3 The Design Point 5.5 [lbs] Weight 0° Dihedral Angle 110 [ft/sec] Speed Planform area based on approximated (CL)max and weight estimateDihedral angle of 0° taken from RoskamDesign speed decreased from 150 ft/secDesigned to high speed missionWeight5.5 [lbs]Dihedral Angle0°Speed110 [ft/sec]Horizontal Tail Span1.5 [ft]
4 Airfoil Selection: Main Wing Wing SectionNACA 1408Gives approximate 2D Cl needed for dashRelatively thin for minimizing dragThick enough for structural strength
6 Airfoil Selection: Tail Tail SectionsHorizontal StabilizerSymmetric with low Cd over a wider range of a.o.a. compared to other similar airfoilsSymmetric Jones airfoil (≈8% t/c)Vertical StabilizerNACA 0006
19 Flap analysis Ads Use (CL)max approximation from Raymer Use XFOIL to find (Cl)max with flapsObservation -Flapped (Cl)max follows linear trendDetermine maximum achievable (CL)maxFind flap configuration that acheives optimal (CL)max
22 Flap analysis: (continued) Use linear fit lines to find a Δ(Cl)max and then find Δ(CL)max with the following equation from Raymer:adsThe ratio blank is based on the intial sizing of the wing area and tail span and is assumed to remain constant
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