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open access

Aerodynamic characteristics and pressure distributions of a 6-percent-thick 49 degree sweptback wing with blowing over half-span and full-span flaps

Description: From Introduction: "The investigation reported herein was initiated to define further the effects on the aerodynamic characteristics and load distribution of a thin, sweptback wing of a low-pressure blowing system and also to provide information on which to base a more thorough study of a complete airplane configuration."
Date: September 20, 1955
Creator: Whittle, Edward F., Jr. & McLemore, H. Clyde
open access

Comparison Between Analytical and Wind-Tunnel Results on Flutter of Several Low-Aspect-Ratio, High-Density, Unswept Wings at High Subsonic Speeds and Zero Angle of Attack

Description: Memorandum presenting experimental flutter Mach numbers for several solid, thin, rectangular cantilever wings with uniform section properties, low aspect ratio, and high relative density estimated from the results of previous tests at zero angle of attack. The experimental values are considered estimates, rather than determinations, in the high subsonic speed range because in that range the amplitude criterion was necessarily arbitrary. Results regarding conservatism of standard analysis relati… more
Date: September 20, 1955
Creator: Warner, Robert W.
open access

Component Performance Investigation of J71 Type II Turbines 3 - Overall Performance of J71 Type IIA Turbine

Description: "The over-all component performance characteristics of the J71 Type IIA three-stage turbine were experimentally determined over a range of speed and over-all turbine total-pressure ratio at inlet-air conditions af 35 inches of mercury absolute and 700 deg. R. The results are compared with those obtained for the J71 Type IIF turbine, which was previously investigated, the two turbines being designed for the same engine application. Geometrically the two turbines were much alike, having the same … more
Date: January 20, 1955
Creator: Schum, Harold J.; Davison, Elmer H. & Petrash, Donald A.
open access

Effect of Several Modifications to Center Body and Cowling on Supercritical Performance of a Supersonic Inlet at Mach Number of 2.02

Description: Report discussing an investigation of several modifications of the center body and cowling of a supersonic inlet at Mach number 2.02 and angles of attack up to 12.25 degrees. Information about the effect on stable range of boundary-layer control on the center body, the stable range of distortion of conical shock, and the stable range of cowling-lip thickness is provided.
Date: May 20, 1955
Creator: Trimpi, Robert L. & Cohen, Nathaniel B.
open access

Effects of spanwise location of sweep discontinuity on the low-speed longitudinal stability characteristics of a complete model with wings of M and W plan form

Description: Report presenting an investigation of the low-speed static longitudinal stability characteristics of a complete model with a series of M- or W-wings. They were obtained through modification of a basic 45 degree swept wing and had several spanwise locations of sweep discontinuity. Results regarding pitching-moment characteristics, drag due to lift, aerodynamic parameters at zero lift, and possible configurations of airplanes with M- and W-wings are provided.
Date: January 20, 1955
Creator: Fournier, Paul G.
open access

Free-Flight Tests to Determine the Power-on and Power-Off Pressure Distribution and Drag of the NACA RM-10 Research Vehicle at Large Reynolds Numbers Between Mach Numbers 0.8 and 3.0

Description: Memorandum presenting an investigation of the effect of a propulsive jet on the drag and pressure distribution of the NACA RM-10 missile configuration at large Reynolds numbers that utilized rocket models between Mach numbers 0.8 and 3.0. Pressures were measured along the body, near the fin root, and at the base. Results regarding basic data, body pressures, fin pressures, and drag are provided.
Date: September 20, 1955
Creator: Hoffman, Sherwood
open access

A Heated-Wire Liquid-Water-Content Instrument and Results of Initial Flight Tests in Icing Conditions

Description: Memorandum presenting an investigation of a flight version of the NACA heated-wire liquid-water-content instrument, which was constructed and flight tested in natural icing conditions. Data obtained simultaneously with rotting multicylinders indicated that reliable flight measurements of liquid-water content could be made with the heated-wire instrument.
Date: January 20, 1955
Creator: Neel, Carr B.
open access

Investigation of Aerodynamic Characteristics in Pitch and Sideslip of a 45 Degree Sweptback-Wing Airplane Model With Various Vertical Locations of Wing and Horizontal Tail: Basic-Data Presentation, M = 2.01

Description: Memorandum presenting an investigation conducted in the 4- by 4-foot supersonic pressure tunnel to determine the effects of vertical location of wing and horizontal tail on the aerodynamic characteristics in combined pitch and sideslip of a supersonic airplane configuration at a Mach number of 2.01. The configurations investigated included a high-wing, a midwing, and a low-wing arrangement, each with four horizontal-tail locations.
Date: January 20, 1955
Creator: Spearman, M. Leroy; Driver, Cornelius & Hughes, William C.
open access

Performance of 15-Stage Experimental J71 Axial-Flow Compressor. 3 - Effects of Inlet-Guide-Vane Adjustment

Description: The stall-limit line at low speeds was improved somewhat by closing the inlet guide vanes 6 deg, while the design-speed maximum flow and pressure ratio were reduced. The first-stage characteristic curve was moved to lower values of both flog coefficient and equivalent pressure ratio. The second-stage pressure ratio was decreased slightly at high speeds, while the later stages were unaffected.
Date: April 20, 1955
Creator: Lucas, James G. & Filippi, Richard E.
open access

A pressure-distribution investigation of the aerodynamic characteristics of a body of revolution in the vicinity of a reflection plane at Mach numbers of 1.41 and 2.01

Description: The changes in the aerodynamic characteristics of a body of revolution with a fineness ratio of 8 have been determined at Mach numbers of 1.41 and 2.01, a Reynolds number, based on body length, of 4.54 x 10 to the 6th power, and angles of incidence of 0 degrees and plus or minus 3 degrees as the position of the body is varied with respect to a reflection plane. The data are compared with theoretical results.
Date: January 20, 1955
Creator: Gapcynski, John P. & Carlson, Harry W.
open access

Qualitative Results from a Flight Investigation to Determine Aileron Effectiveness of Two Rocket-Propelled 1/20-Scale Models of the MX-76 Missile

Description: "Free-flight tests of two rocket-propelled l/20-scale models of the Bell MX-776 missile have been conducted to obtain measurements of the aileron deflection required to counteract the induced rolling moments caused by combined angles of attack and sideslip and thus to determine whether the ailerons provided were capable of controlling the model at the attitudes produced by the test conditions. Inability to obtain reasonably steady-state conditions and superimposed high-frequency oscillations in… more
Date: October 20, 1955
Creator: Stevens, Joseph E.
open access

Steady-state and surge characteristics of a compressor equipped with variable inlet guide vanes operating in a turbojet engine

Description: Report presenting an investigation of a turbojet engine with variable inlet guide vanes in an altitude test facility to determine the steady-state compressor performance and surge characteristics. Compressor surge pressure ratios were found to be unaffected by changes in flight condition for either position of the inlet guide vanes. Decreasing the inlet Reynolds number was found to reduce the corrected fuel flow required for compressor surge.
Date: June 20, 1955
Creator: Wallner, Lewis E. & Lubick, Robert J.
open access

Study of some effects of structural flexibility on the longitudinal motions and loads as obtained from flight measurements of a swept-wing bomber

Description: Report presenting measurements obtained during elevator-pulse maneuvers with a Boeing B-47A airplane in the a range of Mach numbers which were analyzed to obtain frequency responses in pitching velocity and normal load factor up to frequencies of 43 radians per second.
Date: May 20, 1955
Creator: Donegan, James J. & Huss, Carl R.
open access

Tank investigation of the hydrodynamic characteristics of a 1/3.33-scale jet-powered dynamic model of the Martin XP6M-1 flying boat with a revised forebody planing bottom : TED No. NACA DE 385

Description: From Summary: "Hydrodynamic characteristics have been determined for a 1/13.33-scale jet-powered dynamic model of the Martin XP6M-1 flying boat with the forebody modified so as to increase the depth of step and the angle between the forebody and afterbody keels. Longitudinal stability during takeoff and landing in smooth water and resistance of the complete model in smooth water and in waves are presented."
Date: October 20, 1955
Creator: Blanchard, Ulysse J. & Carter, Arthur W.
open access

Transonic Longitudinal Aerodynamic Effects of Sweeping Up the Rear of the Fuselage of a Rocket-Propelled Airplane Model Having No Horizontal Tail

Description: Report presenting an investigation to determine the effects of fuselage upsweep on the transonic longitudinal aerodynamic characteristics for the horizontal tail-off position of airplanes. Information about lift, static and dynamic stability, trim, drag, and local flow angles at the tail is provided. Sweeping up the rear of the fuselage was found to generally reduce the lift-curve slope, particularly at low positive angles of attack.
Date: January 20, 1955
Creator: Parks, James H.
open access

Transonic Wind-Tunnel Investigation of Effects of Windshield Shape and Canopy Location on the Aerodynamic Characteristics of Canopy-Body Combinations

Description: "Aerodynamic data have been obtained for a fuselage forebody alone and for canopy-body configurations consisting of four different canopies mounted on a fuselage forebody. Two of the canopies had the same shape and size rearward of the windshield but one had a "flat" and the other a "vee" windshield. The remaining two canopies were located at different body stations and were geometrically similar. The data indicated that the drag of the flat-windshield model was consistently lower than that of … more
Date: September 20, 1955
Creator: Cornette, Elden S. & Robinson, Harold L.
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