FAR 23 certified multiengine aeroplanes with Wto less than 6000 Lbs must have a stall speed of no more than 61 knots. The power off stall speed maybe determined from part 1, chapter 3, page 90 as:
Vs = {2(W/S)/ρCLmax}½ (answer is in feet / second)
Given the following details from the single engine design are already known; Wing profile NACA 747A415, a highly laminar flow wing with low drag profile but generates poor lift at slow speeds so CLmax (clean) = 1.4 and CLmax (flap) = 1.8 With a Mean Aerodynamic Chord (MAC) = 1300 mm and a proposed increase in span to 9 meters then;
(S) surface area = 120 sq.ft
(W/S) = 16.5 Lbs/sq.ft
| | Sea Level | 5000 ft |
| Stall Clean (Vs) | 59.0 kts | 63.6 kts |
| Stall Flap (Vso) | 52.1 kts | 56.1 kts |
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