Question

Givens (Questions 1

Answer 1

V (KTAS)	q (psf)	CL	CD	CL / CD	DP (lb)	DI (lb)	DT (lb)
VS 150.64	76.92	1,3	0,09	14,44	153,84	538,44	692,28
160	86,96	1,15	75*10^-3	15,33	173,92	478,28	652,2
180	109,89	0,91	42*10^-3	21,67	219,78	241,76	461,54
200	135,14	0,74	42*10^-3	17,62	270,28	297,31	567,59
205	142,85	0,7	40*10^-3	17,5	285,7	285,7	571,4
210	149,25	0,67	39*10^-3	17,18	298,5	283,57	582,07
220	163,93	0,61	35*10^-3	17,43	327,86	245,89	573,75
240	196,08	0,51	31*10^-3	16,45	392,16	215,69	607,85
260	227,27	0,44	28*10^-3	15,71	454,54	181,82	636,36
280	263,15	0,38	26*10^-3	14,61	526,3	157,89	684,19
300	303,03	0,33	24,5*10^-3	13,47	606,06	136,36	742,42

Equations for Table:

q =              

C_L =      

C_D = C_DP + [1/ (e AR)] C_L²            

Dp = C_Dp q S

Di = Dt - Dp = C_Di q S = [1/ (e AR)] C_L² q S                                              

Dt = Di + Dp = C_D q S

1.      Determine V_STALL        (Stall speed in KTAS)

Vstall = 150,64 KTAS

2.      Determine D_MIN              (Minimum drag in pounds)

Dmin = 461,54 lb

3.      Determine V_DMIN         (Minimum drag speed in KTAS)

Vdmin = 180 KTAS

4.      Determine the parasitic drag at D_MIN (pounds)

      DP min =219.78 lb

5.      Determine the induced drag at D_MIN (pounds)

Dimin = 241.76 lb

_6.        Find Glide Ratio at V_DMIN

_{Glide Ratio = Cl/Cd = 21.67}