HOME WORK 1 CONSIDER TEST FLY FOR AIRPLANE FLYING AT DIFFERENT ALTITUDES SUCH AS 5,625 M,...

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HOME WORK 1 CONSIDER TEST FLY FOR AIRPLANE FLYING AT DIFFERENT ALTITUDES SUCH AS 5,625 M, 13,490 M, and 22,300M) FROM THE SEE LEVEL. CALCULATE THE FOLOWING PARAMETERS: 1. TEMEPRATURE, PRESSUER, DENSITY, COEFFICIENT OF VISCOSITY, KINEMATIC VISCOSITY, PRESSURE RATIO AND SENSITY RATIO. 2. ASSUME THE AIRPLANE VELOCITY (V= 200 M/S), THE LENGTH OF THE AERODYMANIC CHORD (C= 2.5 M) OF THE WING. CALCULATE THE REYNOLD'S NUMBER (Re) OF THE FLOW STREAM OVER THE WING. HOME WORK 1 CONSIDER TEST FLY FOR AIRPLANE FLYING AT DIFFERENT ALTITUDES SUCH AS 5,625 M, 13,490 M, and 22,300M) FROM THE SEE LEVEL. CALCULATE THE FOLOWING PARAMETERS: 1. TEMEPRATURE, PRESSUER, DENSITY, COEFFICIENT OF VISCOSITY, KINEMATIC VISCOSITY, PRESSURE RATIO AND SENSITY RATIO. 2. ASSUME THE AIRPLANE VELOCITY (V= 200 M/S), THE LENGTH OF THE AERODYMANIC CHORD (C= 2.5 M) OF THE WING. CALCULATE THE REYNOLD'S NUMBER (Re) OF THE FLOW STREAM OVER THE WING.

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Test fly 1 5625m Troposphere 011kon For Troposphere Soin Leepse rate 7 dt 4... View the full answer