You see what I see across many planes is...
Laminar Wings offers less lift but produce less drag and have lower CL_Max 1.28-1.32
Elliptical Wings provide lift but are efficient in producing low drag for lift ratio. CL-Max is roughly 1.36
Normal Wings usually have about 1.4-1.5 CL_Max.
——————
Now... P-51D has laminar wings, This is why it's so aerodynamic and achieving 604km/h at Sea level with only 1630 horsepower whilst having 21.65m2 wing area.
However I was caught off guard with this...
A guy showed me this claiming P-51D's laminar wings had 1.49 CL_Max which I instantly was skeptical about. If they produce that much lift they would also give a lot of drag and 21.65m2 isn't example small wing area. Then achieving 604km/h at SL with only 1630 horse power is quiet the achievement as it is.
Then he posted from P-51D manual the stall speed which is 102mph (164km/h) at 9700lb weight (4400kg)
Lift Force (Newton's) = 4400kg x 9.81 (Gravity)
-
Air Density at Sea Level = 1.225kg/m3
-
Velocity = 164km/h (stall)
-
Wing Area = 21.65m2
This however gives me CL_Max of 1.57 which makes no sense bevause it's far too high and yet I feel it's not high enough to be with flaps deployed.
Laminar Wings offers less lift but produce less drag and have lower CL_Max 1.28-1.32
Elliptical Wings provide lift but are efficient in producing low drag for lift ratio. CL-Max is roughly 1.36
Normal Wings usually have about 1.4-1.5 CL_Max.
——————
Now... P-51D has laminar wings, This is why it's so aerodynamic and achieving 604km/h at Sea level with only 1630 horsepower whilst having 21.65m2 wing area.
However I was caught off guard with this...
A guy showed me this claiming P-51D's laminar wings had 1.49 CL_Max which I instantly was skeptical about. If they produce that much lift they would also give a lot of drag and 21.65m2 isn't example small wing area. Then achieving 604km/h at SL with only 1630 horse power is quiet the achievement as it is.
Then he posted from P-51D manual the stall speed which is 102mph (164km/h) at 9700lb weight (4400kg)
Lift Force (Newton's) = 4400kg x 9.81 (Gravity)
-
Air Density at Sea Level = 1.225kg/m3
-
Velocity = 164km/h (stall)
-
Wing Area = 21.65m2
This however gives me CL_Max of 1.57 which makes no sense bevause it's far too high and yet I feel it's not high enough to be with flaps deployed.