Rolling Moment Calculation

[Inseo Choi]

Hi.

I'm trying to calculate the rolling moment coefficient(cl) of the wing when the case of OEI(One Engine Inoperative) case.

The problem is the direction of the rolling moment coefficient, cl.

Fig. 1 shows the case of the OEI.

                                                                     Fig. 1

One propeller is removed.

And Fig. 2 is the results of the integrated value of the section lift coefficient along span-wise and the distribution of the section lift coefficient.

(a) integrated value of the section lift coefficient(A2 > A1)

(b) distribution of the section lift coefficient

                                                                     Fig. 2

And the Fig. 3 is the description of the direction of the rolling moment coefficient that I guessed.

                                                                     Fig. 3

So I guessed the direction of the rolling moment is (+) but the result is not.

 the value of the rolling moment coefficient is negative.

I cannot understand this result.

Is there any other method to calculate the rolling moment coefficient in vspaero ?

Here is the *.vsp file.

Best Regards,

Inseo.