Consider the data for the NACA 0012 airfoil at an angle of attack of 8 degrees. First find the low speed section lift coefficient (Appendix B), and estimate the critical Mach number using the NACA Handbook (page number 115 of the handbook, page 117 of the pdf).

G Problem 6. Using the information from Problem 5, determine what the value of the low speed coefficient of pressure is for the NACA 0012 for an 8 degree angle of attack. Do your results correspond to the notion of thick, medium and thin airfoils? Explain this result.

Air is to be cooled in the evaporator section of a refrigerator by passing it over a bank of 0.8-cm-outer-diameter and 0.4-m-long tubes inside which the refrigerant is evaporating at -20°c. air approaches the tube bank in the normal direction at 0°c and 1 atm with a mean velocity of 4 m/s. the tubes are arranged in-line with longitudinal and transverse pitches of sl- st 1.5 cm. there are 30 rows in the flow direction with 15 tubes in each row. determine (a) the refrigeration capacity of this system and (b) pressure drop across the tube bank. evaluate the air properties at an assumed mean temperature of -5°c and 1 atm. is this a good assumption?

Slip occurs via two partial dislocations because of (a) the shorter path of the partial dislocation lines; (b) the lower energy state through partial dislocations; (c) the charge balance.

Hydraulic fluid with a sg. of 0.78 is flowing through a 1.5 in. i.d. pipe at 58 gal/min. the fluid has an absolute viscosity of 11.8 x 105 lbf-sec/ft2. is the flow laminar, turbulent or within the critical range? give both a numerical reynolds number and a term answer.