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The Forces and Pressure Distribution at Subsonic Speeds on a Plane Wing Having 45 Degrees of Sweepback, an Aspect Ratio of 3, and a Taper Ratio of 0.5

Description: Memorandum presenting an investigation to determine the effects of scale and compressibility on the forces, moments, and pressure distribution on a wing with an aspect ratio of 3 and a taper ratio of 0.5. Lift, drag, and pitching-moment data and the chordwise distribution of static pressure at seven spanwise stations are presented for several sets of Reynolds and Mach numbers. The results indicated that for all Mach and Reynolds numbers in the test range, no apparently flow separation existed n… more
Date: October 16, 1951
Creator: Kolbe, Carl D. & Boltz, Frederick W.
Item Type: Refine your search to only Report
open access

Free Flight Investigation at Transonic Speeds of the Power-on Characteristics Including Some Effects of Sonic Propulsive Jets of a Four Engine Delta Wing Configuration

Description: Report discussing a model of a delta-wing configuration with four engines mounted two to a nacelle below the wing that was tested a variety of Mach numbers and Reynolds numbers. The wing static-pressure coefficients, wing pressure coefficients, and lift coefficient of different configurations are described.
Date: August 16, 1957
Creator: Falanga, Ralph A. & Judd, Joseph H.
Item Type: Refine your search to only Report
open access

Free-flight investigation at transonic speeds of the power-on characteristics including some effects of sonic propulsive jets of a four-engine delta-wing configuration

Description: Report presenting an investigation of a free-flight model of a delta-wing configuration with four engines mounted two to a nacelle below the wing with rocket turbojet simulators operating at a range of Mach numbers. Results regarding wing pressure coefficients, fuselage pressure coefficient, airplane aerodynamic characteristics, and airplane trim are provided.
Date: August 16, 1957
Creator: Judd, Joseph H. & Falanga, Ralph A.
Item Type: Refine your search to only Report
open access

Free-Jet Investigation of a 20-Inch Ram-Jet Combustor Utilizing High-Heat-Release Pilot Burner

Description: Report presenting an investigation of the performance of a 20-inch-diameter ramjet engine with a high-heat-release pilot burner conducted at zero angle of attack in a free-jet test facility at a Mach number of 3.0. Two flame-holder configurations were used in conjunction with the high-heat-release pilot burner over a range of altitudes. Results regarding the performance of the high-heat-release pilot burner and performance of combustion-chamber configurations are provided.
Date: October 16, 1953
Creator: Henzel, James G., Jr. & Wentworth, Carl B.
Item Type: Refine your search to only Report
open access

Free-Spinning-Tunnel Tests of a 1/29-Scale Model of the Republic XP-91 Airplane with a Vee Tail Installed

Description: "A spin investigation has been conducted in the Langley 20 -foot free-spinning tunnel on a 1/29 - scale model of the Republic XP-91 airplane with vee tail installed. The effects of control settings and movements upon the effect spin and recovery characteristics of the model were determined for the clean condition (wing tanks removed, landing gear and flaps retracted). The tests were made at a loading simulating that following cruise at altitude and at a time when nearly all fuel was expended" (… more
Date: January 16, 1948
Creator: Snyder, Thomas L.
Item Type: Refine your search to only Report
open access

General Treatment of Compressible Flow in Ejectors and Example of Its Application to Problem of Effect of Ejector Addition on Thrust of Jet-Propulsion Units

Description: Memorandum presenting a general treatment of compressible flow in ejectors with friction in the mixing tube included. A secondary object is to show the application of the flow theory to the calculation of the effect of ejector addition on thrust of jet-propelled airplanes and missiles. Results regarding the outline of methods of applying the general theory to some other problems and future explorations of ejector problems are provided.
Date: June 16, 1947
Creator: Ellerbrock, Herman H., Jr.
Item Type: Refine your search to only Report
open access

The Heat of Combustion of Tetraethyldiborane

Description: "The net heat of combustion of a sample of tetraethyldiborane was found to be 20,400 plus or minus 130 Btu per pound for the reaction of liquid fuel to gaseous carbon dioxide, gaseous water ,and solid boric oxide. The measurements were made in a Parr oxygen bomb calorimeter and the combustion is believed to have been 99 percent complete. A more reasonable value for the net heat of combustion would therefore be 20,600 plus or minus 130 Btu per pound" (p. 1).
Date: January 16, 1957
Creator: Tannenbaum, Stanley
Item Type: Refine your search to only Report
open access

Hydrodynamic Characteristics of an Aerodynamically Refined Planing-Tail Hull

Description: The hydrodynamic characteristics of an aerodynamically refined planing-tail hull were determined from dynamic model tests in Langley tank no. 2. Stable take-off could be made for a wide range of locations of the center of gravity. The lower porpoising limit peak was high, but no upper limit was encountered. Resistance was high, being about the same as that of float seaplanes. A reasonable range of trims for stable landings was available only in the aft range of center-of-gravity locations.
Date: July 16, 1948
Creator: McKann, Robert & Suydam, Henry B.
Item Type: Refine your search to only Report
open access

Influence of a canard-type control surface on flow field in vicinity of symmetrical fuselage at Mach numbers 1.8 and 2.0

Description: Report presenting an experimental investigation of the flow field downstream of a canard-type control surface and in the vicinity of a symmetrical body in the 8- by 6-foot supersonic tunnel at Mach numbers of 1.8 and 2.0. The results indicated severe total pressure losses and large flow deflections in the control surface wake.
Date: July 16, 1952
Creator: Wise, George A. & Dryer, Murray
Item Type: Refine your search to only Report
open access

Investigation at High Subsonic Speeds of the Effects of Various Horizontal Fuselage Forebody Fins on the Directional and Longitudinal Stability of a Complete Model Having a 45 Degree Sweptback Wing

Description: Memorandum presenting an investigation conducted in the high-speed 7- by 10-foot tunnel of the effects of various horizontal fuselage forebody fins on the directional and longitudinal stability characteristics at high subsonic speeds of a complete model with a 45 degree sweptback wing mounted in a high position on the fuselage. The model wing had an aspect ratio of 4, a taper ratio of 0.30, and NACA 65A006 airfoil sections parallel to the free stream.
Date: January 16, 1957
Creator: Sleeman, William C., Jr.
Item Type: Refine your search to only Report
open access

Investigation of a 10-Stage Subsonic Axial-Flow Research Compressor 2: Preliminary Analysis of Overall Performance

Description: Report presenting an investigation of the overall performance of a 20-inch-tip-diameter 10-stage compressor as the initial step to examine the problems encountered in an axial-flow compressor with a high pressure ratio per stage. The investigation was carried out over a range of weight flows and percentages of the design speed. Results regarding the part-speed efficiency, surge characteristics, overspeed characteristics, compressor discharge Mach number, and stage characteristics are provided.
Date: June 16, 1952
Creator: Budinger, Ray E. & Thomson, Arthur R.
Item Type: Refine your search to only Report
open access

Investigation of a Chromium Plus Aluminum Oxide Metal-Ceramic Body for Possible Gas Turbine Blade Application

Description: "A metal-ceramic composition containing approximately 80 percent chromium plus 20 percent aluminum oxide (Al(sub 2)O(sub 3)) by weight has been investigated for possible gas-turbine blade use. The results of modulus-of-rupture, thermal-shock, and blade-performance studies indicate that this material may have adequate thermal-shock resistance; however, the strength for the application appears marginal" (p. 1).
Date: November 16, 1953
Creator: Hoffman, Charles A.
Item Type: Refine your search to only Report
open access

Investigation of Control Signals for Variable Ramps of Twin-Duct Side Inlets

Description: Report presenting an investigation to determine the effectiveness of experimental control signals applied to a theoretical inlet throat Mach number control system and normal-shock-position control system for varying the inlet geometry of a twin-duct prototype aircraft. Results regarding inlet instability, control requirements, individual throat Mach number control signals, average throat Mach number control signals, theoretical thraot Mach number control analysis, effect of angle of attack, and… more
Date: January 16, 1958
Creator: Beheim, Milton A. & Yeager, Richard A.
Item Type: Refine your search to only Report
open access

Investigation of Control Signals for Variable Ramps of Twin-Duct Side Inlets

Description: Report presenting an investigation in the supersonic wind tunnel to determine the effectiveness of experimental control signals applied to a theoretical inlet throat Mach number control system and normal-shock-position control system for varying the inlet geometry of a twin-duct, side-inlet, fuselage forebody model of a prototype aircraft. These types of control systems have been found to be particularly helpful in supersonic flight. Results regarding inlet stability, control requirements, indi… more
Date: January 16, 1958
Creator: Beheim, Milton A. & Yeager, Richard A.
Item Type: Refine your search to only Report
open access

Investigation of distribution of losses in a conservatively designed turbine

Description: "A primary objective of turbine research is to obtain information that will aid in the design of gas turbines for any given application with minimum losses. As part of a program to obtain such information, flow surveys downstream of both the stator and the rotor of an experimental turbine were made in order to obtain detailed information about the flow conditions and the losses within the machine. The single-stage, low-radius-ratio turbine studied is relatively conservative in design, having lo… more
Date: March 16, 1953
Creator: Whitney, Rose L.; Heller, Jack A. & Hauser, Cavour H.
Item Type: Refine your search to only Report
open access

An Investigation of the Aerodynamic Characteristics in Pitch of an XB-52 Airplane Model in a High-Speed Wind Tunnel

Description: "A wind-tunnel investigation of a 0.049-scale model of the Boeing XB-52 airplane was made at Mach numbers from 0.30 to 0.925 and at corresponding Reynolds numbers from about 2.3 x 10(exp 6) to 4.3 x 10(exp 6). The results of the investigation indicate satisfactory static longitudinal stability throughout the test Mach-number range and some loss in tail effectiveness beginning at about 0.80 Mach number. A comparison of the results of these tests with those of the same model in the Boeing Airplan… more
Date: March 16, 1951
Creator: Cleary, Joseph W. & Coe, Charles F.
Item Type: Refine your search to only Report
open access

Investigation of the Attenuation of Plane Shock Waves Moving Over Very Rough Surfaces

Description: "Experimental measurements of the attenuation of plane shock waves moving over rough walls have been made in a shock tube. Measurements of the boundary-layer characteristics, including thickness and velocity distribution behind the shock, have also been made with the aid of new cal techniques which provide direct information on the local boundary-layer conditions at the rough walls. Measurements of shock speed and shock pressure ratio are presented for both smooth-wall and rough-wall flow over … more
Date: June 16, 1953
Creator: Huber, Paul W.; McFarland, Donald R. & Levine, Philip
Item Type: Refine your search to only Report
open access

Investigation of the Distribution of Lift, Drag, and Pitching Moment Between the Wing and Fuselage of a 1/30-Scale Semispan Model of the Bell X-5 Airplane at a Mach Number of 1.24 by the NACA Wing-Flow Method

Description: Report presenting an investigation at a Mach number of 1.24 to determine the distribution of lift, drag, and pitching moment between the wing and fuselage of a scale semispan model of the Bell X-5 airplane. Lift, drag, pitching moments, and wing bending moments were obtained for various angles of attack for 40 through 60 degrees sweptback duralumin wings in the presence of, but detached from, the fuselage.
Date: January 16, 1952
Creator: Silsby, Norman S. & Morris, Garland J.
Item Type: Refine your search to only Report
open access

An investigation of wing-body juncture interference effects at transonic speeds for several swept-wing and body combinations

Description: Report presenting the results of an investigation of wing-body juncture interference effects at high subsonic and transonic speeds. Three different model series were used: one with a swept wing of aspect ratio 6 and two with swept wings of aspect ratio 3. Results regarding drag, lift, pressure distributions, and tests with the body alone are provided.
Date: May 16, 1957
Creator: McDevitt, John B. & Taylor, Robert A.
Item Type: Refine your search to only Report
open access

Jet effects on flow over afterbodies in supersonic stream

Description: From Summary: "Current NACA research on the subject of jet effects on the flow over afterbodies in a supersonic stream is briefly summarized. Several jet nozzle types installed in various afterbody configurations are considered for a wide range of operating conditions."
Date: November 16, 1953
Creator: Cortright, Edgar M., Jr. & Kochendorfer, Fred D.
Item Type: Refine your search to only Report
open access

Lift, drag, and hinge moments at supersonic speeds of an all-movable triangular wing and body combination

Description: Report presenting hinge-moment data for a wing-body combination at Mach numbers of 1.46 and 1.99 and some lift and drag results for the lower Mach number. The model consisted of an aspect ratio 4, triangular, all-movable wing with an 8-percent-thick double-wedge section mounted on a pointed cylindrical body of fineness ratio 9-1/3. The results indicated that the wing has a relative effectiveness ranging from 63 to 98 percent.
Date: September 16, 1953
Creator: Drake, William C.
Item Type: Refine your search to only Report
open access

Lift, drag and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds: comparison of three wings of aspect ratio 2 of rectangular, swept-back and triangular plan form, including effects of thickness distribution

Description: Report presenting the aerodynamic characteristics of three wing-body combinations with wings of aspect ratio 2 and rectangular, swept-back, and triangular plan form and a comparison at subsonic and supersonic speeds. All three wings had 3-percent-thick airfoil sections and were investigated with biconvex and rounded-nose airfoil sections. Results regarding the effects of wing plan form, effects of airfoil-section thickness distribution, and effects of Reynolds number are provided.
Date: February 16, 1953
Creator: Hightower, Ronald C.
Item Type: Refine your search to only Report
open access

Low-Lift Buffet Characteristics Obtained From Flight Tests of Unswept Thin Intersecting Surfaces and of Thick 35 Degree Sweptback Surfaces

Description: Report presenting testing of two rocket-propelled research models to determine the effect of the intersection of thin aerodynamic surfaces and the effect of moderate sweepback of thick aerodynamic surfaces on low-lift buffeting. Results regarding trim changes and drag are also provided. It was discovered that low-lift buffeting may be induced at high subsonic speeds by interference due to the intersection of thin aerodynamic surfaces.
Date: January 16, 1953
Creator: Mason, Homer P.
Item Type: Refine your search to only Report
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