Download or read book Effect of Forebody Strakes on the Aerodynamic Characteristics in Pitch and Sideslip of a Hypersonic Airplane Configuration at Mach Numbers of 1 41 2 01 and 6 86 written by Cornelius Driver and published by . This book was released on 1959 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Effect at High Subsonic Speeds of Fuselage Forebody Strakes on the Static Stability and Vertical tail load Characteristics of a Complete Model Having a Delta Wing written by Edward C. Polhamus and published by . This book was released on 1958 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: A wind-tunnel investigation at high subsonic speeds has been conducted to determine the effect of fuselage forebody strakes on the static stability and the vertical-tail-load characteristics of an airplane-type configuration having a delta wing. The tests were made at Mach numbers from 0.60 to 0.92 corresponding to Reynolds numbers from 3,000,000 to 4,200,000, based on the wing mean aerodynamic chord, and at angles of attack from approximately -2 to 24 degrees.
Download or read book Aerodynamic Characteristics of an All body Hypersonic Aircraft Configuration at Mach Numbers from 0 65 to 10 6 written by Walter P. Nelms and published by . This book was released on 1971 with total page 108 pages. Available in PDF, EPUB and Kindle. Book excerpt: Aerodynamic characteristics of a model designed to represent an all body, hypersonic cruise aircraft are presented for Mach numbers from 0.65 to 10.6. The configuration had a delta planform with an elliptic cone forebody and an afterbody of elliptic cross section. Detailed effects of varying angle of attack (-2 to 15 deg), angle of sideslip (-2 to 8 deg), Mach number, and configuration buildup were considered. In addition, the effectiveness of horizontal tail, vertical tail, and canard stabilizing and control surfaces was investigated. The results indicate that all configurations were longitudinally stable near maximum lift drag ratio. The configurations with vertical tails were directionally stable at all angles of attack. Trim penalties were small at hypersonic speeds for a center of gravity location representative of the airplane, but because of the large rearward travel of the aerodynamic center, trim penalties were severe at transonic Mach numbers.
Download or read book Effects of Forebody Strakes and Mach Number on Overall Aerodynamic Characteristics of Configuration with 55 Deg Cropped Delta Wing written by Gary E. Erickson and published by . This book was released on 1992 with total page 176 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Effects of Body Shape on the Aerodynamic Characteristics of an All body Hypersonic Aircraft Configuration at Mach Numbers from 0 65 to 10 6 written by Walter P. Nelms and published by . This book was released on 1972 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Effects of Forebody Strakes and Mach Number on Overall Aerodynamic Characteristics of Configuration with 55 cropped Delta Wing written by Gary Edward Erickson and published by . This book was released on 1992 with total page 167 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book The Effects of Wing Plan Form on the Static Longitudinal Aerodynamic Characteristics of a Flat top Hypersonic Aircraft at Mach Numbers from 0 6 to 1 4 written by Stuart L. Treon and published by . This book was released on 1960 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Effects of Forebody Strakes and Mach Number on Overall Aerodynamic Characteristics of Configuration with 55 Deg Cropped Delta Wing written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-17 with total page 174 pages. Available in PDF, EPUB and Kindle. Book excerpt: A wind tunnel data base was established for the effects of chine-like forebody strakes and Mach number on the longitudinal and lateral-directional characteristics of a generalized 55 degree cropped delta wing-fuselage-centerline vertical tail configuration. The testing was conducted in the 7- by 10-Foot Transonic Tunnel at the David Taylor Research Center at free-stream Mach numbers of 0.40 to 1.10 and Reynolds numbers based on the wing mean aerodynamic chord of 1.60 x 10(exp 6) to 2.59 x 10(exp 6). The best matrix included angles of attack from 0 degree to a maximum of 28 degree, angles of sidesip of 0, +5, and -5 degrees, and wing leading-edge flat deflection angles of 0 and 30 degrees. Key flow phenomena at subsonic and transonic conditions were identified by measuring off-body flow visualization with a laser screen technique. These phenomena included coexisting and interacting vortex flows and shock waves, vortex breakdown, vortex flow interactions with the vertical tail, and vortices induced by flow separation from the hinge line of the deflected wing flap. The flow mechanisms were correlated with the longitudinal and lateral-directional aerodynamic data trends. Erickson, Gary E. and Rogers, Lawrence W. Langley Research Center AERODYNAMIC CHARACTERISTICS; DELTA WINGS; FLOW CHARACTERISTICS; FOREBODIES; LATERAL STABILITY; LONGITUDINAL STABILITY; MACH NUMBER; STRAKES; WIND TUNNEL TESTS; AIRFOIL PROFILES; ANGLE OF ATTACK; BOUNDARY LAYER SEPARATION; CHORDS (GEOMETRY); FLOW VISUALIZATION; SHOCK WAVES; VORTEX BREAKDOWN; VORTICES; WING FLAPS...
Download or read book Effects of Forebody Strakes and Mach Number on Overall Aerodynamic Characteristics of Configuration with 550 Cropped Delta Wing written by and published by . This book was released on 1992 with total page 167 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Effects of Forebody Strakes and Mach Number on Overall Aerodynamic Characteristics of Configuration with 55 Degree Cropped Delta Wing written by Gary E. Erickson and published by . This book was released on 1992 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aerodynamic Characteristics at Mach 6 of a Hypersonic Research Airplane Concept Having a 70 swept Delta Wing written by Louis E. Clark and published by . This book was released on 1977 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Effects of Forebody Strakes and Mach Number on Overall Aerodynamic Characteristics on Configuration with 55 Degrees Cropped Delta Wing written by Gary E. Erickson and published by . This book was released on 1992 with total page 170 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Effect of Forebody Geometry on the Supersonic Aerodynamic Characteristics of a Fixed Wing Canard Supersonic Transport Model written by and published by . This book was released on 1964 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aerodynamic Characteristics of a 1 22 scale Model of a Fighter Airplane with an Extended Forebody and Other Modifications at Mach Numbers of 1 57 and 2 01 written by and published by . This book was released on 1963 with total page 94 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aerodynamic Characteristics Including Effect of Body Shape of a Mach 6 Aircraft Concept written by Gregory D. Riebe and published by . This book was released on 1983 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aerodynamic Characteristics at Mach 6 of a Wing body Concept for a Hypersonic Research Airplane written by James L. Dillon and published by . This book was released on 1978 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt: The static aerodynamic characteristics of a 1/30 scale model of a wing-body concept for a high speed research airplane were investigated in the Langley 20 inch Mach six tunnel. The investigation consisted of configuration buildup from the basic body by adding a wing, center vertical tail, three-module scramjet, and six-module scramjet engine. The test Mach number was six at a Reynolds number, based on model fuselage length, of about 13,700,000. The test angle-of-attack range was 4 to 20 D at constant angles of sideslip of 0, 2, and 4 deg. The elevons were deflected from 10 to -15 D for pitch control. Roll and yaw control were investigated. Experimental aerodynamic characteristics are compared with analytical elements.
Download or read book Supersonic Aerodynamic Characteristics of an Advanced F 16 Derivative Aircraft Configuration written by Mike C. Fox and published by . This book was released on 1993 with total page 130 pages. Available in PDF, EPUB and Kindle. Book excerpt:
