Download or read book Investigation of 75 millimeter bore Cylindrical roller Bearings at High Speeds written by E. Fred Macks and published by . This book was released on 1951 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt: Oil inlet distribution (5 methods were investigated) and oil inlet temperature (100 to 205 degrees F) were found to be significant factors in the cooling effectiveness of a given quantity of oil. Dimensional analysis was used to generalize the test-rig results so that it is possible to predict the inner- or outer-race temperatures above the oil inlet temperature from a single curve regardlesss of whether speed, load, oil flow, oil inlet temperature, oil-jet diameter or any combination of the parameters is varied.

Download or read book A Selected Listing of NASA Scientific and Technical Reports for written by and published by . This book was released on 1949 with total page 750 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Index of NACA Technical Publications written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1956 with total page 306 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Correlation of Physical Properties with Molecular Structure for Some Dicyclic Hydrocarbons Having High Thermal energy Release Per Unit Volume 2 Alkylbiphenyl and the Two Isomeric 2 Alkybicyclohexyl Series written by Aaron S. Boksenbom and published by . This book was released on 1952 with total page 226 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Technical Note National Advisory Committee for Aeronautics written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1956 with total page 974 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Report National Advisory Committee for Aeronautics written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1952 with total page 1208 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Comparison of High speed Operating Characteristics of Size 215 Cylindrical roller Bearings as Determined in Turbojet Engine and in Laboratory Test Rig written by Arthur W. Goldstein and published by . This book was released on 1952 with total page 236 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Annual Report National Advisory Committee for Aeronautics written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1957 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.

Download or read book Technical Note written by and published by . This book was released on 1951 with total page 474 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Report written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1954 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Research Memorandum written by and published by . This book was released on 1953 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book NACA Research Memorandum written by and published by . This book was released on 1953 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Gust tunnel Investigation of a Wing Model with Semichord Line Swept Back 60 Degrees written by Harold B. Pierce and published by . This book was released on 1950 with total page 688 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was made in the Langley gust tunnel of a 60 degree sweptback-wing model to determine its response to gusts. On the basis of results, a simplified method of analysis, which uses a slope of the lift curve derived by the cosine law and which uses strip theory to estimate the penetration effect, appears to be applicable for the prediction of gust loads on wings swept as much as 60 degrees.

Download or read book Applied Mechanics Reviews written by and published by . This book was released on 1948 with total page 630 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Linearized Supersonic Axially Symmetric Flow about Open nosed Bodies Obtained by Use of Stream Function written by Franklin Moore and published by . This book was released on 1950 with total page 756 pages. Available in PDF, EPUB and Kindle. Book excerpt: First-order relations were obtained for attenuation of shock and flow deflection outward along the shock. These relations probably conform closely to physical fact, provided the entrance slope is small. These relations contain an error, but become exact as the radial coordinate approaches inifinity. The error is thus probably of the second order over the entire shock front.

Download or read book Comparison of Performance of Experimental and Conventional Cage Designs and Materials for 75 millimeter bore Cylindrical Roller Bearings at High Speeds written by Donald R. Riley and published by . This book was released on 1954 with total page 296 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Studies of the Use of Freon 12 as a Wind tunnel Testing Medium written by Albert E. Von Doenhoff and published by . This book was released on 1953 with total page 668 pages. Available in PDF, EPUB and Kindle. Book excerpt: A number of studies relating to the use of Freon-12 as a substitute medium for air in aerodynamic testing have been made. The use of Freon-12 instead of air makes possible large savings in wind-tunnel drive power. Because of the fact that the ratio of specific heats is approximately 1.13 for Freon-12 as compared with 1.4 for air, some differences exist between data obtained in Freon-12 and air. Methods for predicting aerodynamic characteristics of bodies in air from data obtained in Freon-12, however, have been developed from the concept of similarity of the streamline pattern. These methods, derived from consideration of two-dimensional flows, provide substantial agreement in all cases for which comparative data are available. These data consist of measurements throughout a range of Mach number from approximately 0.4 to 1.2 of pressure distributions and hinge moments on swept and unswept wings having aspect ratios ranging from 4.0 to 9.0, including cases where a substantial part of the wing was stalled.