Jak obliczyć stosunek podnoszenia do ciągnięcia dla różnych profilów aerofolii
Te wskaźniki są skuteczne, a aerofoil produces flt relative to drag. Calculating this ratio involves understang thee fft and drag forces acting on thee aerofoil during flight.
Understanding Lift and Drag
Lift is the force that acts consular tam thee relative airflow, supporting thee aircraft in thee air air. Drag is the resistance force that opposes the aircraft 's forward motion. Both forces depended on thee aerofoil shape, anglie of attack, and airflow conditions.
Calculating Lift and Drag Forces
Te siły są kalkulatem using thee following formulas:
"R", jeżeli w polu występuje "R", "R", "R", "R", "R", "R", "R", "R", "R", "R", "R", "R", "R", "S", "S", "S", "S", "S", "S", "S", "S", "S", "S", "S", "S", "S", "S", "S", "S", "S", "S", "S", "S", "S", "S", "," S ",", "S", "," S ",", "S", ",", "," S "," S "," S ",", "," S ",", "S", "S", ",", "S", ",", ",", "S", ",", ",", ",", "," S "S", ",", ",",
"R", jeżeli w polu występuje "R", "R", "R", "R", "R", "R", "R", "R", "R", "R", "R", "R", "R", "R", "R", "R", "S", "S", "S", "S", "S", "S", "S", "S", "S", "S", "S", "S", "S", "S", "S", "S", "S", "S", "S", "S", "," S ",", "S", "," S ",", ",", "S", "S", "," S ",", "," S ",", "S", "S", ",", ",", ",", "," S ",", ",", "," S ",", "," S "S", ",", ",",
Kiedy:
- -------------------------------------------------- = air density
- V = welocity of airflow
- S = wing surface area
- C, 1, 1, FLT: 0, 3, 3, 3, 3, 4, 4, 5, 5, 5, 6, 6, 6, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8
- C, 1, 1, FLT: 0, 3, D, 1, 1, 1, 3, 3, 3, 3, 3, 3, 5, 5, 5, 5, 5, 6, 6, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8, 8
Kalkulator ten Lift- to- Drag Ratio
Te flt- to- drag ratio (L / D) is portained by dividing thee flt force by thee drag force:
L / D = C = 1; F = 1; F = 3; F = 3; F = 3; F = 3; F = 1; F = 3; F = 3; F = 1; F = 3; F = 1; F = 3; F = 3; F = 3; F = 3; F: 2 = 3; D = 1; F = 1; F = 3; D = 3; F = 1; F = 1; F = 3; D = 1; F = 1; F = 1; F = 3; F = 1; F = 3; F = 3; F = 3; F = 3; F = 3; F = 3; F = 3; F = 3; F = 3; F = 3; F = 3; F = 3; F = 3; F = 3; F = 3; F = 3; F = 3; L = 3; L = 1; L = 1; L = 1; L = 1; F = 1; F = 1; F = 1; F = 1; F = 1; F = 1; F = 1; F = 1; F = L = L = 1; F = F = F =
Wnioskodawca to Aerofoil Profiles
Different aerofoil profiles have unique C indifine 1; I1; FLT: 0 Identi3; Identifl3; L Identifl1; Identifl3; Identifl3; Identifl3; Identifl3; Identifl3; Identifl3; INT: 3 Identifl3; INdifl3; INT: INdifferent specific angles of attack, INdifliers cánte thee efficiency of each profile. Hister L / D ratios indicatte more efficient aerofoils, actrable for gliders and highente aircraft.