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Aerodynamic Characteristics Of A 00667 Scale Model Of The North American X 15 Research Airplane At Transonic Speeds
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Book Synopsis Aerodynamic Characteristics of a 0.0667-scale Model of the North American X-15 Research Airplane at Transonic Speeds by : Robert S. Osborne
Download or read book Aerodynamic Characteristics of a 0.0667-scale Model of the North American X-15 Research Airplane at Transonic Speeds written by Robert S. Osborne and published by . This book was released on 1959 with total page 112 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Investigation of the Aerodynamic Characteristics of a 0.067-scale Model of the X-15 Airplane (configuration 3) at Mach Numbers of 2.29, 2.98, and 4.65 by : Arthur E. Franklin
Download or read book Investigation of the Aerodynamic Characteristics of a 0.067-scale Model of the X-15 Airplane (configuration 3) at Mach Numbers of 2.29, 2.98, and 4.65 written by Arthur E. Franklin and published by . This book was released on 1959 with total page 180 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Longitudinal Aerodynamic Characteristics of a Model Airplane Configuration Equipped with a Scaled X-1 Airplane Wing by : James H. Parks
Download or read book Longitudinal Aerodynamic Characteristics of a Model Airplane Configuration Equipped with a Scaled X-1 Airplane Wing written by James H. Parks and published by . This book was released on 1952 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Longitudinal Stability Characteristics at Transonic Speeds of a Rocket-propelled Model of an Airplane Having a 45 Degree Swept Wing of Aspect Ratio 6.0 by : John C. McFall
Download or read book Longitudinal Stability Characteristics at Transonic Speeds of a Rocket-propelled Model of an Airplane Having a 45 Degree Swept Wing of Aspect Ratio 6.0 written by John C. McFall and published by . This book was released on 1954 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerodynamic Characteristics at Transonic and Supersonic Speeds of a Rocket-propelled Airplane Configuration Having a Diamond-plan-form Wing Aspect Ration 3.08 and a Low, Swept Horizontal Tail by : Alan B. Kehlet
Download or read book Aerodynamic Characteristics at Transonic and Supersonic Speeds of a Rocket-propelled Airplane Configuration Having a Diamond-plan-form Wing Aspect Ration 3.08 and a Low, Swept Horizontal Tail written by Alan B. Kehlet and published by . This book was released on 1954 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Investigation of the Aerodynamic Characteristics of a 0.067-scale Model of the X-15 Airplane /configuration 3/ at Mach Numbers of 2.29, 2.98, and 4.65 by :
Download or read book Investigation of the Aerodynamic Characteristics of a 0.067-scale Model of the X-15 Airplane /configuration 3/ at Mach Numbers of 2.29, 2.98, and 4.65 written by and published by . This book was released on 1959 with total page 176 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Subsonic Flight Tests of a 1/7-scale Radio-controlled Model of the North American X-15 Airplane with Particular Reference to High Angle-of-attack Conditions by : Donald E. Hewes
Download or read book Subsonic Flight Tests of a 1/7-scale Radio-controlled Model of the North American X-15 Airplane with Particular Reference to High Angle-of-attack Conditions written by Donald E. Hewes and published by . This book was released on 1960 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NACA Research Memorandum written by and published by . This book was released on 19?? with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Transonic Longitudinal Aerodynamic Effects of Sweeping Up the Rear of the Fuselage of a Rocket-propelled Airplane Model Having No Horizontal Tail by : James H. Parks
Download or read book Transonic Longitudinal Aerodynamic Effects of Sweeping Up the Rear of the Fuselage of a Rocket-propelled Airplane Model Having No Horizontal Tail written by James H. Parks and published by . This book was released on 1955 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Low-Speed Aerodynamic Characteristics of a Model of a Hypersonic Research Airplane at Angles of Attack Up to 90 Deg for a Range of Reynolds Numbers by :
Download or read book Low-Speed Aerodynamic Characteristics of a Model of a Hypersonic Research Airplane at Angles of Attack Up to 90 Deg for a Range of Reynolds Numbers written by and published by . This book was released on 1960 with total page 70 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Transonic Longitudinal Aerodynamic Characteristics of a Fighter-type Airplane Model with a Low-aspect-ratio Unswept Wing and Tee-tail by : Gerald Hieser
Download or read book Transonic Longitudinal Aerodynamic Characteristics of a Fighter-type Airplane Model with a Low-aspect-ratio Unswept Wing and Tee-tail written by Gerald Hieser and published by . This book was released on 1956 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Transonic Investigation of Aerodynamic Characteristics of a Swept-wing Fighter-airplane Model with Leading-edge Droop in Combination with Outboard Chord-extensions and Notches by : Charles F. Whitcomb
Download or read book Transonic Investigation of Aerodynamic Characteristics of a Swept-wing Fighter-airplane Model with Leading-edge Droop in Combination with Outboard Chord-extensions and Notches written by Charles F. Whitcomb and published by . This book was released on 1956 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation of the effects of several wing leading-edge modifications on the aerodynamic characteristics of a 45 degree swept-wing fighter-airplane model has been conducted in the Langley 16-foot transonic tunnel at low and high lifting conditions at Mach numbers from 0.85 to 1.03. The investigation included the determination of the effect on longitudinal stability and performance characteristics of wing leading-edge and chord-extension droops of 6 and 20 degrees, chord-extension overhangs of 0.075c and 0.15c (where c is the wing chord), leading-edge notches cut out at the inboard end of the 0.075c chord-extension to depths of 0.075c and 0.125c, and indentation of the model fuselage to conform partially to the supersonic area rule for a Mach number of 1.20. Lift, drag, and pitching-moment data were obtained for configurations with the tail on and off. Comparisons of data obtained from the present model with data from a configuration with leading-edge slats are included.
Book Synopsis Investigation of the Subsonic Stability and Control Characteristics of a 1/7-Scale Model of the North American X-15 Airplane with and Without Fuselage Forebody Strakes by :
Download or read book Investigation of the Subsonic Stability and Control Characteristics of a 1/7-Scale Model of the North American X-15 Airplane with and Without Fuselage Forebody Strakes written by and published by . This book was released on 1960 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Determination by the Free-fall Method of the Longitudinal Stability and Control Characteristics of a 1/4-scale Model of the Bell XS-1 Airplane at Transonic Speeds by : James F. Matthews
Download or read book Determination by the Free-fall Method of the Longitudinal Stability and Control Characteristics of a 1/4-scale Model of the Bell XS-1 Airplane at Transonic Speeds written by James F. Matthews and published by . This book was released on 1948 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerodynamic Characteristics and Control Effectiveness of the HL-20 Lifting Body Configuration at Mach 10 in Air by : William I. Scallion
Download or read book Aerodynamic Characteristics and Control Effectiveness of the HL-20 Lifting Body Configuration at Mach 10 in Air written by William I. Scallion and published by . This book was released on 1999 with total page 62 pages. Available in PDF, EPUB and Kindle. Book excerpt: A 0.0196-scale model of the HL-20 lifting body, one of several configurations proposed for future crewed spacecraft, was tested in the Langley 31-Inch Mach 10 Tunnel. The purpose of the tests was to determine the effectiveness of fin-mounted elevons, a lower surface flush-mounted body flap, and a flush-mounted yaw controller at hypersonic speeds. The nominal angle-of-attack range, representative of hypersonic entry, was 20 to 41 degrees, the sideslip angles were 0, 2, and -2 degrees, and the test Reynolds number was 1.06 x 10[factor 6] based on model reference length. The aerodynamic, longitudinal, and lateral control effectiveness along with surface oil flow visualizations are presented and discussed. The configuration was longitudinally and laterally stable at the nominal center of gravity. The primary longitudinal control, the fin-mounted elevons, could not trim the model to the desired entry angle of attack of 30 degrees. The lower surface body flaps were effective for roll control and the associated adverse yawing moment was eliminated by skewing the body flap hinge lines. A yaw controller, flush-mounted on the lower surface, was also effective, and the associated small rolling moment was favorable.
Book Synopsis Aerodynamic Properties of Cruciform-wing and Body Combinations at Subsonic, Transonic, and Supersonic Speeds by : John R. Spreiter
Download or read book Aerodynamic Properties of Cruciform-wing and Body Combinations at Subsonic, Transonic, and Supersonic Speeds written by John R. Spreiter and published by . This book was released on 1949 with total page 646 pages. Available in PDF, EPUB and Kindle. Book excerpt: The aerodynamic forces and moments exerted on pitched and yawed wing-body combinations consisting of a slender body of revolution and a cruciform arrangement of thin wings have been investigated by two theoretical methods. One method, an extension of the slender wing-body theory of NACA TN No. 1662, makes possible the determination of simple closed expressions for the load distribution, of simple closed expressions for the load distribution, the forces, and the moments for slender cruciform-wing and body combinations in which the wings may be dissimilar plan form. The second method treats cruciform-wing and body combinations consisting of a body of revolution and identical wings of arbitrary aspect ratio and plan form. The results are valid at subsonic, transonic, and supersonic speeds.
