Model Design Using IRon Spreadsheets Bozzonetti Figure 1 Spreadsheet file model segmented wing panel IN PUT CONVENTIONAL MODEL DESIGN SEGMENTED WING WING N STAR P STAR FUSELAGE ENGINE 55 WINGSPAN GO SPAN SECTION PANEL. 155 ROOT CNORD05 SWEEP-ROOT SEC FWD-BNNOf0 MID CWORD105 SPAN SECTION PANEL 145 TIP CHORD S SWEEPTIP SECT FWDBKWDIS 125 AIRFOIL ENTER VALUE 052 SYHMETRICAL/SEMI S52 FLAT57 UNDER CAMBER60 SECTION MACA 23015 DIHEDRAL INCHES-PERPANEL3 SPAN175 ROOT CHORDS TIP CHORD5 LESWEEPFWD- BKWD0 SECTION ROOT FLAT TIP MEJONT45 ROOT CHORD95 TIP CHORD45 LESWEEPFWD-BkNDf 0 SECTION ROOT FLAT TIP DIST NOSE TO WING LE 9 0151 WING TE TON STAB LE . 215 01ST N STAR TE TO FUSE END 15 DISPLACEMENT CU IN045 HORSEPOWER1 MODEL WEIGHT LBS EST MODEL WEIGHT EST B MODEL WEIGHT EST C OUTPUT AREA5641 AC FROM IE AT ROOT . 3587 MACB4S4 CG FROM LE AT ROOT 3553TO 4441 ASPECT RATIO63141 IE SWEEP ROOT SECTIONIDEG TIP SECTION2209 DEG TAPER RATIO0571 WING LOADING2039A WING LOADING22430 WING LOADING2441C DIHEDRAL DEGREES-PANEL 5139 DEG AREA THEORETICAL8610 AREA ACTUAL075 N STAB OF WING 15491 AC FROM IE AT ROOT 125 ASPECT RATIO351 IE SWEEP0DEG TAPER RATIOI AREA TNEORETICAL3325 AREA ACTUAL315 VSTAB OF WINO 55171 VSTAG N OF N STAB361 ACFROM IE AT ROOT 4026 ASPECT RATIO09961 LESWEEP0DEG TAPER RATIO0413 LENGTH445 LENGTH 1 OF WINGSPAN1416 1 NOSE MOMENT FROM CS2820 1 TAIL MOMENT FROM CD 1191 LOADING LBS PER CU IN LOADING LBS PER CU IN LOADING LOS PER CU IN LOADING POUNDS PER HP LOADING POUNDS PER HP LOADiNG POUNDS PER HP 1111A 122281 1333C 5A 55N B C SWEPT TIPS 03-Mar-91 ft uncommon something f designed purpose used something else has happened spreadsheet programs intended accounting purposes spreadsheet lends itself practical model aircraft design tool replacing hand-held calculator article briefly describes efforts utilizing spreadsheet program perform calculations require designing model aircraft advantages Its easy learn No special skills knowledge required Results instantaneously displayed Changes data format can made easily file models data can stored future reference hard copy can easily made Two files have developed far Figure 1 file model segmented wing panel Figure 2 three-view layout model shown file model unbroken wing panel Data Input side files used generate results Output side except information regarding airfoil sections wing horizontal vertical stabilizers included historical purposes advantage files simplicity enter values Input side blink eye results displayed Output side have goal certain wing area wing loading aspect ratio combination vary Input values wing immediately see design goals will met Using hand-held calculator would very time-consuming formulas used files primarily obtained articles Model Aviation referenced later other model aviation magazine articles aeronautical textbooks January1998 59 WING H STAB V STAB FUSELAGE ENGINE WEIGHT spreadsheet programs capability utilizing formulas key adaptability model airplane design has formula inclusion file necessary format acceptable form spreadsheet example formula used calculating Mean Aerodynamic Chord MAC wing 2/3 T files wing root chord R assigned cell CS wing tip chord T assigned cell C9 formula spreadsheet would read 2/3*(CSC9 (C8 * C9IC8C9) Whatever values used cells CS C9 will calculated wherever used spreadsheet Modifications format can easily made wanted insert new line data would add line space choose displaced cell designations formulas would automatically change reflect new designations format shown allows data displayed its entirety monitor screen likewise printed output contained page very convenient Spreadsheet uses limited imagination example files article could rearranged provide space performance data column fellow District Columbia Radio Control Club DCRC club members Art Kresse designing flying wing model using spreadsheet program utilizing graphing feature obtain performance data Figure 2 Three-view layout model segmented wing panel LII]] KNA use spreadsheet program model aviation use outgrowth series June 1984 January 1986 articles Model Aviation Dick Sarpolus Bernie Raad presented programs written BASIC calculations model designs After using programs evident shortcoming existed entire program run after data entered order see calculated results should problem except whenever design model 6 Input data changes made before arriving final design dimensions Thats does have problem spreadsheet program results displayed instantly after entry spreadsheet program can also used full-scale aircraft evidenced series articles John Roncz Sport Aviation magazine 1990-91 anyone doing own model designs advantages using spreadsheet program worth investigating Files work equally well Lotus l23TM QuattroTM Pro programs available reasonable cost Bozzonetti 3783 Boteler Road Mt Airy MD 21771 60 Model Aviation
Edition: Model Aviation - 1998/01
Page Numbers: 59, 60
Model Design Using IRon Spreadsheets Bozzonetti Figure 1 Spreadsheet file model segmented wing panel IN PUT CONVENTIONAL MODEL DESIGN SEGMENTED WING WING N STAR P STAR FUSELAGE ENGINE 55 WINGSPAN GO SPAN SECTION PANEL. 155 ROOT CNORD05 SWEEP-ROOT SEC FWD-BNNOf0 MID CWORD105 SPAN SECTION PANEL 145 TIP CHORD S SWEEPTIP SECT FWDBKWDIS 125 AIRFOIL ENTER VALUE 052 SYHMETRICAL/SEMI S52 FLAT57 UNDER CAMBER60 SECTION MACA 23015 DIHEDRAL INCHES-PERPANEL3 SPAN175 ROOT CHORDS TIP CHORD5 LESWEEPFWD- BKWD0 SECTION ROOT FLAT TIP MEJONT45 ROOT CHORD95 TIP CHORD45 LESWEEPFWD-BkNDf 0 SECTION ROOT FLAT TIP DIST NOSE TO WING LE 9 0151 WING TE TON STAB LE . 215 01ST N STAR TE TO FUSE END 15 DISPLACEMENT CU IN045 HORSEPOWER1 MODEL WEIGHT LBS EST MODEL WEIGHT EST B MODEL WEIGHT EST C OUTPUT AREA5641 AC FROM IE AT ROOT . 3587 MACB4S4 CG FROM LE AT ROOT 3553TO 4441 ASPECT RATIO63141 IE SWEEP ROOT SECTIONIDEG TIP SECTION2209 DEG TAPER RATIO0571 WING LOADING2039A WING LOADING22430 WING LOADING2441C DIHEDRAL DEGREES-PANEL 5139 DEG AREA THEORETICAL8610 AREA ACTUAL075 N STAB OF WING 15491 AC FROM IE AT ROOT 125 ASPECT RATIO351 IE SWEEP0DEG TAPER RATIOI AREA TNEORETICAL3325 AREA ACTUAL315 VSTAB OF WINO 55171 VSTAG N OF N STAB361 ACFROM IE AT ROOT 4026 ASPECT RATIO09961 LESWEEP0DEG TAPER RATIO0413 LENGTH445 LENGTH 1 OF WINGSPAN1416 1 NOSE MOMENT FROM CS2820 1 TAIL MOMENT FROM CD 1191 LOADING LBS PER CU IN LOADING LBS PER CU IN LOADING LOS PER CU IN LOADING POUNDS PER HP LOADING POUNDS PER HP LOADiNG POUNDS PER HP 1111A 122281 1333C 5A 55N B C SWEPT TIPS 03-Mar-91 ft uncommon something f designed purpose used something else has happened spreadsheet programs intended accounting purposes spreadsheet lends itself practical model aircraft design tool replacing hand-held calculator article briefly describes efforts utilizing spreadsheet program perform calculations require designing model aircraft advantages Its easy learn No special skills knowledge required Results instantaneously displayed Changes data format can made easily file models data can stored future reference hard copy can easily made Two files have developed far Figure 1 file model segmented wing panel Figure 2 three-view layout model shown file model unbroken wing panel Data Input side files used generate results Output side except information regarding airfoil sections wing horizontal vertical stabilizers included historical purposes advantage files simplicity enter values Input side blink eye results displayed Output side have goal certain wing area wing loading aspect ratio combination vary Input values wing immediately see design goals will met Using hand-held calculator would very time-consuming formulas used files primarily obtained articles Model Aviation referenced later other model aviation magazine articles aeronautical textbooks January1998 59 WING H STAB V STAB FUSELAGE ENGINE WEIGHT spreadsheet programs capability utilizing formulas key adaptability model airplane design has formula inclusion file necessary format acceptable form spreadsheet example formula used calculating Mean Aerodynamic Chord MAC wing 2/3 T files wing root chord R assigned cell CS wing tip chord T assigned cell C9 formula spreadsheet would read 2/3*(CSC9 (C8 * C9IC8C9) Whatever values used cells CS C9 will calculated wherever used spreadsheet Modifications format can easily made wanted insert new line data would add line space choose displaced cell designations formulas would automatically change reflect new designations format shown allows data displayed its entirety monitor screen likewise printed output contained page very convenient Spreadsheet uses limited imagination example files article could rearranged provide space performance data column fellow District Columbia Radio Control Club DCRC club members Art Kresse designing flying wing model using spreadsheet program utilizing graphing feature obtain performance data Figure 2 Three-view layout model segmented wing panel LII]] KNA use spreadsheet program model aviation use outgrowth series June 1984 January 1986 articles Model Aviation Dick Sarpolus Bernie Raad presented programs written BASIC calculations model designs After using programs evident shortcoming existed entire program run after data entered order see calculated results should problem except whenever design model 6 Input data changes made before arriving final design dimensions Thats does have problem spreadsheet program results displayed instantly after entry spreadsheet program can also used full-scale aircraft evidenced series articles John Roncz Sport Aviation magazine 1990-91 anyone doing own model designs advantages using spreadsheet program worth investigating Files work equally well Lotus l23TM QuattroTM Pro programs available reasonable cost Bozzonetti 3783 Boteler Road Mt Airy MD 21771 60 Model Aviation