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5:54 LTE X Fundamentals of Ae... Fundamentals of Aerodynamics Effect of Mach Number and Altitude on Calibrated Airspeed Activity No.1 Effect of Mach Number and Altitude on Calibrated Airspeed Members Date Submitted Instructor Rating Explanation of Table Column No. 0.286 213.5 · √5 [(* {[1 + 0.2 (4) ²²¹³ - 1} + 1) *** - 1] 661.5) Where: M Mach Number Vc = Calibrated Airspeed in Knots = ICAO Standard Atmosphere Pressure Ratio (6), Above Sea level up to tropopause Po 6 = 2 = (1 + h) 5.26 a = -0.003566 R/ft To=519R h = Any altitude above sea level up to tropopause in ft Pressure Ratio (6), Above Sea level up to tropopause P 1.26 8= Po e4.805x10-5h Where: h = Any altitude above tropopause up to stratopause in ft 1) V₁= Given 2) M= Where: o
er, M h = Any altitude above tropopause up to stratopause in ft Pressure Ratio, 6 Altitude, h ft Sea Level 1.000 5000 P 10000 8-=(1+)526 15000 Po To 20000 25000 30000 35000 40000 45000 P 1.26 8 = 50000 55000 Po e4.805x10-5h 60000 65000 70000 75000 80000 123 4 5 6 7 8 9 10 11 Sea Level 5000 10000 15000 20000 25000 30000 35000 40000 45000 M M M M M M M Ve M M M Knots 100 150 200 250 300 350 400 450 500 550 600 650 3.5 √5[(² {[¹ + 0.2 (~7³¹³ - 1} + 1) 0.286 - 1 1 661.5A 12 19 13 14 15 16 17 18 50000 55000 60000 65000 70000 75000 80000 Knots Ve M M M M M M M 100 650 3.5 0.286 + 0.2 (VE) ²] 5 -1} + 1)² 1.4 1.2 1 08 M = M = FIGL 16 =
Mach Number, M 1.4 1.2 1 0.8 0.6 0.4 0.2 0 25000 30000 35000 40000 45000 50000 55000 60000 65000 70000 75000 80000 0 P 1.26 Po e4.805x10-5h 1 2 3 6 7 8 9 10 11 4 5 10000 15000 20000 25000 30000 35000 40000 45000 Sea Level 5000 Ve M M Knots M M M M M M M M 100 150 200 250 300 350 400 450 500 550 600 650 0.286 3.5 √5 [(² {[¹ + 0.2² ( ² ¹ ³ - 1} + 1) ²² VE 1 661.5/ 12 14 15 16 18 19 13 50000 55000 60000 17 70000 75000 80000 65000 Knots Ve M M M M M M M 100 650 0.286 3.5 √5[(* {[1 + 0.2² (~*²³5 – ¹1} + 1) 0² – 1] - 661.5A 5 6 Calibrated Airspeed, Vc M = M = 1 2 8 - = 7