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  • 1975-1979  (9)
  • 1
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    Longitudinal aerodynamic characteristics at Mach numbers from 1.60 to 2.86 for a fixed-span missile with three wing planforms (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Effects of wing planform modifications on the longitudinal aerodynamic characteristics of a fixed span, maneuverable cruciform missile configuration were determined. A basic delta planform and two alternate trapezoidal planforms having progressively increasing tip chords were included. Data were obtained for angles of attack up to approximately -32 deg, model roll angles of 0 deg to 45 deg, and tail control deflections of 0 deg and -20 deg. The experimental drag due to lift was compared with linear values.
    Keywords: AERODYNAMICS
    Type: NASA-TM-74088 , L-11916
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Historical development of world wide guided missiles (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: This paper attempts to put in perspective the development of missiles from early history to present time. The influence of World War II in accelerating the development of guided missiles, particularly through German scientists, is discussed. The dispersion of German scientists to other countries and the coupling of their work with native talent to develop guided missiles is traced. Particular emphasis is placed on the evolution of the missile in the U.S. and the U.S.S.R. Since the Soviets possess what is probably the world's most complete array of dedicated missile system types, their known inventory is reviewed in some detail.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: AIAA PAPER 78-210 , Aerospace Sciences Meeting; Jan 16, 1978 - Jan 18, 1978; Huntsville, AL
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Historical development of worldwide supersonic aircraft (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Aerodynamic problems in the development of supersonic aircraft, their solutions, and innovative design features are presented. Studies of compressibility, introduction of jets, supersonic phenomena, transonic drag and lift, longitudinal and directional stability, dynamic pressure fields, and advent of the supersonic fighter are discussed. The flight research aircraft such as the Bell X-1 and the Douglas-558, the century series models, reconnaissance aircraft, the multimission tactical fighter, and the current generation fighters such as F-16 and F-18 are described. The SCAT program is considered, along with supersonic developments in Great Britain, France, and USSR. It is concluded that the sonic boom still appears to be an inherent problem of supersonic flight that particularly affects overland commercial flight, and efforts continue for increased efficiency for economic and performance gains and increased safety for military and civilian aircraft.
    Keywords: AERONAUTICS (GENERAL)
    Type: AIAA PAPER 79-1815 , American Institute of Aeronautics and Astronautics, Aircraft Systems and Technology Meeting; Aug 20, 1979 - Aug 22, 1979; New York, NY
    Format: text
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  • 4
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    Effects of external stores on the air combat capability of a delta wing fighter (1977)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Delta wing point-design fighters with two pylon mounted missiles and aft tail controls (similar to several Soviet designs) have been investigated for a Mach number range from about 0.6 to 2.0. Whereas minimum drag penalties that are expected with the addition of external stores do occur, the effects at higher lifts, corresponding to maneuvering flight, are less severe and often favorable. The drag-due-to-lift factor is less with stores on although the lift curve slope is unaffected. The longitudinal stability level is reduced by the addition of stores while the pitch control effectiveness is unchanged. The directional stability was generally reduced at subsonic speeds and increased at supersonic speeds by the addition of stores but sufficiently high stability levels are obtainable that are compatible with the longitudinal maneuvering limits. Some examples of the potential maneuvering capability in terms of normal acceleration and turn radius are included.
    Keywords: AERODYNAMICS
    Type: Aircraft/Stores Compatibility Symposium; Oct 12, 1977 - Oct 14, 1977; Fort Walton Beach, FL
    Format: text
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  • 5
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    Aerodynamic characteristics of supersonic fighter airplane configurations based on Soviet design concepts (1977)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The aerodynamic, stability, and control characteristics of several supersonic fighter airplane concepts are examined. The configurations, which are based on Soviet design concepts, include fixed-wing aircraft having delta wings, swept wings, and trapezoidal wings, and a variable wing-sweep aircraft. Each concept employs aft tail controls. The concepts vary from lightweight, single-engine, air superiority, point interceptor, or ground attack types to larger twin-engine interceptor and reconnaissance designs. Analytical and experimental results indicate that careful application of the transonic or supersonic area rule can provide nearly optimum shaping for minimum drag for a specified Mach number requirement. In addition, through the proper location of components and the exploitation of interference flow fields, the concepts provide linear pitching moment characteristics, high control effectiveness, and reasonably small variations in aerodynamic center location with a resulting high potential for maneuvering capability.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 77-1162 , Atmospheric Flight Mechanics Conference; Aug 08, 1977 - Aug 10, 1977; Hollywood, FL
    Format: text
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  • 6
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    Supersonic aerodynamic characteristics of a tail-control cruciform maneuverable missile with and without wings (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The aerodynamic characteristics for a winged and a wingless cruciform missile are examined. The body was an ogive-cylinder with a 3.5 caliber forebody; an overall length-to-diameter ratio of 11.667; and has cruciform tails that were trapexoidal in planform. Tests were made both with and without 72.9 deg cruciform delta wings. The investigation was made for Mach numbers from 1.50 to 4.63, roll attitudes of 0 and 45 deg, angles of attack from -40 to 22 deg, and tail control deflections from 10 to -40 deg. The purpose is to determine the influence of the aerodynamic behavior on the design choice for maneuverable missiles intended primarily for air-to-air or surface-to-surface missions. The results indicate that the winged missile with its more linear aerodynamic characteristics and higher lift-curve slope, should provide the highest maneuverability over a large operational range.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 78-1351 , Atmospheric Flight Mechanics Conference; Aug 07, 1978 - Aug 09, 1978; Palo Alto, CA
    Format: text
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  • 7
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    The role of wind tunnels in predicting sounding rocket aerodynamics (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The aerodynamic characteristics of sounding rockets, in some cases, may be adequately determined by various estimating procedures, however, there are cases where these procedures fail and wind tunnel studies become necessary. The present paper deals with configurations of the latter type, for which the problems of concern include mismatched diameters between stages, mutual fin interference effects, fin alignment and orientation, body deflections between stages, boundary layer growth, and stability changes that occur as stages are dropped. Some characteristics related to separated flow, interference flow fields, and Reynolds number are examined.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 79-0505 , Sounding Rocket Technology Conference; Mar 07, 1979 - Mar 09, 1979; Houston, TX
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Aerodynamic characteristics of missile configurations based on Soviet design concepts (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The aerodynamic characteristics of several missile concepts are examined. The configurations, which are based on some typical Soviet design concepts, include fixed-wing missiles with either forward- or aft-tail controls, and wing-control missiles with fixed aft stabilizing surfaces. The conceptual missions include air-to-air, surface-to-air, air-to-surface, and surface-to-surface. Analytical and experimental results indicate that through the proper shaping and location of components, and through the exploitation of local flow fields, the concepts provide generally good stability characteristics, high control effectiveness, and low control hinge moments. In addition, in the case of some cruise-type missions, there are indications of the application of area ruling as a means of improving the aerodynamic efficiency. In general, a point-design philosophy is indicated whereby a particular configuration is developed for performing a particular mission.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 79-1657 , Atmospheric Flight Mechanics Conference for Future Space Systems; Aug 06, 1979 - Aug 08, 1979; Boulder, CO
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Wind-tunnel studies of the effects of simulated damage on the aerodynamic characteristics of airplanes and missiles (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: In order to assess the effects on static aerodynamic characteristics of battle damage to an aircraft or missile, wind tunnel studies were performed on models from which all or parts of the wing or horizontal or vertical tail had been removed. The effects of damage on the lift, longitudinal stability, lateral stability and directional stability of a swept-wing fighter are presented, along with the effects of wing removal on the control requirements of a delta-wing fighter. Results indicate that the loss of a major part of the vertical tail will probably result in the loss of the aircraft at any speed, while the loss of major parts of the horizontal tail generally results in catastrophic instability at subsonic speeds but, at low supersonic speeds, may allow the aircraft to return to friendly territory before pilot ejection. Major damage to the wing may be sustained without the loss of aircraft or pilot. The loss of some of the aerodynamic surfaces of cruise or surface-to-air missiles may result in catastrophic instability or may permit a ballistic trajectory to be maintained, depending upon the location of the lost surface with respect to the center of gravity of the missile.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: American Defense Preparedness Association, Vulnerability and Survivability Symposium, 4th, Tyndall AFB; Mar 14, 1979 - Mar 15, 1979; Tyndall AFB, FL
    Format: text
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