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Heat Transfer Measurements In Free Flight At Mach Numbers Up To 146 On A Flat Faced Conical Nose With A Total Angle Of 29c
Download Heat Transfer Measurements In Free Flight At Mach Numbers Up To 146 On A Flat Faced Conical Nose With A Total Angle Of 29c full books in PDF, epub, and Kindle. Read online Heat Transfer Measurements In Free Flight At Mach Numbers Up To 146 On A Flat Faced Conical Nose With A Total Angle Of 29c ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis Heat-transfer Measurements in Free Flight at Mach Numbers Up to 14.6 on a Flat-faced Conical Nose with a Total Angle of 29 Degrees by : Charles B. Rumsey
Download or read book Heat-transfer Measurements in Free Flight at Mach Numbers Up to 14.6 on a Flat-faced Conical Nose with a Total Angle of 29 Degrees written by Charles B. Rumsey and published by . This book was released on 1958 with total page 43 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Measurements of Aerodynamic Heat Transfer and Boundary-layer Transition on a 10° Cone in Free Flight at Supersonic Mach Numbers Up to 5.9 by : Charles B. Rumsey
Download or read book Measurements of Aerodynamic Heat Transfer and Boundary-layer Transition on a 10° Cone in Free Flight at Supersonic Mach Numbers Up to 5.9 written by Charles B. Rumsey and published by . This book was released on 1956 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstract: Aerodynamic heat-transfer measurements were at six stations on the 40-inch-long 10° total-angle conical nose of a rocket-propelled model which was flight tested at Mach numbers up to 5.9. The range of local Reynolds number was from 6.6 x 106 to 55.2 x 106. Laminar, transitional, and turbulent heat-transfer coefficients were measured, and, in general, the laminar and turbulent measurements were in good agreement with theory for cones. Experimental transition Reynolds numbers varied from less than 8.5 x 106 to 19.4 x 106. At a relatively constant ratio of wall temperature to local static temperature near 1.2, the transition Reynolds number increased from 9.2 x 106 to 19.4 x 106 as Mach number increased from 1.57 to 3.38. At Mach numbers near 3.7, the transition Reynolds number decreased as the skin temperature increased toward adiabatic wall temperatures.
Book Synopsis Free-flight Measurements of Aerodynamic Heat Transfer to Mach Number 3.9 and of Drag to Mach Number 6.9 of a Fin-stabilized Cone-cylinder Configuration by : Charles B. Rumsey
Download or read book Free-flight Measurements of Aerodynamic Heat Transfer to Mach Number 3.9 and of Drag to Mach Number 6.9 of a Fin-stabilized Cone-cylinder Configuration written by Charles B. Rumsey and published by . This book was released on 1955 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: Aerodynamic-heat-transfer measurements have been made at a station on the 10 degree total angle conical nose of a rocket-propelled model at flight Mach numbers of 1.4 to 3.9. The corresponding values of local Reynolds number varied from 18,000,000 to 46,000,000 and the ratio of skin temperature to local static temperature varied from 1.2 to 2.4. The experimental data, reduced to Stanton number, were in fair agreement with values predicted by Van Driest's theory for heat transfer on a cone with turbulent flow from the nose tip.
Book Synopsis Additional Heat Transfer Measurements Obtained in Free Flight on a Hemispherical Concave Nose at Mach Numbers Up to 7.1 by : Jack Levine
Download or read book Additional Heat Transfer Measurements Obtained in Free Flight on a Hemispherical Concave Nose at Mach Numbers Up to 7.1 written by Jack Levine and published by . This book was released on 1961 with total page 54 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Free-flight Skin-temperature and Surface-pressure Measurements on a Highly Polished Nose Having a 1000 Total-angle Cone and a 100 Half-angle Conical Flare Section Up to a Mach Number of 4.08 by : Bernard Rashis
Download or read book Free-flight Skin-temperature and Surface-pressure Measurements on a Highly Polished Nose Having a 1000 Total-angle Cone and a 100 Half-angle Conical Flare Section Up to a Mach Number of 4.08 written by Bernard Rashis and published by . This book was released on 1961 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Measurements of Aerodynamic Heat Transfer on a 15 Degree Cone-cylinder-flare Configuration in Free Flight at Mach Numbers Up to 4.7 by : Charles R. Rumsey
Download or read book Measurements of Aerodynamic Heat Transfer on a 15 Degree Cone-cylinder-flare Configuration in Free Flight at Mach Numbers Up to 4.7 written by Charles R. Rumsey and published by . This book was released on 1961 with total page 66 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Measurements of Aerodynamic Heat Transfer and Boundary-layer Transition on a 10 Degree Cone in Free Flight at Supersonic Mach Numbers Up to 5.9 by : Charles B. Rumsey
Download or read book Measurements of Aerodynamic Heat Transfer and Boundary-layer Transition on a 10 Degree Cone in Free Flight at Supersonic Mach Numbers Up to 5.9 written by Charles B. Rumsey and published by . This book was released on 1961 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Measurements of Aerodynamic Heat Transfer and Boundary-Layer Transition on a 10 Deg Cone in Free Flight at Supersonic Mach Numbers Up to 5.9 by : Charles B. Rumsey
Download or read book Measurements of Aerodynamic Heat Transfer and Boundary-Layer Transition on a 10 Deg Cone in Free Flight at Supersonic Mach Numbers Up to 5.9 written by Charles B. Rumsey and published by . This book was released on 1961 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Free Flight Measurements of Heat Transfer to a Simulated Winged Cone Glide Vehicle at Angles of Attack and at Mach Numbers from 10 to 14.3 by : James R. Hall
Download or read book Free Flight Measurements of Heat Transfer to a Simulated Winged Cone Glide Vehicle at Angles of Attack and at Mach Numbers from 10 to 14.3 written by James R. Hall and published by . This book was released on 1961 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Heat-transfer and Pressure Measurements on a Concove-nose Cylinder for a Mach Number Range of 2.49 to 4.44 by : Stallings, Jr. (Robert L.)
Download or read book Heat-transfer and Pressure Measurements on a Concove-nose Cylinder for a Mach Number Range of 2.49 to 4.44 written by Stallings, Jr. (Robert L.) and published by . This book was released on 1959 with total page 21 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Heat-transfer and Pressure Measurements on a Concave-nose Cylinder for Mach Number Range of 2.49 to 4.44 by :
Download or read book Heat-transfer and Pressure Measurements on a Concave-nose Cylinder for Mach Number Range of 2.49 to 4.44 written by and published by . This book was released on 1959 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerodynamic Heating and Boundary-layer Transition on a 1/10-power Nose Shape in Free Flight at Mach Numbers Up to 6.7 and Free-stream Reynolds Numbers Up to 16 X 10(6) by : Benjamine J. Garland
Download or read book Aerodynamic Heating and Boundary-layer Transition on a 1/10-power Nose Shape in Free Flight at Mach Numbers Up to 6.7 and Free-stream Reynolds Numbers Up to 16 X 10(6) written by Benjamine J. Garland and published by . This book was released on 1962 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Measurements of Aerodynamic Heat Transfer on a 15 Deg Cone-cylinder-flare Configuration in Free Flight at Mach Numbers Up to 4.7 by : CHARLES B. RUMSEY
Download or read book Measurements of Aerodynamic Heat Transfer on a 15 Deg Cone-cylinder-flare Configuration in Free Flight at Mach Numbers Up to 4.7 written by CHARLES B. RUMSEY and published by . This book was released on 1961 with total page 1 pages. Available in PDF, EPUB and Kindle. Book excerpt: Measurements of aerodynamic heat transfer were made at a number of stations along a cone-cylinder-flare model having a 15 degrees total-angle conical nose and a 10 degrees half-angle flare skirt. The maximum Mach number was 4.7, and local Reynolds numbers based on body length to a measurement station varied from 2 x 10 to the 6th power to 138 x 10 to the 6th power. Local Stanton numbers measured on the nose cone and flare showed fair agreement with laminar and turbulent theories, while the measurements on the cylinder were generally somewhat lower than theory. Experimental recovery factors, determined twice during the test, were unaccountably lower than theoretical values. Local transition Reynolds numbers, based on length from the nose tip, varied from 3 x 10 to the 6th power to 18 x 10 to the 6th power and were much lower than values previously obtained on the smoother nose of a similar model. At an angle of attack of about 9 degrees, the heat transfer on the flare increased to more than twie the theoretical turbulent value for zero angle of attack. (Author).
Book Synopsis Pressure and Heat-transfer Measurements on the Flat Face of a Blunted 10 ̊half-cone Body (semidisk) at a Mach Number of 6.15 by : P. Calvin Stainback
Download or read book Pressure and Heat-transfer Measurements on the Flat Face of a Blunted 10 ̊half-cone Body (semidisk) at a Mach Number of 6.15 written by P. Calvin Stainback and published by . This book was released on 1963 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Heat-transfer Measurements on a Flat Plate and Attached Fins at Mach Numbers of 3.51 and 4.44 by : Earl A. Price
Download or read book Heat-transfer Measurements on a Flat Plate and Attached Fins at Mach Numbers of 3.51 and 4.44 written by Earl A. Price and published by . This book was released on 1964 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Measurements of Aerodynamic Heat Transfer and Boundary-layer Transition on a 15 Degree Cone in Free Flight at Supersonic Mach Numbers Up to 5.2 by : Charles B. Rumsey
Download or read book Measurements of Aerodynamic Heat Transfer and Boundary-layer Transition on a 15 Degree Cone in Free Flight at Supersonic Mach Numbers Up to 5.2 written by Charles B. Rumsey and published by . This book was released on 1961 with total page 43 pages. Available in PDF, EPUB and Kindle. Book excerpt: Measurements of aerodynamic heat transfer have been made at several stations on the 15 degree total-angle conical nose of a rocket-propelled model in free flight at Mach numbers up to 5.2. Data are presented for a range of local Mach number just outside the boundary layer from 1.40 to 4.65 and a range of local Reynolds number from 3.8 times 10 to the 6th power to 46.5 times 10 to the 6th power, based on length from the nose tip to a measurement station. Laminar, transitional, and turbulent heat-transfer coefficients were measured. The laminar data were in agreement with laminar theory for cones, and the turbulent data agreed well with turbulent theory for cones using Reynolds number based on length from the nose tip. (Author).
