Supersonic Aerodynamic Characteristics of an Advanced F-16 Derivative Aircraft Configuration
Author: Mike C. Fox
Publisher:
Published: 1993
Total Pages: 130
ISBN-13:
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Author: Mike C. Fox
Publisher:
Published: 1993
Total Pages: 130
ISBN-13:
DOWNLOAD EBOOKAuthor: National Aeronautics and Space Adm Nasa
Publisher: Independently Published
Published: 2018-11-14
Total Pages: 124
ISBN-13: 9781731320186
DOWNLOAD EBOOKA supersonic wind tunnel investigation was conducted in the NASA Langley Unitary Plan Wind Tunnel on an advanced derivative configuration of the United States Air Force F-16 fighter. Longitudinal and lateral directional force and moment data were obtained at Mach numbers of 1.60 to 2.16 to evaluate basic performance parameters and control effectiveness. The aerodynamic characteristics for the F-16 derivative model were compared with the data obtained for the F-16C model and also with a previously tested generic wing model that features an identical plan form shape and similar twist distribution. Fox, Mike C. and Forrest, Dana K. Langley Research Center AERODYNAMIC CHARACTERISTICS; AIRCRAFT CONFIGURATIONS; AIRCRAFT MODELS; DELTA WINGS; F-16 AIRCRAFT; MACH NUMBER; WIND TUNNEL MODELS; WIND TUNNEL TESTS; CONTROLLABILITY; SUPERSONIC WIND TUNNELS...
Author:
Publisher:
Published: 1960
Total Pages: 80
ISBN-13:
DOWNLOAD EBOOKA free-flight rocket-propelled-model investigation was conducted at Mach numbers of 1.2 to 1.9 to determine the longitudinal and lateral aero-dynamic characteristics of a low-drag aircraft configuration. The model consisted of an aspect-ratio -1.86 arrow wing with 67.5 deg. leading-edge sweep and NACA 65A004 airfoil section and a triangular vertical tail with 60 deg. sweep and NACA 65A003 section in combination with a body of fineness ratio 20. Aerodynamic data in pitch, yaw, and roll were obtained from transient motions induced by small pulse rockets firing at intervals in the pitch and yaw directions. From the results of this brief aerodynamic investigation, it is observed that very slender body shapes can provide increased volumetric capacity with little or no increase in zero-lift drag and that body fineness ratios of the order of 20 should be considered in the design of long-range supersonic aircraft. The zero-lift drag and the drag-due-to-lift parameter of the test configuration varied linearly with Mach number. The maximum lift-drag ratio was 7.0 at a Mach number of 1.25 and decreased slightly to a value of 6.6 at a Mach number of 1.81. The optimum lift coefficient, normal-force-curve slope, lateral-force-curve slope, static stability in pitch and yaw, time to damp to one-half amplitude in pitch and yaw, the sum of the rotary damping derivatives in pitch and also in yaw, and the static rolling derivatives all decreased with an increase in Mach number. Values of certain rolling derivatives were obtained by application of the least-squares method to the differential equation of rolling motion. A comparison of the experimental and calculated total rolling-moment-coefficient variation during transient oscillations of the model indicated good agreement when the damping-in-roll contribution was included with the static rolling-moment terms.
Author: Warren Gillespie Jr.
Publisher:
Published: 1960
Total Pages: 64
ISBN-13:
DOWNLOAD EBOOKAuthor: Gerald V. Foster
Publisher:
Published: 1964
Total Pages: 54
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DOWNLOAD EBOOKAuthor: William J. Monta
Publisher:
Published: 1980
Total Pages: 64
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DOWNLOAD EBOOKAuthor: James C. Ferris
Publisher:
Published: 1966
Total Pages: 66
ISBN-13:
DOWNLOAD EBOOKAuthor: Alan B. Kehlet
Publisher:
Published: 1954
Total Pages: 42
ISBN-13:
DOWNLOAD EBOOKAuthor: Francis J. Capone
Publisher:
Published: 1986
Total Pages: 112
ISBN-13:
DOWNLOAD EBOOKAuthor: Warren Gillespie
Publisher:
Published: 1957
Total Pages: 59
ISBN-13:
DOWNLOAD EBOOKA free-flight rocket-propelled model investigation was conducted at Mach numbers of 1.2 to 1.9 to determine the longitudinal and lateral aerodynamic characteristics of a low-drag aircraft configuration. The model consisted of an aspect-ratio-1.86 arrow wing with 67.5 degree leading-edge sweep and NACA 65A004 section, and a triangular vertical tail with 60 degree sweep and NACA 65A003 section, in combination with a body of fineness ratio 20. Aerodynamic data in pitch, yaw, and roll were obtained from transient motions induced by small pulse rockets firing at intervals in the pitch and yaw directions.