An aircraft is to be designed to have max lift coefficient as 2.8 and at q=10Pa. If maximum load factor n=5 then, what will be the stall speed?(a) 1.80m/s(b) 1.80mph(c) 2.80mph(d) 2.80m/sThis question was addressed to me during an interview for a job.I would like to ask this question from Selection of Thrust-Weight and Wing Loading in chapter Thrust-Weight Ratio and Wing Loading of Aircraft Design

An aircraft is to be designed to have max lift coefficient as 2.8 and

1.	An aircraft is to be designed to have max lift coefficient as 2.8 and at q=10Pa. If maximum load factor n=5 then, what will be the stall speed?(a) 1.80m/s(b) 1.80mph(c) 2.80mph(d) 2.80m/sThis question was addressed to me during an interview for a job.I would like to ask this question from Selection of Thrust-Weight and Wing Loading in chapter Thrust-Weight Ratio and Wing Loading of Aircraft Design
Answer» Right option is (a) 1.80m/s The explanation: Given, lift coefficient = 2.8, q=10Pa, n=5 Since DENSITY is not given we will take as sea level. Load factor n = qCL/(W/S) (W/S)/CL = q/n = 10/5 = 2. Now, stall speed V is given by, V = \(\sqrt{2(\FRAC{W}{S})/(\rhoCL)}\) = \(\sqrt{22/1.225}\) = 1.80m/s.

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