iCLEAN – Loitering Attack UCAV - aero.com

WIND TUNNEL TEST RESULTSThe results of the wind tunnel were compared with the theoreticalcalculations. The results are displayed in the following graphs:The theoretical results for the whole aircraft are very accurate. The onlybig difference between the results is between the stall angles – the windtunnel stall angle is 18 degrees and the theoretical stall angle is 13.1degrees. This difference can occur because vortexes are created on thetips of the winds in the tunnel and create a smaller effective angle onthe wings.For the comparison between the wind tunnel and the theoretical resultsfor each lift component, the results are not so close:1- For the fuselage, a wrong choice of the 2D slope lift line ( 2 rad)is probably the cause for the difference between the slopes of thegraphs.- For the wing's lift coefficient, the lack of consideration of thebody-wing effects on each other (can enlarge the lift) is probablythe cause for the offset between the graphs.36