds: A Collection of Three Papers

Description: The three papers collected here are: 'The Effect of Nose Shape on the Drag of Bodies of Revolution at Zero Angle of Attack.', 'Base Pressure on Wings and Bodies with Turbulent Boundary Layers', and 'Flow over Inclined Bodies'. The subject of the first paper is the drag of the nose section of bodies of revolution at zero angle of attack. The main object of the second paper is to summarize the prinicpal results of the many wind tunnel and free flight measurements of base pressure on both bodies o… more
Date: November 9, 1951
Creator: Seiff, Alvin; Sandahl, Carl A.; Chapman, Dean R.; Perkins, E. W. & Gowen, F. E.
Partner: UNT Libraries Government Documents Department
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Aerodynamic Characteristics of Four Bodies of Revolution Showing Some Effects of Afterbody Shape and Fineness Ratio at Free-Stream Mach Numbers From 1.50 to 1.99

Description: The effects of fineness ratio (14.2 and 12.2) and boattailing on aerodynamic characteristics of four bodies of revolution at Mach numbers from 1.50 to 1.99 within a range of angles of attack from 0 degrees 10 degrees at an approximate Reynolds number of 35x10(superscript)6 based on body length were investigated. A comparison of experimental data with available theory is included. At zero angle of attack, fineness ratio has no appreciable effect on model characteristics while boattailing and boa… more
Date: May 22, 1951
Creator: Cohen, Robert J.
Partner: UNT Libraries Government Documents Department
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Aerodynamic Characteristics of Four Wings of Sweepback Angles 0 Degrees, 35 Degrees, 45 Degrees, and 60 Degrees, NACA 65A006 Airfoil Section, Aspect Ratio 4, and Taper Ratio 0.6 in Combination With a Fuselage at High Subsonic Mach Numbers and at a Mach Number of 1.2

Description: Report discussing an investigation of the effect of sweepback angle on wing-fuselage characteristics at a subsonic and a supersonic Mach number. Lift, drag, and pitching-moment coefficients, downwash-angle, and total-pressure measurements are all provided.
Date: June 6, 1951
Creator: Luoma, Arvo A.
Partner: UNT Libraries Government Documents Department
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Aerodynamic Characteristics of Tapered Wings Having Aspect Ratios of 4, 6, and 8, Quarter-Chord Lines Swept Back 45 Degrees, and NACA 63(Sub 1)a012 Airfoil Sections: Transonic-Bump Method

Description: Report presenting testing of a series of three wings over a range of Mach numbers by the use of the transonic-bump technique. The lift, drag, pitching-moment, and root-bending-moment data of wings of a variety of aspect ratios but with the same quarter-chord lines and airfoil sections were obtained.
Date: June 13, 1951
Creator: Polhamus, Edward C. & King, Thomas J., Jr.
Partner: UNT Libraries Government Documents Department
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Aerodynamic characteristics of the NACA RM-10 research missile in the Ames 1- by 3-foot supersonic wind tunnel no. 2: Pressure and force measurements at Mach numbers of 1.52 and 1.98

Description: Report presenting an experimental investigation of the aerodynamic characteristics of a fin-stabilized body of revolution, designated as RM-10, in a supersonic wind tunnel. Pressure distributions and force characteristics were determined at two different Mach numbers. Results regarding pressure distributions, body-alone force tests, and body-tail combination force tests are provided.
Date: September 19, 1951
Creator: Perkins, Edward W.; Gowen, Forrest E. & Jorgensen, Leland H.
Partner: UNT Libraries Government Documents Department
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Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : effectiveness at supersonic speeds of a 30-percent chord, 50-percent semispan elevon as a lateral control device

Description: Report presenting the effectiveness of a 50-percent-semispan, constant-percent-chord elevon, and of upper-space spoilers as lateral control surfaces for a wing-fuselage combination with a wing swept back 63 degrees over a range of Mach numbers. For the elevon, results indicated that only about half of the predicted rolling-moment effectiveness was realized. The spoilers were found to be inferior to the elevons for lateral control because of a rapid loss of effectivness above an angle of attack … more
Date: January 18, 1951
Creator: Olson, Robert N. & Mead, Merrill H.
Partner: UNT Libraries Government Documents Department
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Aerodynamics of slender bodies at Mach number of 3.12 and Reynolds numbers from 2 x 10(exp 6) to 15 x 10(exp 6) 1: body of revolution with near-parabolic forebody and cylindrical afterbody

Description: An experimental investigation of the aerodynamic characteristics of a slender, square-based body of revolution was conducted at a Mach number of 3.12 for angles of attack from 0 degree to 10 degrees and for Reynolds numbers from 2 x 10(exp 6) to 15 x 10(exp 6). Boundary-layer measurements at zero angle of attack are compared with several compressible flow formulating for predicting boundary-layer characteristics. Comparison of experimental pressure and force values with theoretical values showe… more
Date: November 13, 1951
Creator: Jack, John R. & Burgess, Warren C.
Partner: UNT Libraries Government Documents Department
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Altitude-ignition limit of a turbojet engine using a condenser-discharge ignition system

Description: The altitude-ignition limits of a condenser-discharge ignition system installed on a turbojet engine were determined at a flight Mach number of 0.6 using 1.1-pound Reid vapor pressure fuel. Ignition was possible up to an altitude of 55,000 feet with 4.8 joules per spark and 6 sparks per second.
Date: October 23, 1951
Creator: Armstrong, John C.
Partner: UNT Libraries Government Documents Department
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Altitude investigation of 16 flame-holder and fuel-system configurations in tail-pipe burner

Description: From Introduction: "The data obtained for each configuration are presented in a manner to show the effects of fuel distribution and flame-holder design on net thrust, specific fuel consumption, exhaust-gas temperature, combustion efficiency, operable range of tail-pipe-burner fuel-air ratios, and maximum altitude limit."
Date: December 12, 1951
Creator: Grey, Ralph E.; Krull, H. G. & Sargent, A. F.
Partner: UNT Libraries Government Documents Department
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Altitude-performance and Reynolds number investigation of centrifugal-flow-compressor turbojet engine

Description: From Introduction: "Altitude-chamber and wind-tunnel investigations of the performance of turbojet engines such as those reported in references 1 to 4 have shown that the conventional correction factors fail to generalize the engine performance variables at high altitudes. An investigation was therefore made at the NACA Lewis laboratory to determine the altitude performance of the J33-A-23 turbojet engine and to demonstrate the magnitude of departure of actual altitude performance from that pre… more
Date: May 15, 1951
Creator: Wilsted, H. D. & Grey, R. E.
Partner: UNT Libraries Government Documents Department
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Altitude Performance of J35-A-17 Turbojet Engine in an Altitude Chamber

Description: "An investigation of the altitude performance characteristics of an Allison J35-A-17 turbojet engines have been conducted in an altitude chamber at the NACA Lewis laboratory. Engine performance was obtained over a range of altitudes from 20,000 to 60,000 feet at a flight Mach number of 0.62 and a range of flight Mach numbers from 0.42 to 1.22 at an altitude of 30,000 feet. The performance of the engine over the range investigated could be generalized up to an altitude of 30,000 feet" (p. 1).
Date: January 3, 1951
Creator: Vincent, K. R. & Gale, B. M.
Partner: UNT Libraries Government Documents Department
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Altitude-test-chamber investigation of performance of a 28-inch ram-jet engine 3: combustion and operational performance of three flame holders with a center pilot burner

Description: Report presenting a direct-connect altitude test chamber investigation of the combustion performance of a 28-inch-diameter ramjet engine with a can-type center pilot burner. Combustion-chamber configurations with three different flame holders were investigated at a simulated flight Mach number of 2.0 and several different altitudes.
Date: February 6, 1951
Creator: Shillito, Thomas B.; Younger, George G. & Henzel, James G., Jr.
Partner: UNT Libraries Government Documents Department
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Altitude-Test-Chamber Investigation of Performance of a 28-Inch Ram-Jet Engine 4: Effect of Inlet-Air Temperature, Combustion-Chamber-Inlet Mach Number, and Fuel Volatility on Combustion Performance

Description: Report presenting testing of the effects of the following variables on combustion performance are determined: inlet-air temperature, combustion-chamber-inlet Mach number and pressure, and fuel density and volatility.
Date: July 27, 1951
Creator: Kahn, Robert W.; Nakanishi, Shigeo & Harp, James L., Jr.
Partner: UNT Libraries Government Documents Department
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Altitude-Wind-Tunnel Investigation of Performance Characteristics of a J47D Prototype (RX1-1) Turbojet Engine With Fixed-Area Exhaust Nozzle

Description: Report presenting an investigation to determine the overall performance of a prototype model of the J47D (RX1-1) turbojet engine with a fixed-area exhaust nozzle. Data was obtained for a range of engine speeds, altitudes, and Mach numbers. Results regarding the effect of those variables and generalization in terms of pumping characteristics are provided.
Date: September 4, 1951
Creator: Saari, M. J. & Wintler, J. T.
Partner: UNT Libraries Government Documents Department
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Altitude-Wind-Tunnel Investigation of Performance Characteristics of a J47D Prototype (RX1-1) Turbojet Engine With Variable-Area Exhaust Nozzle

Description: Performance of a J47D (RX1-1) turbojet engine equipped with afterburner, variable-area exhaust nozzle, and integrated electronic control was determined over a range of flight conditions. These data were obtained with the electronic control both operative and inoperative. For operation with scheduled exhaust nozzle area, the minimum specific fuel consumption of 1.15 pounds of fuel per hour per pound of net thrust occurred at about 7200 rpm at altitudes from 5000 to 25,000 feet at a flight Mach n… more
Date: September 5, 1951
Creator: Conrad, E. William & McAulay, John E.
Partner: UNT Libraries Government Documents Department
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Altitude Wind Tunnel Investigation of the Performance of Compressor, Combustor, and Turbine Components of Prototype J47D (RX1-1) Turbojet Engine

Description: "As a portion of an over-all performance investigation of the prototype J47D (RX-1) turbojet engine, performance of the compressor, combustor, and turbine components has been determined in the Lewis altitude wind tunnel over a range of altitude from 5000 to 55,000 feet and at flight Mach numbers from 0.19 to 0.92. Investigations were conducted with the engine operating on an electronic control schedule and slow with a two-lever control system by which fuel flow and exhaust-nozzle area could be … more
Date: December 21, 1951
Creator: Farley, John M.
Partner: UNT Libraries Government Documents Department
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