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:
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 39 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Pressure Distributions on Blunt Delta Wings at a Mach Number of 2 91 and Angles of Attack Up to 90 Deg written by and published by . This book was released on 1962 with total page 120 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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:
Download or read book Pressure Distributions on Blunt Delta Wings at Angles of Attack Up to 90 and Mach Number of 6 85 written by Peter T. Bernot and published by . This book was released on 1963 with total page 39 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Pressure Distributions on Blunt Delta Wings at a Mach Number of 2 91 and Angles of Attack Up to 90 written by James N. Mueller and published by . This book was released on 1962 with total page 114 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Pressure Distributions on a Flat plate Delta Wing Swept 65 Deg at a Mach Number of 5 97 at Angles of Attack from 65 Deg to 115 Deg and Angles of Roll from 0 Deg to 25 Deg at a 90 Deg Angle of Attack written by and published by . This book was released on 1962 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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:
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 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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.
Download or read book Pressure Measurements on Two 60 Degree Swept Delta Wings with Blunt Leading Edges and Dihedral Angles of 0 Degree and 45 Degrees at a Mach Number of 4 95 written by P. CALVIN. STAINBACK and published by . This book was released on 1962 with total page 1 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation was conducted to measure the pressures on two 60 degree swept delta wings with cylindrical leading edges of 0.25-inch radii and dihedral angles of 0 and 45 degrees. The tests were conducted at a Mach number of 4.95 and a stagnation temperature of 400 F. The test-section unit Reynolds number was 15.19 x 10 to the 6th power and the angle of attack was varied from 0 to 20 degrees. The results of the investigation indicated that, in general, Newtonian theory would not predict the pressure distri ution on the model in a plane normal to the leading edge for angles of attac greater than zero. A method which utilizes a linear combination of viscous and inviscid pressure terms, developed by Creager for predicting pressures on blunt-leading-e ge delta wing at angles of attac, was in good agreement with the measured pressure distributions. The stagnationline pressure level could be predicted within!9 percent by using the ideal-gas normal-shock relationship with the normal component of the free-stream Mach number. (Author).
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:
Download or read book Experimental Pressure and Heat Transfer Distributions on Blunt nose Delta Wings for Angles of Attack Up to 30 at Mach Number 7 written by R. Douglas Archer and published by . This book was released on 1963 with total page 205 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Heat transfer and Pressure Distributions of a 60 Deg Delta Wing with Dihedral at a Mach Number of 6 and Angles of Attack from 0 Deg to 52 Deg written by and published by . This book was released on 1961 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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°.
Download or read book Surface Pressure Measurements on a Double Delta Wing body Configuration at Mach 2 and Mach 3 WTR 1396 written by Donald W. Ausherman and published by . This book was released on 1992 with total page 190 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Prediction of Centerline Shock layer Thickness and Pressure Distribution on Delta Wing body Configurations written by George E. Kaattari and published by . This book was released on 1971 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:
