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Investigation at Mach Number 1.62 of the Pressure Distribution Over a Rectangular Wing With Symmetrical Circular-Arc Section and 30-Percent-Chord Trailing-Edge Flap

Description: Report presenting an investigation of the pressure distribution over a rectangular wing with a 9-percent-thick symmetrical circular-arc section and a 30-percent-chord trailing-edge flap. Results are given for pressure distributions, Schileren and liquid-film studies, and wing section characteristics are provided.
Date: January 25, 1950
Creator: Czarnecki, K. R. & Mueller, James N.
Partner: UNT Libraries Government Documents Department
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Wind-tunnel investigation of the vortex wake and downwash field behind triangular wings and wing-body combinations at supersonic speeds

Description: Report presenting an investigation of the flow field behind triangular wings alone and in combination with a pointed cylindrical body at Mach numbers of 1.5 and 2.0 through an angle-of-attack range of 0 to 24 degrees. Results regarding the geometric characteristics of the vortex system and downwash characteristics are provided.
Date: June 25, 1953
Creator: Spahr, J. Richard & Dickey, Robert R.
Partner: UNT Libraries Government Documents Department
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Weight Bar Charts

Description: The weight breakdowns in bar chart form in the present report have been prepared to give an indication of 'how we spend our weight.' They are expected to focus attention on the design functions that warrant weight reduction activity on future models.
Date: June 25, 1953
Creator: Saelman, B. J. & Vick, H. W.
Partner: UNT Libraries Government Documents Department
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Comparison of Zero-Lift Drag Determined by Flight Tests at Transonic Speeds of Pylon, Underslung, and Symmetrically Mounted Nacelles at 40 Percent Semispan of a 45 Degrees Sweptback Wing and Body Combination

Description: Report presenting the effect on drag of varying the vertical position of a nacelle at 40 percent semispan of a 45 degree sweptback wing and body combination as determined by transonic flight tests at zero lift. Three nacelle positions were investigated: a pylon mounted nacelle, an underslung nacelle, and a symmetrically mounted nacelle. Results regarding total drag coefficient and maximum wing-tip helix angle are provided.
Date: June 25, 1951
Creator: Hoffman, Sherwood
Partner: UNT Libraries Government Documents Department
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Characteristics of Four Nose Inlets as Measured at Mach Numbers Between 1.4 and 2.0

Description: Memorandum presenting the pressure recovery, mass flow, and axial force of four bodies with nose inlets measured at Mach numbers between 1.4 and 2.0 and angles of attack of 0, 3, 6, and 9 degrees. The drag coefficients of axially symmetric diffusers operating at the maximum mass-flow rates were calculated from schileren photographs of the head shock waves and frictional drag considerations. Results regarding open-nose diffusers and conical-shock diffusers are provided.
Date: June 25, 1951
Creator: Brajnikoff, George B. & Rogers, Arthur W.
Partner: UNT Libraries Government Documents Department
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Flight calibration of angle-of-attack and sideslip detectors on the fuselage of a 35 degree swept-wing fighter airplane

Description: Report presenting measurements of the position errors of angle-of-attack and sideslip detectors located on the fuselage of a 35 degree swept-wing fighter airplane over a range of Mach numbers and at lift coefficients up to the buffet boundary. Results regarding the angle of attack and sideslip are provided.
Date: February 25, 1952
Creator: McFadden, Norman M.; Bray, Richard S. & Rathert, George A., Jr.
Partner: UNT Libraries Government Documents Department
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A Correlation by Means of the Transonic Similarity Rules of the Experimentally Determined Characteristics of 22 Rectangular Wings of Symmetrical Profile

Description: From Summary: "The transonic similarity rules have been applied to the correlation of experimental data for a series of 22 rectangular wings having symmetrical NACA 63A-series sections, aspect ratios from 1/2 to 6, and thicknesses from 2 to 10 percent. The data were obtained by use of the transonic bump technique over a Mach number range from 0.40 to 1.10, corresponding to a Reynolds number range from 1.25 to 2.05 million. The results show that it is possible to correlate experimental data throughout the subsonic, transonic, and moderate supersonic regimes by using the transonic similarity parameters in forms which are consistent with the Prandtl-Glauert rule of linearized theory."
Date: February 25, 1952
Creator: McDevitt, John B.
Partner: UNT Libraries Government Documents Department
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Flight Measurement of Aerodynamic Loads and Moments on an External Store Mounted Under the Wing of a Swept-Wing Fighter-Type Airplane

Description: Report discussing an investigation of external-store characteristics using a 245-gallon external fuel tank mounted under a wing of a North American F-86A airplane. The store normal force was found to increase abruptly on penetration of the buffet boundary. Information about the normal- and side-load distribution and integrated force and moment coefficients is provided.
Date: November 25, 1953
Creator: O'Bryan, Thomas C.
Partner: UNT Libraries Government Documents Department
open access

Investigation of Spoilers at a Mach Number of 1.93 to Determine the Effects of Height and Chordwise Location on the Section Aerodynamic Characteristics of a Two-Dimensional Wing

Description: Report presenting an investigation of spoilers at a Mach number of 1.93 to determine the effects of height and chordwise location on the section pressure distributions and section aerodynamic characteristics of a two-dimensional, 6-percent-thick, symmetrical wing. Spoilers of 3-, 5-, and 7-percent-chord height were tested at three chordwise locations. Results regarding pressure distributions, aerodynamic characteristics, and shock boundary-layer interactions are provided.
Date: March 25, 1953
Creator: Mueller, James N.
Partner: UNT Libraries Government Documents Department
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Evaluation of End- and Radial-Burning Solid Fuels in Ram Jets Mounted in a Free Jet at Mach Numbers of 2.0, 2.2, and 2.3

Description: Report presenting testing of two types of solid fuels in a 6.5-inch-diameter ram-jet engine mounted in a free supersonic jet at several Mach numbers. Results regarding radial-burning fuel, end-burning fuel, and a comparison of the two are provided. Unlike in previous testing, no fuel breakup was noted due to recently developed molding techniques.
Date: November 25, 1952
Creator: Bartlett, Walter A., Jr.
Partner: UNT Libraries Government Documents Department
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Free-Jet Altitude Investigation of a 20-Inch Ram-Jet Combustor With a Rich Inner Zone of Combustion for Improved Low-Temperature-Ratio Operation

Description: From Summary: "An investigation of the altitude performance of a 20-inch-diameter high-temperature-ratio ram-jet combustor which had been redesigned to provide good combustor efficiency over a wide range of temperature ratios was conducted at zero angle of attack in a free-jet facility at a Mach number of 3.0. Configurations investigated incorporated a cylindrical control sleeve which confined the injected fuel at low over-all fuel-air ratios to about 40 percent of the engine air flow. This provided an optimum fuel-air mixture over a portion of the flame holder when the over-all fuel-air ratio was about 0.02."
Date: May 25, 1953
Creator: Trout, Arthur M. & Wentworth, Carl B.
Partner: UNT Libraries Government Documents Department
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Effect of rotor- and stator-blade modifications on surge performance of an 11-stage axial-flow compressor 2: redesigned compressor for XJ-40-WE-6 engine

Description: Report presenting an investigation to increase the compressor surge-limit pressure ratio of the XJ40-WE-6 turbojet engine at high equivalent speeds. An evaluation of the basic redesign of the compressor and 11 additional modifications are examined.
Date: May 25, 1953
Creator: Conrad, E. William; Finger, Harold B. & Essig, Robert H.
Partner: UNT Libraries Government Documents Department
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Effects of slot location and geometry on the flow in a square tunnel at transonic Mach numbers

Description: Report presenting data from an investigation of the effects of slot location and slot geometry on the flow in a square tunnel for a Mach number range up to 1.4. Calculated static-pressure and angle-of-flow distributions along the slotted boundary are presented for several slot configurations in a tunnel with two opposite walls slotted.
Date: November 25, 1953
Creator: Nelson, William J. & Cubbage, James M., Jr.
Partner: UNT Libraries Government Documents Department
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Bodies of Revolution for Minimum Drag at High Supersonic Airspeeds

Description: From Summary: "Approximate shapes of nonlifting bodies having minimum pressure foredrag at high supersonic airspeeds are calculated.With the aid of Newton's law of resistance, the investigation is carried out for various combinations of the conditions of given body length, base diameter, surface area, and volume. In general it is found that when body length is fixed, the body has a blunt nose; whereas, when the length is not fixed, the body has a sharp nose."
Date: February 25, 1952
Creator: Eggers, A. J., Jr.; Dennis, David H. & Resnikoff, Meyer M.
Partner: UNT Libraries Government Documents Department
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An Experimental Investigation of Two-Dimensional, Supersonic Cascade-Type Inlets at a Mach Number of 3.11

Description: Memorandum presenting an investigation of two-dimensional, supersonic cascade-type inlets at a free-stream Mach number of 3.11. Two cascade-type inlets utilizing different methods of internal-flow compression were designed and tested. Results regarding the cascade inlet and stepped-cascade inlet are provided.
Date: August 25, 1954
Creator: Óffenhartz, Edward
Partner: UNT Libraries Government Documents Department
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Effects of base bleed on the base pressure of blunt-trailing-edge airfoils at supersonic speeds

Description: Report presenting the effect on base pressure of bleeding air to the semidead-air region at the trailing edge of two-dimensional blunt-trailing-edge airfoils at two Mach numbers. Variation of base pressure with base-bleed rate was determined for two airfoils profiles with both laminar and turbulent boundary layers approaching the trailing edge. Results regarding the effects of jet geometry, effects of jet area, effect of base bleed on the flow in the wake, effect of angle of attack, effect of Reynolds number, correlation of the results with mass-flow rate of the bleed air, and effect of base bleed on the drag of blunt-trailing-edge airfoils are provided.
Date: March 25, 1954
Creator: Wimbrow, William R.
Partner: UNT Libraries Government Documents Department
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Transonic Wind-Tunnel Investigation of the Effects of Body Indentation on the Aerodynamics of a Semielliptical Sweptback Wing-Root Inlet Configuration

Description: Report presenting an investigation in the transonic blowdown tunnel between Mach numbers of 0.65 and 1.4 to determine whether the principles of the transonic area rule could be used to improve the transonic drag-rise characteristics of a semielliptical shaped sweptback air inlet installed in the root of a sweptback wing-body combination. Results regarding the effect of the inlet and the interaction of Mach number and drag coefficient are provided.
Date: March 25, 1954
Creator: Keith, Arvid L., Jr.
Partner: UNT Libraries Government Documents Department
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Limits of Flammability of Pure Hydrocarbon-Air Mixtures at Reduced Pressures and Room Temperature

Description: Memorandum presenting a systematic study to determine the effect of molecular structure on the flammability limits of pure hydrocarbon-air mixtures at reduced pressures and room temperature. This report presents results obtained for 17 pure normal paraffins, branched paraffins, and mono-olefins. Results regarding experimental variables and experimental observations are provided.
Date: May 25, 1951
Creator: DiPiazza, James T.
Partner: UNT Libraries Government Documents Department
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Preliminary Data on the Effect of Body-Nose Bluntness on the Drag and Pressure Recovery of a Side-Inlet-Body Combination at Mach Numbers of 1.4 and 1.7

Description: Memorandum presenting the pressure recovery, mass flow, and drag of a twin-scoop, side-inlet-body combination measured at Mach number 1.4 and 1.7. The inlet was located on a body having an ogival nose followed by a cylindrical section and a total fineness ratio of 5.
Date: April 25, 1951
Creator: Stroud, John F. & Anderson, Warren E.
Partner: UNT Libraries Government Documents Department
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Effects of inlet icing on performance of axial-flow turbojet engine in natural icing conditions

Description: A flight investigation in natural icing conditions was conducted to determine the effect of inlet ice formations on the performance of axial-flow turbojet engines. The results are presented for icing conditions ranging from a liquid-water content of 0.1 to 0.9 gram per cubic meter and water-droplet size from 10 to 27 microns at ambient-air temperature from 13 to 26 degrees F. The data show time histories of jet thrust, air flow, tail-pipe temperature, compressor efficiency, and icing parameters for each icing encounter. The effect of inlet-guide-vane icing was isolated and shown to account for approximately one-half the total reduction in performance caused by inlet icing.
Date: May 25, 1950
Creator: Acker, Loren W. & Kleinknecht, Kenneth S.
Partner: UNT Libraries Government Documents Department
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Determination by the Free-Fall Method of the Drag and Longitudinal Stability and Control Characteristics of a Canard Model at Transonic Speeds

Description: Report discussing the stability and control characteristics and drag of a canard or tail-first configuration explored using the free-fall method. Information about the basic flight characteristics, experimental coefficients, zero-lift drag configurations, and longitudinal stability and trim characteristics is provided.
Date: August 25, 1950
Creator: Kraft, Christopher C., Jr. & Mathews, Charles W.
Partner: UNT Libraries Government Documents Department
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Flight Investigation of the Drag of Round-Nosed Bodies of Revolution at Mach Numbers From 0.6 to 1.5 Using Rocket-Propelled Test Vehicles

Description: "Values of total drag coefficient were measured for four round-nosed bodies of revolution in free flight at Mach numbers from 0.6 to 1.5 and Reynolds numbers from 10 x 10(6) to 50 x 10(6). The bodies were designed by rounding off the sharp, fineness-ratio-3.56 nose of a previously tested configuration. The nose radii tested were 27.4, 38.7, 80.6, and 100 percent of the maximum body radius and corresponded to values of 0.075, 0.150, 0.650, and 1.000, respectively, for the ratio of nose-sphere frontal area to body frontal area" (p. 1).
Date: July 25, 1951
Creator: Hart, Roger G.
Partner: UNT Libraries Government Documents Department
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Pressure-distribution measurements over a 45 degree sweptback wing at transonic speeds by the NACA wing-flow method

Description: Report presenting measurements of pressure made over the chord of a swept-wing model at four stations along the span by the NACA wing-flow method. The model was an untapered 45 degree sweptback wing of aspect ratio 3.5 with 2-inch-chord NACA 65-210 airfoil sections normal to the leading edge. Results regarding the chordwise pressure distributions and spanwise distributions of section lift, drag, and pitching moment.
Date: June 25, 1951
Creator: Danforth, Edward C. B. & O'Bryan, Thomas C.
Partner: UNT Libraries Government Documents Department
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Lift and drag coefficients for the Bell X-1 airplane (8-percent-thick wing) in power-off transonic flight

Description: Report presenting drag coefficients determined by the accelerometer method for the Bell X-1 airplane with 8-percent-thick wing and 6-percent-thick tail in power-off flight over a range of Mach numbers and lift coefficients. Results regarding the variation of computed lift and drag coefficients, variation of lift coefficient with Mach number, and effect of Mach number on lift-drag ratio are provided.
Date: June 25, 1951
Creator: Carman, L. Robert & Carden, John R.
Partner: UNT Libraries Government Documents Department
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