Aero 212

Question 1

D min

Answer 1

2mg root(ab)

Question 2

Clmd

Answer 2

Root(a/b)

Question 3

Clmp

Answer 3

Root(3a/b)

Question 4

Vmd

Answer 4

Root((2mg/rhoS)root(b/a))

Question 5

Cdmd

Answer 5

2a

Question 6

Cdmp

Answer 6

4a

Question 7

Vmp

Answer 7

root(2mg/RhoSClmp) = 0.76Vmd

Question 8

Pmin

Answer 8

2aRhoS(Vmp)^3

Question 9

Rate of climb, h dot

Answer 9

VSin(gamma)

Question 10

Gamma (flight angle) for jet aircraft

Answer 10

T/mg - Cd/Cl

Question 11

L (climb)

Answer 11

mgCos(gamma)

Question 12

T (climb)

Answer 12

D + mgSin(gamma)

Question 13

Gamma (climb angle) for propellor aircraft

Answer 13

NuProot(rhoSCl/2(mg)^3) - (Cd/Cl)

Question 14

h dot (rate of climb) max (prop)

Answer 14

(NuPshaftmax - Pmin)/mg

Question 15

Turn rate (omega)

Answer 15

V/R

Question 16

Centripetal force, F

Answer 16

LSin(phi) = mV^2/R = mRomega^2 = mVomega

Question 17

Tan(phi)

Answer 17

V^2/Rg

Question 18

Normal load factor, n

Answer 18

Sec(phi)

Question 19

Cl for n-g turn

Answer 19

nmg/0.5rhoV^2S

Question 20

Centripetal acceleration, a

Answer 20

V^2/R = root(n^2 - 1)g

Question 21

Cruise climb range (jet)

Answer 21

(Vmd/gCf)x(1/root(ab))x[(V/Vmd)^3/(1+(V/Vmd)^4)]xLn(w)

Question 22

Cruise climb endurance (jet)

Answer 22

(1/gCf)x(1/root(ab))x[(V/Vmd)^2/(1+(V/Vmd)^4)]xLn(w)

Question 23

w

Answer 23

(M+mf)/M

Question 24

Cl for max rate of climb (jet)

Answer 24

(-(T/mg) + root((T/mg)^2 + 12ab)) / 2b

Question 25

Speed for max rate of climb, Vhmax (jet)

Answer 25

Vhmax = root(2mg/rhoSClhmax)