Aero 212 Flashcards by George Mitchell

Q

D min

A

2mg root(ab)

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Q

Clmd

A

Root(a/b)

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Q

Clmp

A

Root(3a/b)

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Q

Vmd

A

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

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Q

Cdmd

A

2a

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Q

Cdmp

A

4a

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Q

Vmp

A

root(2mg/RhoSClmp) = 0.76Vmd

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Q

Pmin

A

2aRhoS(Vmp)^3

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Q

Rate of climb, h dot

A

VSin(gamma)

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Q

Gamma (flight angle) for jet aircraft

A

T/mg - Cd/Cl

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Q

L (climb)

A

mgCos(gamma)

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Q

T (climb)

A

D + mgSin(gamma)

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Q

Gamma (climb angle) for propellor aircraft

A

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

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Q

h dot (rate of climb) max (prop)

A

(NuPshaftmax - Pmin)/mg

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Q

Turn rate (omega)

A

V/R

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Q

Centripetal force, F

A

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

Q

Tan(phi)

A

V^2/Rg

Q

Normal load factor, n

A

Sec(phi)

Q

Cl for n-g turn

A

nmg/0.5rhoV^2S

Q

Centripetal acceleration, a

A

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

Q

Cruise climb range (jet)

A

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

Q

Cruise climb endurance (jet)

A

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

Q

w

A

(M+mf)/M

Q

Cl for max rate of climb (jet)

A

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

Q

Speed for max rate of climb, Vhmax (jet)

A

Vhmax = root(2mg/rhoSClhmax)