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May 15, 2012, 08:08 PM
greg
somerset, nj
Joined Feb 2005
377 Posts
Discussion
aircraft polar model

rough estimate of 2-33 polar
Code:
```function calcCdi (Cl, Ar, k)  {
return k * (Cl^2) / (Pi * Ar)
}

# ------------------------------------------------
function getAirspeed (cl, area, weight)  {
return sqrt(weight / (0.5 * Rho * area * cl))
}

function getCl    (airspeed, area, weight) {
return weight / (0.5 * Rho * area * airspeed^2)
}

# ------------------------------------------------
function getLift  (cl, airspeed, area)  {
return 0.5 * Rho * area * cl * airspeed^2
}

# ------------------------------------------------
function gen (Weight, Area, Ar, Cd, col)  {
v0     = int(getAirspeed(CLmax, Area, Weight))
v1     = int(getAirspeed(CLmin, Area, Weight))
N      = v1 - v0

printf "## airspeed  %8.4f - %8.4f\n", v0, v1

for (n = 0; n <= N; n++)  {
airspeed  [n]  = v0 + n
cl        [n]  = getCl(airspeed [n], Area, Weight)
cdi       [n]  = calcCdi(cl [n], Ar, 1)

induced   [n]  = getLift(cdi [n], airspeed [n], Area)
parasitic [n]  = getLift(Cd,  airspeed [n], Area)

lift      [n]  = getLift(cl [n], airspeed [n], Area)
drag      [n]  = induced [n] + parasitic [n]

Ld        [n]  = lift [n] / drag [n]
sink      [n]  = 4 * airspeed [n] / Ld [n]

airspeed  [n] /= 5280/3600
}
}

# ---------------------------------------------------------
BEGIN  {
Pi     = atan2(0, -1)
Rho    = 0.002378       # slugs / cu.ft.

# general
CLmax  = 1.5
CLmin  = 0.175

# 2-33 parameters
Empty  = 600            # lbs
Cargo  = 300
Weight = Empty + Cargo  # lbs
Span   = 51             # ft
Area   = 220            # sq.ft.
Ar     = 11.85

# estimates
Cd     = 0.007

gen(Weight, Area, Ar, Cd)
}```
a 2nd polar plot is added. It shows polars with weight increases equivalent to
lift increases necessitated by bank angle increases of 15, 30, 45 and 60.

It also shows AOA/Cl corresponding to min-sink speed in each plot.