OC 1 Em(Tm/W)s. (3-42a) T 1/2 (Tsu/S) 11/2 (Ts./W)(W/S 1/2 V. Ps. PSL Coo (3-42b) Notice the influence of the wing loa

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Oc 1 Em Tm W S 3 42a T 1 2 Tsu S 11 2 Ts W W S 1 2 V Ps Psl Coo 3 42b Notice The Influence Of The Wing Loa 1 (5.54 KiB) Viewed 48 times

Oc 1 Em Tm W S 3 42a T 1 2 Tsu S 11 2 Ts W W S 1 2 V Ps Psl Coo 3 42b Notice The Influence Of The Wing Loa 2 (10.02 KiB) Viewed 48 times

Oc 1 Em Tm W S 3 42a T 1 2 Tsu S 11 2 Ts W W S 1 2 V Ps Psl Coo 3 42b Notice The Influence Of The Wing Loa 3 (41.96 KiB) Viewed 48 times

OC 1 Em(Tm/W)s. (3-42a)
T 1/2 (Tsu/S) 11/2 (Ts./W)(W/S 1/2 V. Ps. PSL Coo (3-42b) Notice the influence of the wing loading and the zero-lift-drag coefficient. If v= -Coscov)" - Centro - WWW.9) "2 DO
need help with problem 3-5 part A and b 3-5. For Aircraft A: a. Find the maximum absolute ceiling using the approximation of Eq. 3-42a. b. Find the airspeed (mph) and Mach number at this ceiling. If the latter is greater than the drag-rise Mach number, determine the actual ceiling. C. Do (a) above, using the more exact relationship of Eq. 3.41 and com pare with the results of (a). The three aircraft whose major characteristics are given below will be used in many of the problems of this chapter and of the two subsequent chapters. Aircraft A Executive Aircraft B Medium Range Aircraft C Long Range Type Gross weight (lb) Wing area (fº) Maximum thrust (lb) 24,000 600 6.000 Сро 0.02 140.000 2.333 37.800 0.018 0.048 0.8 2.0 600.000 5.128 180.000 0.017 0.042 0.85 2.2 K MOR Chaan 0.056 0.72 1.8