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Effects At Mach Numbers Of 161 And 201 Of Camber And Twist On The Aerodynamic Characteristics Of Three Swept Wings Having The Same Planform
Download Effects At Mach Numbers Of 161 And 201 Of Camber And Twist On The Aerodynamic Characteristics Of Three Swept Wings Having The Same Planform full books in PDF, epub, and Kindle. Read online Effects At Mach Numbers Of 161 And 201 Of Camber And Twist On The Aerodynamic Characteristics Of Three Swept Wings Having The Same Planform ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis Effects of Twist and Camber and Thickness on the Aerodynamic Characteristics of a 75° Swept Arrow Wing at a Mach Number of 2.91 by : James N. Mueller
Download or read book Effects of Twist and Camber and Thickness on the Aerodynamic Characteristics of a 75° Swept Arrow Wing at a Mach Number of 2.91 written by James N. Mueller and published by . This book was released on 1959 with total page 72 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Transonic Aerodynamic Loading Characteristics of a Wing-body-tail Combination Having 52.5° Sweptback Wing of Aspect Ratio 3 with Conical Wing Camber and Body Indentation for a Design Mach Number [square Root Of] 2 by : Marlowe D. Cassetti
Download or read book Transonic Aerodynamic Loading Characteristics of a Wing-body-tail Combination Having 52.5° Sweptback Wing of Aspect Ratio 3 with Conical Wing Camber and Body Indentation for a Design Mach Number [square Root Of] 2 written by Marlowe D. Cassetti and published by . This book was released on 1961 with total page 104 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been made of the effects of conical wing camber and body indentation according to the supersonic area rule on the aerodynamic wing loading characteristics of a wing-body-tail configuration at transonic speeds. The wing aspect ratio was 3, taper ratio was 0.1, and quarter-chord-line sweepback was 52.5° with 3-percent-thick airfoil sections. The tests were conducted in the Langley 16-foot transonic tunnel at Mach numbers from 0.80 to 1.05 and at angles of attack from 0° to 14°, with Reynolds numbers based on mean aerodynamic chord varying from 7 x 106 to 8 x 106. Conical camber delayed wing-tip stall and reduced the severity of the accompanying longitudinal instability but did not appreciably affect the spanwise load distribution at angles of attack below tip stall. Body indentation reduced to transonic chordwise center-of-pressure travel from about 8 percent to 5 percent of the mean aerodynamic chord.
Book Synopsis Off-design Aerodynamic Characteristics at Mach Numbers 1.61 and 2.20 of a Series of Highly Swept Arrow Wings Designed for Mach Number 2.0 Employing Various Degrees of Twist and Camber by : Wilbur D. Middleton
Download or read book Off-design Aerodynamic Characteristics at Mach Numbers 1.61 and 2.20 of a Series of Highly Swept Arrow Wings Designed for Mach Number 2.0 Employing Various Degrees of Twist and Camber written by Wilbur D. Middleton and published by . This book was released on 1963 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Transonic Aerodynamic Characteristics of a Wing-body Combination Having a 52.20 Sweptback Wing of Aspect Ratio 3 with Conical Camber and Designed for a Mach Number of 2 by : William B. Igoe
Download or read book Transonic Aerodynamic Characteristics of a Wing-body Combination Having a 52.20 Sweptback Wing of Aspect Ratio 3 with Conical Camber and Designed for a Mach Number of 2 written by William B. Igoe and published by . This book was released on 1961 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effects of Leading-edge Sweep Angle and Design Lift Coefficient on Performance of a Modified Arrow Wing at a Design Mach Number of 2.6 by : Robert J. Mack
Download or read book Effects of Leading-edge Sweep Angle and Design Lift Coefficient on Performance of a Modified Arrow Wing at a Design Mach Number of 2.6 written by Robert J. Mack and published by . This book was released on 1974 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt: Wing models were tested in the high-speed section of the Langley Unitary Plan wind tunnel to study the effects of the leading-edge sweep angle and the design lift coefficient on aerodynamic performance and efficiency. The models had leading-edge sweep angles of 69.44 deg, 72.65 deg, and 75.96 deg which correspond to values of the design Mach-number-sweep-angle parameter (beta cotangent A) sub DES of 0.6, 0.75, and 0.9, respectively. For each sweep angle, camber surfaces having design lift coefficients of 0,0.08, and 0.12 at a design Mach number of 2.6 were generated. The wind-tunnel tests were conducted at Mach numbers of 2.3, 2.6, and 2.96 with a stagnation temperature of 338.7 K (150 F) and a Reynolds number per meter of 9.843 times 10 to the 6th power. The results of the tests showed that only a moderate sweeping of the wing leading edge aft of the Mach line along with a small-to-moderate amount of camber and twist was needed to significantly improve the zero-lift (flat camber surface) wing performance and efficiency.
Book Synopsis Static Longitudinal Aerodynamic Characteristics of Close-coupled Wing-canard Configurations at Mach Numbers from 1.60 to 2.86 by : Samuel M. Dollyhigh
Download or read book Static Longitudinal Aerodynamic Characteristics of Close-coupled Wing-canard Configurations at Mach Numbers from 1.60 to 2.86 written by Samuel M. Dollyhigh and published by . This book was released on 1971 with total page 126 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation was made in the Mach number range from 1.60 to 2.86 to determine the static longitudinal aerodynamic characteristics of close-coupled wing-canard configurations. Three canards, ranging in exposed planform area from 17.5 to 30.0 percent of the wing reference area, were employed in this investigation. The canards were either located in the plane of the wing or in a position 18.5 percent of the wing mean geometric chord above the wing plane. Most data obtained were for a model with a 60 deg leading-edge-sweep wing; however, a small amount of data were obtained for a 44 deg leading-edge-sweep wing. The model utilized two balances to isolate interference effects between wing and canard. In general, it was determined that at angle of attack for all configurations investigated with the canard in the plane of the wing an unfavorable interference exists which causes the additional lift on the canard generated by a canard deflection to be lost on the wing due to an increased downwash at the wing from the canard. Further, this interference decreased somewhat with increasing Mach number. Raising the canard above the plane of the wing also greatly decreased the interference of the canard deflection on the wing lift. However, at Mach 2.86 the presence of the canard in the high position had a greater unfavorable interference effect at high angles of attack than the canard in the wing plane. This interference resulted in the in-plane canard having better trimmed performance at Mach 2.86 for the same center-of-gravity location.
Book Synopsis Aerodynamic Characteristics at Mach Number 2.05 of a Series of Highly Swept Arrow Wings Employing Various Degrees of Twist and Camber by : Harry W. Carlson
Download or read book Aerodynamic Characteristics at Mach Number 2.05 of a Series of Highly Swept Arrow Wings Employing Various Degrees of Twist and Camber written by Harry W. Carlson and published by . This book was released on 1960 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Experimental Investigation at a Mach Number of 2.01 of the Effects of Body Cross-section Shape on the Aerodynamic Characteristics of Bodies and Wing-body Combinations by : Harry W. Carlson
Download or read book An Experimental Investigation at a Mach Number of 2.01 of the Effects of Body Cross-section Shape on the Aerodynamic Characteristics of Bodies and Wing-body Combinations written by Harry W. Carlson and published by . This book was released on 1955 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstract: An experimental investigation has been performed to determine the effect of changes in body cross-section shape on the aerodynamic characteristics of bodies and wing-body combinations. A series of 13 bodies having a given length and given longitudinal distribution of cross-sectional area but various cross-section shapes were tested at a Mach number of 2.01. The bodies were tested alone and in combination with a 47° sweptback wing having a 6-percent-thick hexagonal section.
Book Synopsis Aerodynamic Characteristics of a Tailless Fixed-wing Supersonic Transport Configuration at Mach Number 2.20 by : Gerald V. Foster
Download or read book Aerodynamic Characteristics of a Tailless Fixed-wing Supersonic Transport Configuration at Mach Number 2.20 written by Gerald V. Foster and published by . This book was released on 1964 with total page 54 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effects of Wing Elevation, Incidence, and Camber on the Aerodynamic Characteristics of a Representative Hypersonic Cruise Configuration at Mach Numbers from 0.65 to 10.70 by : Walter P. Nelms
Download or read book Effects of Wing Elevation, Incidence, and Camber on the Aerodynamic Characteristics of a Representative Hypersonic Cruise Configuration at Mach Numbers from 0.65 to 10.70 written by Walter P. Nelms and published by . This book was released on 1970 with total page 82 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis The Effect of Camber on the Aerodynamic Characteristics of a Body at a Mach Number of 2.01 by : John P. Gapcynski
Download or read book The Effect of Camber on the Aerodynamic Characteristics of a Body at a Mach Number of 2.01 written by John P. Gapcynski and published by . This book was released on 1959 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Some Effects of Tail Height and Wing Plan Form on the Static Longitudinal Stability Characteristics of a Small-scale Model at High Subsonic Speeds by : Albert G. Few
Download or read book Some Effects of Tail Height and Wing Plan Form on the Static Longitudinal Stability Characteristics of a Small-scale Model at High Subsonic Speeds written by Albert G. Few and published by . This book was released on 1954 with total page 78 pages. Available in PDF, EPUB and Kindle. Book excerpt: The drag due to lift increases with increasing sweep through the Mach number range. Some increase in bag due to lift is evident decrease in taper ratio for wings having 300of sweep through most of the speed range.
Book Synopsis Low-speed Investigation of the Effects of Wing Sweep on the Aerodynamic Characteristics of Parawings Having Equal-length Leading Edges and Keel by : Rodger L. Naeseth
Download or read book Low-speed Investigation of the Effects of Wing Sweep on the Aerodynamic Characteristics of Parawings Having Equal-length Leading Edges and Keel written by Rodger L. Naeseth and published by . This book was released on 1963 with total page 88 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been made in the Langley 300-MPH 7- by 10-foot tunnel to determine the aerodynamic characteristics of a related series of parawings in which wing sweep was the primary variable. The leading-edge sweep angles varied from 400 to 750 and the three basic parawings had flat-planform sweep angles of 350, 450, and 550. The canopies of the wings were made of fabric. Tests were made at an airspeed of 38.6 mph and a Reynolds number of approximately 1.5 X 106. The maximum angle-of-attack range was from 140 to 530 for the wings having a canopy of 350 flat-planform sweep. A limited investigation of lateral characteristics was made for sideslip angles from approximately -50 to 160 for two angles of attack, and lateral stability derivatives were obtained for some configurations through a angle-of-attack range. Forces and moments acting on the wing and apex hinge moments were measured.
Book Synopsis Longitudinal Aerodynamic Characteristics of a High-subsonic-speed Transport Airplane Model with a Cambered 40° Sweptback Wing of Aspect Ratio 8 at Mach Numbers to 0.96 by : Atwood R. Heath
Download or read book Longitudinal Aerodynamic Characteristics of a High-subsonic-speed Transport Airplane Model with a Cambered 40° Sweptback Wing of Aspect Ratio 8 at Mach Numbers to 0.96 written by Atwood R. Heath and published by . This book was released on 1960 with total page 92 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 Aerodynamic-center Considerations of Wings and Wing-body Combinations by : John E. Lamar
Download or read book Aerodynamic-center Considerations of Wings and Wing-body Combinations written by John E. Lamar and published by . This book was released on 1966 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis The Flow Past a Straight- and a Swept-wing-body Combination and Their Equivalent Bodies of Revolution at Mach Numbers Near 1.0 by : W. F. Lindsey
Download or read book The Flow Past a Straight- and a Swept-wing-body Combination and Their Equivalent Bodies of Revolution at Mach Numbers Near 1.0 written by W. F. Lindsey and published by . This book was released on 1954 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstract: The complete flow fields past a straight and a swept wing-body combination and their equivalent bodies of revolution at Mach numbers around 1.0 have been observed by means of motion-picture schlieren photography. The results of these observations indicate that the shock growth and positions on the wing-body combinations are closely reproduced in the flow past their respective equivalent bodies.
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