The main data from a cruise flight is compiled in Table 2, with D and L the drag and lift forces. To simplify the calculations, use these properties for air: R = 287 m²/s²K; Cp = 1005 m²/s²K; k = 1.4 CD= 0.02439 0.508 360 m² CLPUTATE = A C Table 2 Cruise flight at 11000m Data Patm Tatm Hatm M cruise. 6 m 22700 Pa 223.15 K 1.4562 x 10-5 Pa-s 0.85 Drag coefficient Lift coefficient Wing surface Average wing chord Atmospheric pressure Air temperature Air viscosity Mach's number 1. Calculate the speed U of the airplane at its cruising altitude (11000m). 2. Calculate the Reynolds number of the airplane at its cruising altitude, based on the average chord of the wing and the speed of movement of the vehicle. 3. Calculate the total thrust exerted by the engines to move the plane to its altitude of

The main data from a cruise flight is compiled in Table 2, with D and L the drag and lift forces. To simplify the calculations, use these properties for air: R = 287 m²/s²K; Cp = 1005 m²/s²K; k = 1.4 CD= 0.02439 0.508 360 m² CLPUTATE = A C Table 2 Cruise flight at 11000m Data Patm Tatm Hatm M cruise. 6 m 22700 Pa 223.15 K 1.4562 x 10-5 Pa-s 0.85 Drag coefficient Lift coefficient Wing surface Average wing chord Atmospheric pressure Air temperature Air viscosity Mach's number 1. Calculate the speed U of the airplane at its cruising altitude (11000m). 2. Calculate the Reynolds number of the airplane at its cruising altitude, based on the average chord of the wing and the speed of movement of the vehicle. 3. Calculate the total thrust exerted by the engines to move the plane to its altitude of

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

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