FRICTION - Skin Friction and Form Drag Program W.H. Mason, Department of Aerospace and Ocean Engineering Virginia Tech, Blacksburg, VA 24061 email:whmason@vt.edu version: Jan. 28, 2006 CASE TITLE: F - 15 AIRCRAFT SREF = 608.00000 MODEL SCALE = 1.000 NO. OF COMPONENTS = 7 input mode = 0 (mode=0: input M,h; mode=1: input M, Re/L) COMPONENT TITLE SWET (FT2) REFL(FT) TC ICODE FRM FCTR FTRANS FUSELAGE 550.0000 54.650 0.055 1 1.0205 0.0000 CANOPY 75.0000 15.000 0.120 1 1.0744 0.0000 NACELLE 600.0000 35.000 0.040 1 1.0124 0.0000 GLV/SPONSON 305.0000 35.500 0.117 1 1.0712 0.0000 OUTB'D WING 698.0000 12.700 0.050 0 1.1356 0.0000 HORIZ. TAIL 222.0000 8.300 0.050 0 1.1356 0.0000 TWIN V. T. 250.0000 6.700 0.045 0 1.1219 0.0000 TOTAL SWET = 2700.0000 REYNOLDS NO./FT =0.480E+06 Altitude = 35000.00 XME = 0.200 COMPONENT RN CF CF*SWET CF*SWET*FF CDCOMP FUSELAGE 0.262E+08 0.00251 1.38212 1.41047 0.00232 CANOPY 0.720E+07 0.00309 0.23164 0.24889 0.00041 NACELLE 0.168E+08 0.00269 1.61561 1.63573 0.00269 GLV/SPONSON 0.170E+08 0.00269 0.81944 0.87782 0.00144 OUTB'D WING 0.609E+07 0.00318 2.21681 2.51746 0.00414 HORIZ. TAIL 0.398E+07 0.00342 0.75829 0.86114 0.00142 TWIN V. T. 0.321E+07 0.00355 0.88656 0.99464 0.00164 SUM = 7.91048 8.54615 0.01406 FRICTION DRAG: CDF = 0.01301 FORM DRAG: CDFORM = 0.00105 REYNOLDS NO./FT =0.288E+07 Altitude = 35000.00 XME = 1.200 COMPONENT RN CF CF*SWET CF*SWET*FF CDCOMP FUSELAGE 0.157E+09 0.00175 0.96201 0.98175 0.00161 CANOPY 0.432E+08 0.00211 0.15826 0.17004 0.00028 NACELLE 0.101E+09 0.00186 1.11769 1.13160 0.00186 GLV/SPONSON 0.102E+09 0.00186 0.56700 0.60740 0.00100 OUTB'D WING 0.366E+08 0.00216 1.51055 1.71542 0.00282 HORIZ. TAIL 0.239E+08 0.00231 0.51314 0.58274 0.00096 TWIN V. T. 0.193E+08 0.00239 0.59777 0.67064 0.00110 SUM = 5.42643 5.85959 0.00964 FRICTION DRAG: CDF = 0.00893 FORM DRAG: CDFORM = 0.00071 REYNOLDS NO./FT =0.480E+07 Altitude = 35000.00 XME = 2.000 COMPONENT RN CF CF*SWET CF*SWET*FF CDCOMP FUSELAGE 0.262E+09 0.00140 0.76912 0.78490 0.00129 CANOPY 0.720E+08 0.00169 0.12643 0.13585 0.00022 NACELLE 0.168E+09 0.00149 0.89337 0.90449 0.00149 GLV/SPONSON 0.170E+09 0.00149 0.45321 0.48550 0.00080 OUTB'D WING 0.609E+08 0.00173 1.20667 1.37032 0.00225 HORIZ. TAIL 0.398E+08 0.00185 0.40980 0.46538 0.00077 TWIN V. T. 0.321E+08 0.00191 0.47731 0.53550 0.00088 SUM = 4.33591 4.68193 0.00770 FRICTION DRAG: CDF = 0.00713 FORM DRAG: CDFORM = 0.00057 SUMMARY J XME Altitude RE/FT CDF CDFORM CDF+CDFORM 1 0.200 0.350E+05 0.480E+06 0.01301 0.00105 0.01406 2 1.200 0.350E+05 0.288E+07 0.00893 0.00071 0.00964 3 2.000 0.350E+05 0.480E+07 0.00713 0.00057 0.00770 END OF CASE