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With over 60 flaps to lift, this colourful book gently introduces important concepts such as size, comparisons and measuring. Young children can spot a slow tortoise and a fast leopard, compare the size of two boats, see which child is the tallest, and much more. A fun introduction to a key early learning topic.
An interactive way for preschool children to learn about differences in sizes and how to measure those differences. With lots to spot and talk about, this is a brilliant book for sharing, encourages vital pre-math skills, and helps them develop their visual discrimination
A lively and dynamic introduction to an important, though sometimes difficult, subject to tackle. Learn how to measure time, speed, length, temperature, mass and more in this entertaining information book, with over 150 flaps to lift. Includes a 25cm pop-out ruler to help answer the measuring questions and puzzles. Illustrations: Full colour throughout
An investigation has been conducted in the Langley full-scale tunnel on a large-scale model powered by turbojet engines with flattened rectangular nozzles. The wing had 35° sweep of the leading edge, an aspect ratio of 6.5, a taper ratio of 0.31, and NACA 65(1)-412 and 65-408 airfoils at the root and tip. The investigation included measurements of the longitudinal aerodynamic characteristics of the model with half-span and full-span flaps and measurements of the sound pressure and skin temperature on the portions of the lower surface of the wing immersed in the jet flow. The tests were conducted over a range or angles of attack from -8° to 16° for Reynolds numbers from 1.8 x 106 to 4.4 x 106 and a range of momentum coefficients from 0 to 2.0. In general, the aerodynamic results of this investigation made with a large-scale hot-jet model verified the results of previous investigations with small models powered by compressed-air jets. Although blowing was only done over the inboard portion of the wing, substantial amounts of induced lift were also obtained over the outboard portion of the wing. Skin temperatures were about 340° F and wing heating could be handled with available materials without cooling. Random acoustic loadings on the wing surface were high enough to indicate that fatigue failure from this source would require special consideration in the design of an external-flow jet flap system for an airplane.
A preliminary investigation has been made of the pressure distribution about the mean-radius section of the rotating blades of a single-stage axial-flow compressor at a blade Mach number of 0.35. A 24-cell pressure-transfer device used in obtaining the pressure data is described and the accuracy of these data is established by several independent methods.
Equations are derived to evaluate the effects of thermal vibration relaxation and specific-heat changes on pneumatic-probe pyrometer measurements in the region 1000 to 3000 degrees K and 0.3
