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Pressure Distributions On Blunt Delta Wings At Angles Of Attack Up To 90 Degrees And Mach Number Of 685
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Book Synopsis Pressure Distributions on Blunt-delta Wings at Angles of Attack Up to 90 Degrees and Mach Number of 6.85 by : Peter T. Bernot
Download or read book Pressure Distributions on Blunt-delta Wings at Angles of Attack Up to 90 Degrees and Mach Number of 6.85 written by Peter T. Bernot and published by . This book was released on 1963 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Local Pressure Distribution on a Blunt Delta Wing for Angles of Attack Up to 35 Degrees at Mach Numbers of 3.4 and 4.7 by : Marvin Kussoy
Download or read book Local Pressure Distribution on a Blunt Delta Wing for Angles of Attack Up to 35 Degrees at Mach Numbers of 3.4 and 4.7 written by Marvin Kussoy and published by . This book was released on 1962 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Pressure Measurements on Two 60° Swept Delta Wings with Blunt Leading Edges and Dihedral Angles of 0° and 45° at a Mach Number of 4.95 by : P. Calvin Stainback
Download or read book Pressure Measurements on Two 60° Swept Delta Wings with Blunt Leading Edges and Dihedral Angles of 0° and 45° at a Mach Number of 4.95 written by P. Calvin Stainback and published by . This book was released on 1962 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Heat-transfer Distribution on 700 Swept Slab Delta Wings at a Mach Number of 9.86 and Angles of Attack Up to 900 by : Philip E. Everhart
Download or read book Heat-transfer Distribution on 700 Swept Slab Delta Wings at a Mach Number of 9.86 and Angles of Attack Up to 900 written by Philip E. Everhart and published by . This book was released on 1964 with total page 62 pages. Available in PDF, EPUB and Kindle. Book excerpt: Heat-transfer distributions were obtained on 700 swept slab delta wings with sharp and blunt noses and cylindrical leading edges. The free-stream Reynolds number based on model thickness was 9 x 10(4). Lees' theory for the heat-transfer distribution is shown to be in good agreement with the data obtained on the nose and leading edge. The point of peak heating on the leading edge is in close agreement with the Newtonian stagnation point at all angles of attack. At angles of attack from 40° to 60° cross-flow theory was in excellent agreement with experimental center-line data; however, at other model attitudes the theory differed significantly from experiment. Nose blunting resulted in reduced heating rates over the aft center-line section of the wing at angles of attack less than about 40°.
Book Synopsis The Aerodynamic Characteristics of Several Thick Delta Wings at Mach Numbers to 6 and Angles of Attack 50° by : John B. McDevitt
Download or read book The Aerodynamic Characteristics of Several Thick Delta Wings at Mach Numbers to 6 and Angles of Attack 50° written by John B. McDevitt and published by . This book was released on 1960 with total page 114 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Pressures and Heat Transfer on a 75 ̊swept Delta Wing with Trailing-edge Flap at Mach 6 and Angles of Attack to 90 by : J. Wayne Keyes
Download or read book Pressures and Heat Transfer on a 75 ̊swept Delta Wing with Trailing-edge Flap at Mach 6 and Angles of Attack to 90 written by J. Wayne Keyes and published by . This book was released on 1969 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: Pressure and heat transfer on swept delta wing with trailing-edge flap.
Book Synopsis In-flight Wing Pressure Distributions for the NASA F/A-18A High Alpha Research Vehicle by : Mark C. Davis
Download or read book In-flight Wing Pressure Distributions for the NASA F/A-18A High Alpha Research Vehicle written by Mark C. Davis and published by . This book was released on 2000 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt: Pressure distributions on the wings of the F/A-18A High Alpha Research Vehicle (HARV) were obtained using both flush-mounted pressure orifices and surface-mounted pressure tubing. During quasi-stabilized 1-g flight, data were gathered at ranges for angle of attack from 5 to 70 degrees, for angle of sideslip from -12 to +12 degrees, and for Mach from 0.23 to 0.64, at various engine settings, and with and without the leading edge extension fence installed. Angle of attack strongly influenced the wing pressure distribution, as demonstrated by a distinct flow separation pattern that occurred between the range from 15 to 30 degrees. Influence was seen on the outboard portion of the wing. Angle-of-sideslip influence on wing pressure distribution was strongest at low angle of attack. Influence of Mach number was observed in the regions of local supersonic flow, diminshing as angle of attack was increased. Engine throttle setting had little influence on the wing pressure distribution.
Book Synopsis Experimental Surface Pressure Data Obtained on 65 ̊delta Wing Across Reynolds Number and Mach Number Ranges by : Julio Chu
Download or read book Experimental Surface Pressure Data Obtained on 65 ̊delta Wing Across Reynolds Number and Mach Number Ranges written by Julio Chu and published by . This book was released on 1996 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Heat-transfer and Pressure Distributions on 60 ̊and 70 ̊swept Delta Wings Having Turbulent Boundary Layers by : William M. Murray (Jr.)
Download or read book Heat-transfer and Pressure Distributions on 60 ̊and 70 ̊swept Delta Wings Having Turbulent Boundary Layers written by William M. Murray (Jr.) and published by . This book was released on 1966 with total page 82 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Experimental Study of the Pressure and Heat-transfer Distribution on a 70° Sweep Slab Delta Wing in Hypersonic Flow by : Mitchel H. Bertram
Download or read book An Experimental Study of the Pressure and Heat-transfer Distribution on a 70° Sweep Slab Delta Wing in Hypersonic Flow written by Mitchel H. Bertram and published by . This book was released on 1963 with total page 136 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results are presented for a study of the pressure and heat-transfer distributions and force characteristics of slab delta wings of 70° sweep at Mach numbers of 6.8 and 9.6 in air and 18 in helium. The wings had cylindrical leading edges and were tested with two different noses. One was sharp in plan view and the other was a tangent sphere with the same diameter as the cylindrical leading edge. Simple approaches to predicting the heat transfer are shown to be successful if the flow pattern peculiar to the angle-of-attack range under consideration is taken into account.
Book Synopsis Aerodynamic Characteristics of a Delta Wing with Leading Edge Swept Back 45 Degrees, Aspect Ratio 4, and NACA 65A006 Airfoil Section by : William C. Sleeman
Download or read book Aerodynamic Characteristics of a Delta Wing with Leading Edge Swept Back 45 Degrees, Aspect Ratio 4, and NACA 65A006 Airfoil Section written by William C. Sleeman and published by . This book was released on 1949 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: This paper presents the results of the investigation of wing-alone and wing-fuselage combination employing a delta wing having 45 degree sweepback of the leading edge, aspect ratio 4, and an NACA 65A006 airfoil section. Lift, drag, pitching moment, and root bending moment were obtained for these configurations. In addition, effective downwash angles and dynamic-pressure characteristics in the region of a probable tail location also were obtained for these configurations, and are presented for a range of tail heights at one tail length. In order to expedite publishing of these data, only a brief analysis is included.
Book Synopsis A Note on the Drag Due to Lift of Delta Wings at Mach Numbers Up to 2.0 by : Robert S. Osborne
Download or read book A Note on the Drag Due to Lift of Delta Wings at Mach Numbers Up to 2.0 written by Robert S. Osborne and published by . This book was released on 1953 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Comprehensive Dissertation Index, 1861-1972: Engineering: general and aeronautical by : Xerox University Microfilms
Download or read book Comprehensive Dissertation Index, 1861-1972: Engineering: general and aeronautical written by Xerox University Microfilms and published by . This book was released on 1973 with total page 906 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Static Pressure on Sharp and Blunt Cones in Conical and Parallel Low-density Flow by : Max Kinslow
Download or read book Static Pressure on Sharp and Blunt Cones in Conical and Parallel Low-density Flow written by Max Kinslow and published by . This book was released on 1974 with total page 78 pages. Available in PDF, EPUB and Kindle. Book excerpt: The static pressure distribution on sharp and blunt 10-deg half-angle cones was measured under rarefied conditions in both a uniform and a source flow field. Angle of attack of the cones was varied up to 10 deg. Pressure distributions are presented for cold-wall conditions at 18.0 = or
Book Synopsis Effects of Compressibility on the Maximum Lift Characteristics and Spanwise Load Distribution of a 12-foot-span Fighter-type Wing of NACA 230-series Airfoil Sections by : E. O. Pearson
Download or read book Effects of Compressibility on the Maximum Lift Characteristics and Spanwise Load Distribution of a 12-foot-span Fighter-type Wing of NACA 230-series Airfoil Sections written by E. O. Pearson and published by . This book was released on 1945 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt: Force and pressure-distribution measurements were made on a fighter-type wing model of conventional NACA 230-series airfoil sections in the Langley 16-foot high-speed tunnel to determine the effects of compressibility on the maximum lift characteristics and the span-wise load distribution. The range of angle of attack investigated was from -10 to +24 degrees. The Mach range of from 0.20 to 0.70 at small and medium angles of attack and from 0.15 to 0.625 at very large angles of attack. Maximum lift coefficient increased up to a Mach number of 0.3, decreased rapidly to a Mach number of 0.55, and then decreased moderately. At high speeds, maximum lift coefficient was reached at from 10 to 12 degrees beyond the stalling angle. In high-speed stalls, resultant load underwent a moderate shift outward.
Book Synopsis Pressure Measurement at Mach 19 for a Winged Re-entry Configuration by : Stavros A. Hartofilis
Download or read book Pressure Measurement at Mach 19 for a Winged Re-entry Configuration written by Stavros A. Hartofilis and published by . This book was released on 1963 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effects of Rounding Corners and Leading Edges on the Windward-surface Pressures of a Delta Wing Swept 650 at a Mach Number of 5.96 at Angles of Attack from 650 to 1150 and Angles of Roll from O0 to 250 at 900 Angle of Attack by : Theodore J. Goldberg
Download or read book Effects of Rounding Corners and Leading Edges on the Windward-surface Pressures of a Delta Wing Swept 650 at a Mach Number of 5.96 at Angles of Attack from 650 to 1150 and Angles of Roll from O0 to 250 at 900 Angle of Attack written by Theodore J. Goldberg and published by . This book was released on 1963 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt:
