erman152
24th Aug 2011, 12:16
Hi I just need to Calculate the stall speed (no flap) at maximum take off weight of a Cessna 172 also has a span of 36 ft 1 inch and a wing area of 174 ft2. The MTOW for the Cessna 172 is 2,450 lb. Base your initial Reynolds Number calculation on ISA sea level conditions and a nominal flight speed of 70 KTAS. Standard roughness of wing surfaces should be assumed.
I have the formula
V= sqrt ( 2 W n / P S Cl max)
where W = weight 2450lbs
P = air density at sea level
S = wing area 174ft ^2
Cl Max = 1.2 got that from the graph
I just cant work out what I have to do for "n"
I have the formula n= 1 / cos ᵠ
But I dont know how to use it
If someone could help me I would greatly appreciate it :)
I have the formula
V= sqrt ( 2 W n / P S Cl max)
where W = weight 2450lbs
P = air density at sea level
S = wing area 174ft ^2
Cl Max = 1.2 got that from the graph
I just cant work out what I have to do for "n"
I have the formula n= 1 / cos ᵠ
But I dont know how to use it
If someone could help me I would greatly appreciate it :)