{"text_format":"2","workbook":"xls","n_sheets":6,"sheets":["INTRO","Find CG","Monoplane","Biplane","Canard ","Floats"],"not_rendered":{"charts":0,"images":0,"macros":0,"external_links":0,"defined_names":1,"comments":0,"pivot_tables":0},"unopened":[],"bounds":{"document_bytes":16777216,"sheet_cells":100000,"run_cost":"one","rows_first":2000,"rows_last":500,"rows_between":2000,"halvings":0,"cell_chars":16384,"cell_head_chars":4096},"cells_cut":0,"cells_raw":0,"read":"whole","date_system":"1900","formulas":"cached_only"}

{"sheet":"INTRO","index":0,"n_rows":62,"n_cols":11,"rows_kept":62,"cut":false,"hidden":false,"merged":[],"flags":["formulas_cached_only"]}
[]
[]
[]
[null,"The AIRPLANE DESIGN CALCULATOR (c) was created by Lee Van Tassle.  It is available for distribution and use for free, as"]
[null,"long as the complete package remains together.  Thank you and enjoy."]
[]
[null,"I would first like to recognize the following sources where all this information was gathered from:"]
[null,"Chuck Cunningham, CUNNINGHAM ON R/C, RCM"]
[null,"Kenneth Smith, DESIGN & BUILD your own R/C AIRCRAFT, Robson House Hobby Supplies"]
[null,"Howard Chevalier, MODEL AIRPLANE DESIGN AND PERFORMANCE FOR THE MODELER, Challenge Engineering, Inc"]
[null,"Andy Lennon, BASICS OF R/C MODEL AIRCRAFT DESIGN, Model Airplane News"]
[null,"Roy Day, GET THE CG RIGHT, Model Airplane News"]
[null,"George from the PALOS R/C Flying Club for the updated CG formulas.  http://www.palosrc.com/instructors/cg.htm"]
[]
[null,"In an effort to provide as much information in one easy to access place I've built this calculator to perform numerous designs"]
[null,"on the same file.  My goal was to provide one stop shopping for your basic aircraft designs without having to research"]
[null,"several books to find all the information you might need.  There are a lot of aspect I didn’t cover here, such as airfoils, lift/drag"]
[null,"coefficients, etc.  If you need more detailed info then you'll need to perform your own research to answer your specific questions."]
[null,"This calculator should get you started well on your way though."]
[]
[null,"Since I have no idea how to make this appear full screen on everyones computer, you will need to adjust your view size to fit your needs. "]
[null," I designed this on a 17\" monitor at 800x600 resolution.  Okay, enough of the small talk…on with the show!!!"]
[null,"To use the calculator, simply fill in the colored blocks (the others are locked) and the rest is done for you.  You will notice the left side of"]
[null,"the spreadsheet is your 'TARGET' values.  Most of the TARGETs are set and you can not change them.  Where a range"]
[null,"is given, I've left you the ability to input the range of your choice to adjust your target values.  All the YELLOW"]
[null,"blocks are for 'Your Design' inputs."]
[]
[null,"All calculations are based off a monoplane design first.  Please fill in the monoplane sheet, then switch over to the biplane,"]
[null,"canard, or float sheets to refine your design.  Of course you can go directly to the design page you want, but your target values"]
[null,"will not be set for your design.  Use the \"FIND CG\" tab to get accurate CG locations (except for Canards)."]
[]
[null,"I've checked and rechecked my calculations and everything seems to work alright.  You may notice if you put in the same"]
[null,"values as your target shows some of the readings will be different.  This is due to the rounding of numbers done to keep the"]
[null,"sheet as uncluttered as possible.  Small difference shouldn't significantly affect your planes performance."]
[]
[null,"One of my pet peeves is measurements given in degrees vs. an inch (sorry, I'm not Mr. Metrics) measurement.  Below are so "]
[null,"formulas to convert degrees to inches, SAE into Metric, etc.    Enjoy and I hope this serves you well in your own design projects."]
[]
[]
[null,"FORMULAS:"]
[null,"TLAR- That Looks About Right.  When your designing process, if it 'looks about right' it'll probably be fine.  Use TLAR throughout"]
[null,"your process.  Something odd doesn't mean bad, just different.  Experiment, remember- You're not flying in it so be brave!!!"]
[]
[null,"To convert degrees into an inch measurement:  0.0175 x degrees x given length = X "]
[]
[]
[]
[]
[]
[]
[null,"Multiply pounds by 16 to get ounces"]
[null,"Multiply feet by 12 to get inches"]
[null,"Multiply inches by 2.54 to get centimeters"]
[null,"Multiply meters by 39.37 to get inches"]
[null,"Multiply ounces by 28.35 to get grams"]
[null,"Multiply grams by 0.03527 to get ounces"]
[null,"Multiply square inches by 6.4516 to get square centimeters"]
[null,"Multiply by zero to get my remaining number of living brain cells"]
[{"$nulls":10},"Airplane Design Calculator ©"]
[{"$nulls":10},"V1.4, Aug 98"]
[{"$nulls":10},"Lee B. Van Tassle"]
[{"$nulls":10},"lee.van@mailexcite.com"]

{"sheet":"Find CG","index":1,"n_rows":93,"n_cols":9,"rows_kept":93,"cut":false,"hidden":false,"merged":[],"flags":["formulas_cached_only"]}
[null,null,"Find Wing CG Location"]
[]
["The CG of a wing can be figured both graphically and via the below calculations.  You will need to input the "]
["measurements and viola, the MAC and CG location will appear…MAGIC!!!"]
[]
["To find your CG you must determine the MAC (Mean Air Chord) or average chord of your wing.  You will then"]
["need to input the desired CG percentage.  The resulting measurement is aft of the leading edge at the MAC."]
["You will then need to run a line perpendicular to the wing's root line that intersects the MACs CG location."]
["Clear as mud; right???  Draw it out graphically just to make sure.   Take a look at the diagrams, I hope it makes sense. "]
["I'd like to thank George from the PALOS R/C Flying Club for the updated formulas.  http://www.palosrc.com/instructors/cg.htm"]
["CG= % of MAC for balance point (Norm 25-30%)"]
[]
[]
["Constant Chord Wing:"]
["Root Chord (R)",12]
["Tip Chord (T)",12]
["Wing Half Span",35]
["Desired CG % of MAC",0.28]
["MAC",12]
["MAC distance from root",17.5]
["Balance Point @ Root Chord",3.3600000000000003]
[]
[]
[]
["Tapered Wing:"]
["Root Chord (R)",12]
["Tip Chord (T)",10]
["Sweep Distance (S)",1]
["Wing Half Span",40]
["Desired CG % of MAC",0.3]
["Sweep Distance @ MAC",0.48484848484848486]
["MAC",11.030303030303031]
["MAC distance from root",19.393939393939394]
["Balance Point @ Root Chord",3.793939393939394]
[]
[]
[]
["Constant Chord Bipe:"]
["Root Chord (R)",20]
["Tip Chord (T)",20]
["Wing Half Span",30]
["Desired CG % of MAC",0.25]
["MAC",20]
["MAC distance from root",15]
["Balance Point @ Frwd Root Chord",5]
[]
[]
[]
[]
[]
[]
["Bent Wing Bipe:"]
["Root Chord (R)",20]
["Tip Chord (T)",15]
["Sweep Distance (S)",4]
["Wing Half Span",32]
["Desired CG % of MAC",0.25]
["Sweep Distance @ MAC",1.9047619047619047]
["MAC",17.61904761904762]
["MAC distance from root",15.238095238095237]
["Balance Point @ Root Chord",6.30952380952381]
{"$rows_empty":10}
["Tapered Swept Wing:"]
["Root Chord (R)",12]
["Tip Chord (T)",6]
["Sweep Distance (S)",9.5]
["Wing Half Span",36]
["Desired CG % of MAC",0.28]
["Sweep Distance @ MAC",4.222222222222222]
["MAC",9.333333333333332]
["MAC distance from root",16]
["Balance Point @ Root Chord",6.835555555555556]
["NOTE:"]
["(For Forward Swept Wing Distance \"S\""]
["needs to be input as a negative (-) number"]
["I.e. -5.  If the 'Balance Point @ Root Chord'"]
["is positive, the CG is aft of the root LE, if negative"]
["the CG point is forward of the root LE)"]
[]
[]
[{"$nulls":8},"Airplane Design Calculator ©"]
[{"$nulls":8},"V1.4, Aug 98"]
[{"$nulls":8},"Lee B. Van Tassle"]
[{"$nulls":8},"lee.van@mailexcite.com"]

{"sheet":"Monoplane","index":2,"n_rows":100,"n_cols":15,"rows_kept":100,"cut":false,"hidden":false,"merged":[],"flags":["formulas_cached_only"]}
[]
[]
[{"$nulls":8},"WING DESIGN"]
[null,"Average Values",null,"TARGET PLANE",{"$nulls":8},"YOUR DESIGN"]
["Engine","Area","Weight","WING",null,"Norms",{"$nulls":6},"WING"]
["C.I.D.","oz/sq.ft.","ounces","Tip Chord",10,{"$nulls":7},"Tip Chord",10]
[0.1,300,29,"Root Chord",10,{"$nulls":7},"Root Chord",10]
[0.15,325,34,"Wing Span",60,{"$nulls":7},"Wing Span",60]
[0.2,420,45,"Mean Air Chord (MAC)",10,{"$nulls":7},"~Mean Air Chord (MAC)",10]
[0.25,450,55,"Area ",600,{"$nulls":7},"Area ",600]
[0.35,550,73,"Aspect Ration (AR)",6," 6:1",{"$nulls":6},"Aspect Ration (AR)",6,":1"]
[0.4,600,79,"CG (% of Chord)",0.27,"25-30%",{"$nulls":6},"Estimated Weight (oz)",88]
[".45-6",700,88,"CG Location",2.7,{"$nulls":7},"Wing Loading (oz/ft2)",21.119999999999997]
[0.5,750,104,"Estimated Weight",79]
[".60-1",800,128,"Wing Loading (oz/sq.ft.)",18.959999999999997]
[null,null,null,"Ailerons",{"$nulls":8},"Ailerons"]
[null,null,null,"Strip",{"$nulls":8},"Strip"]
[null,null,null,"Chord",1,"10% Wing Chord",{"$nulls":6},"Chord",1]
[null,null,null,"Length",27,{"$nulls":7},"Length",27]
[null,null,null,"Area ",27,"4.5% Wing Area",{"$nulls":6},"Area ",27]
[null,null,null,"Barn Door",{"$nulls":8},"Barn Door"]
[null,null,null,"Chord",2.5,"25% Wing Chord",{"$nulls":6},"Chord",2.5]
[null,null,null,"Length",14.4,{"$nulls":7},"Length",14.4]
[null,null,null,"Area ",36,"6% Wing Area",{"$nulls":6},"Area ",36]
[null,null,null,"Flaps",{"$nulls":8},"Flaps"]
[null,null,null,"% of Wing Chord",0.3,"25-30% Wing Chord",{"$nulls":6},"% of Wing Chord",0.3,"25-30% Wing Chord"]
[null,null,null,"Chord",3,{"$nulls":7},"Chord",3]
[null,null,null,"% of Wing Span",0.33,"30-33% Wing Span",{"$nulls":6},"% of Wing Span",0.33,"30-33% Wing Span"]
[null,null,null,"Span",19.8,{"$nulls":7},"Span",19.8]
[null,null,null,"Recommended Dihedral",{"$nulls":8},"Dihedral "]
[null,null,null,"High Wing (1 degrees)",0.525,{"$nulls":7},"Desired Degrees",2]
[null,null,null,"Mid Wing (2 degrees)",1.05,{"$nulls":7},"Dihedral Measurement",1.05]
[null,null,null,"Low Wing (3 degrees)",1.5750000000000002]
[]
[null,null,null,"Empenage",{"$nulls":8},"Empenage"]
[null,null,null,"HORIZONTAL STAB",{"$nulls":8},"HORIZONTAL STAB"]
[null,null,null,"% of Wing Area",0.22," 20-25% ",{"$nulls":6},"Span",19.5]
[null,null,null,"Span",19.8997487421324,{"$nulls":7},"Tip Chord",6]
[null,null,null,"Total Chord",6.6332495807108,{"$nulls":7},"Root Chord",8]
[null,null,null,"Area",132,{"$nulls":7},"MAC",7]
[null,null,null,"AR",3," 3:1",{"$nulls":6},"Area",136.5]
[null,null,null,"Elevator",{"$nulls":8},"AR",2.7857142857142856,":1"]
[null,null,null,"% of Total Chord",0.25,"25-30%",{"$nulls":6},"Elevator"]
[null,null,null,"Chord",1.6583123951777,{"$nulls":7},"% of Total Chord",0.25,"25-30%"]
[null,null,null,"VERTICLE FIN",{"$nulls":8},"Chord",1.75]
[null,null,null,"Height",8.017837257372731,{"$nulls":7},"VERTICLE FIN"]
[null,null,null,"Total Tip Chord",3.2071349029490928,{"$nulls":7},"Height",9]
[null,null,null,"X Height for Root Chord",1.15," 100-125% Height",{"$nulls":6},"Total Tip Chord",4]
[null,null,null,"Total Root Chord",9.22051284597864,{"$nulls":7},"X Height for Root Chord",1.15," 100-125% Height"]
[null,null,null,"% of Wing Area",0.075,"7-12%",{"$nulls":6},"Total Root Chord",10.35]
[null,null,null,"Target Area",45,{"$nulls":7},"Area",64.575]
[null,null,null,"Rudder",{"$nulls":8},"Rudder"]
[null,null,null,"% of Total Tip Chord",0.4,"30-50%",{"$nulls":6},"% of Total Tip Chord",0.5,"30-50%"]
[null,null,null,"Tip Chord",1.2828539611796372,{"$nulls":7},"Tip Chord",2]
[null,null,null,"% of Total Root Chord",0.4,"30-50% ",{"$nulls":6},"% of Total Root Chord",0.5,"30-50%"]
[null,null,null,"Root Chord",3.688205138391456,{"$nulls":7},"Root Chord",5.175]
[null,null,null,"Area",19.928571428571427,{"$nulls":7},"Area",32.2875]
[]
["Engine","Prop.",null,"Fuselage"]
["C.I.D.","Diameter",null,"Fuse Length (A)",42,"Spinner backplate to rudder hinge line",{"$nulls":6},"Fuselage"]
[0.1,7,null,"Nose Length (B)",8.82,"Spinner backplate to wing LE",{"$nulls":6},"Fuse Length (A)",42]
[0.15,8,null,"Tail Length (C)",23.1,"Wing TE to rudder hinge line",{"$nulls":6},"Nose Length (B)",8.82]
[0.2,8,null,"Engine Size",0.4,{"$nulls":7},"Tail Length (C)",23.1]
[0.25,9,null,"Prop Diameter",10,{"$nulls":7},"Engine Size",0.45]
[0.35,9,null,"Landing Gear",{"$nulls":8},"Prop Diameter",11]
[0.4,10,null," Height (D)",7.2,"Axle 20-25% longer than prop radius",{"$nulls":6},"Landing Gear"]
[".45-6",11,null,"Spread",15,"25% Wing Span",{"$nulls":6}," Height (D)",7.92]
[0.5,11,null,"Gear Location",{"$nulls":8},"Spread",15]
[".60-1",12,null,"Trike Front","Axle in line with firewall",{"$nulls":7},"Gear Location"]
[null,null,null,"Trike Main",2.0160000000000005,"1.5\"-2\" behind CG",{"$nulls":6},"Trike Front","Axle in line with firewall"]
[null,null,null,"Tail Dragger Main","Axle in line or ahead of wing leading edge",{"$nulls":7},"Trike Main (inches)",2.2176,"\" behind CG"]
[null,null,null,"Tail Wheel","Hinged on rudder line, axle aft of hinge line",{"$nulls":7},"Tail Dragger Main","Axle in line or ahead of wing leading edge"]
[{"$nulls":12},"Tail Wheel","Hinged on rudder line, axle aft of hinge line"]
{"$rows_empty":23}
[{"$nulls":12},"Airplane Design Calculator ©"]
[{"$nulls":12},"V1.4. Aug 98"]
[{"$nulls":12},"Lee B. Van Tassle"]
[{"$nulls":12},"lee.van@mailexcite.com"]

{"sheet":"Biplane","index":3,"n_rows":117,"n_cols":13,"rows_kept":117,"cut":false,"hidden":false,"merged":[],"flags":["formulas_cached_only"]}
[]
[]
[{"$nulls":6},"WING DESIGN"]
[null,"TARGET PLANE",{"$nulls":8},"YOUR DESIGN"]
[null,"TOP WING",null,"Norms",{"$nulls":6},"TOP WING"]
[null,"Tip Chord",8.366600265340756,{"$nulls":7},"Tip Chord",9.52]
[null,"Root Chord",8.366600265340756,{"$nulls":7},"Root Chord",9.52]
[null,"Wing Span",50.19960159204453,{"$nulls":7},"Wing Span",57.13]
[null,"Mean Air Chord (MAC)",8.366600265340756,{"$nulls":7},"Mean Air Chord (MAC)",9.52]
[null,"Area ",420,{"$nulls":7},"Area ",543.8776]
[null,"Aspect Ration (AR)",6," 6:1",{"$nulls":6},"Aspect Ration (AR)",6.001050420168068,":1"]
[null,"Bottom Wing",{"$nulls":8},"Bottom Wing"]
[null,"Tip Chord",8.366600265340756,{"$nulls":7},"Tip Chord",9.52]
[null,"Root Chord",8.366600265340756,{"$nulls":7},"Root Chord",9.52]
[null,"Wing Span",50.19960159204453,{"$nulls":7},"Wing Span",57.13]
[null,"Mean Air Chord (MAC)",8.366600265340756,{"$nulls":7},"Mean Air Chord (MAC)",9.52]
[null,"Area ",420,{"$nulls":7},"Area ",543.8776]
[null,"Aspect Ration (AR)",6," 6:1",{"$nulls":6},"Aspect Ration (AR)",6.001050420168068,":1"]
[null,"Ailerons",{"$nulls":8},"Ailerons"]
[null,"Strip",{"$nulls":8},"Strip"]
[null,"Chord",0.8366600265340756,"10% Wing Chord",{"$nulls":6},"Chord",0.952]
[null,"Length",22.58982071642004,{"$nulls":7},"Length",25.708500000000004]
[null,"Area ",18.9,"4.5% Wing Area",{"$nulls":6},"Area ",24.474492]
[null,"Barn Door",{"$nulls":8},"Barn Door"]
[null,"Chord",2.091650066335189,"25% Wing Chord",{"$nulls":6},"Chord",2.38]
[null,"Length",12.047904382090687,{"$nulls":7},"Length",13.7112]
[null,"Area ",25.2,"6% Wing Area",{"$nulls":6},"Area ",32.632656]
[null,"Stager",{"$nulls":8},"Stager"]
[null,"Desired Stager",0.25," 0-50% of Chord",{"$nulls":6},"Desired Stager",0.3]
[null,"CG (% of Total Chord)",0.27,"25-30%",{"$nulls":6},"CG (% of Total Chord)",0.27,"25-30%"]
[null,"CG Location",2.8237275895525054,"Aft of forward most wing LE"]
[null,"Gap",8.366600265340756,"1 x Avg MAC",{"$nulls":6},"Gap",9.52]
[null,"Total Wing Area",840,{"$nulls":7},"Total Wing Area",1087.7552]
[null,"Estimated Weight",79,{"$nulls":7},"Estimated Weight",88]
[null,"Wing Loading",13.542857142857143,{"$nulls":7},"Wing Loading (oz/ft2)",11.649680001529756]
[]
[{"$nulls":10},"Dihedral "]
[{"$nulls":10},"Desired Degrees"]
[null,"Recommended Dihedral",{"$nulls":8},"Top",1]
[null,"Top Wing (0 degrees)",0,{"$nulls":7},"Dihedral Measurement",0.4998875000000001]
[null,"Bottom Wing (2 degrees)",0.8784930278607793,{"$nulls":7},"Bottom",2]
[{"$nulls":10},"Dihedral Measurement",0.9997750000000002]
[]
[null,"Empenage",{"$nulls":8},"Empenage"]
[null,"HORIZONTAL STAB",{"$nulls":8},"HORIZONTAL STAB"]
[null,"% of Total Wing Area",0.175,"17-20%",{"$nulls":6},"Span",25.5]
[null,"Span",21,{"$nulls":7},"Tip Chord",7]
[null,"Total Chord",7,{"$nulls":7},"Root Chord",9]
[null,"Target Area",147,{"$nulls":7},"MAC",8]
[null,"AR",3," 3:1",{"$nulls":6},"Area",204]
[null,"Elevator",{"$nulls":8},"AR",3.1875,":1"]
[null,"% of Total Chord",0.28,"27-30%",{"$nulls":6},"Elevator"]
[null,"Chord",1.9600000000000002,{"$nulls":7},"% of Total Chord",0.3,"27-30%"]
[null,"VERTICAL FIN",{"$nulls":8},"Chord",2.4]
[null,"Height",7.937253933193772,{"$nulls":7},"VERTICAL FIN"]
[null,"Total Tip Chord",3.174901573277509,{"$nulls":7},"Height",9]
[null,"X Height for Root Chord",1.125,"100-125% Height",{"$nulls":6},"Total Tip Chord",4]
[null,"Total Root Chord",8.929410674842993,{"$nulls":7},"X Height for Root Chord",1.15,"100-125% Height"]
[null,"% of Stab Area",0.3," 30-50% Stab",{"$nulls":6},"Total Root Chord",10.35]
[null,"Target Area",44.1,{"$nulls":7},"Area",64.575]
[null,"Rudder",{"$nulls":8},"Rudder"]
[null,"% of Total Tip Chord",0.4,"30-50%",{"$nulls":6},"% of Total Tip Chord",0.4,"30-50%"]
[null,"Tip Chord",1.2699606293110037,{"$nulls":7},"Tip Chord",1.6]
[null,"% of Total Root Chord",0.4,"30-50% ",{"$nulls":6},"% of Total Root Chord",0.4,"30-50% "]
[null,"Root Chord",3.5717642699371974,{"$nulls":7},"Root Chord",4.14]
[null,"Area",19.215000000000003,{"$nulls":7},"Area",25.830000000000002]
[]
[null,"Fuselage"]
[null,"Fuse Length (A)",40.15968127363563,"Spinner backplate to rudder hinge line",{"$nulls":6},"Fuselage"]
[null,"Nose Length (B)",8.43353306746348,"Spinner backplate to wing LE",{"$nulls":6},"Fuse Length (A)",45.70400000000001]
[null,"Tail Length (C)",22.087824700499596,"Wing TE to rudder hinge line",{"$nulls":6},"Nose Length (B)",9.597840000000001]
[null,"Engine Size",0.4,{"$nulls":7},"Tail Length (C)",25.137200000000007]
[null,"Prop Diameter",10,{"$nulls":7},"Engine Size",0.45]
[null,"Landing Gear",{"$nulls":8},"Prop Diameter",11]
[null," Height (D)",7.2,"Axle 20-25% longer than prop radius",{"$nulls":6},"Landing Gear"]
[null,"Spread",12.549900398011133,"25% Wing Span",{"$nulls":6}," Height (D)",7.92]
[null,"Gear Location",{"$nulls":8},"Spread",14.2825]
[null,"Tail Dragger Main","Axle in line or ahead of foremost wing leading edge",{"$nulls":7},"Gear Location"]
[null,"Tail Wheel","Hinged on rudder line, axle aft of hinge line",{"$nulls":7},"Tail Dragger Main","Axle in line or ahead of wing leading edge"]
[{"$nulls":10},"Tail Wheel","Hinged on rudder line, axle aft of hinge line"]
{"$rows_empty":25}
["NOTES:"]
["Wings:  Bipe wings are only ~80% as efficient as a monoplane.  Wing span is a monoplane equivalent span +40% more, then split between the upper and lower wings.  You can increase the upper"]
["wing span and decrease the lower wing span, same goes for the chords as long as your total wing area remains around the target zone.  Wings are separated by 1 chord span measured from the"]
["wing chord lines.  The lower wing and horizontal stab incidence is normally 0 degrees to the thrust line, the upper wing ranges from -1 to +1 degree to the thrust line (this designer prefers -1 degree)."]
["Wing stager is a matter of personal choice from 0 to 50% chord positive (top wing forward of lower wing) or negative (bottom wing forward of top wing) stager; normal is in the 25%"]
["positive stager range."]
["Empenage:  The horizontal and vertical stabilizers sizes are about the same as an equivalent monoplane, just figured a little differently because of the wing changes."]
[]
[{"$nulls":10},"Airplane Design Calculator ©"]
[{"$nulls":10},"V1.4, Aug 98"]
[{"$nulls":10},"Lee B. Van Tassle"]
[{"$nulls":10},"lee.van@mailexcite.com"]

{"sheet":"Canard ","index":4,"n_rows":98,"n_cols":14,"rows_kept":98,"cut":false,"hidden":false,"merged":[],"flags":["formulas_cached_only"]}
[]
[]
[{"$nulls":6},"CANARD DESIGN"]
["FOREPLANE",null,"NORMS",{"$nulls":8},"FOREPLANE"]
["% of Wing Area",0.3,"15-50% "]
["Tip Chord",6.708203932499369,{"$nulls":9},"Tip Chord",8]
["Root Chord",6.708203932499369,{"$nulls":9},"Root Chord",10]
["MAC",6.708203932499369,{"$nulls":9},"MAC",9]
["Span",26.832815729997478,{"$nulls":9},"Span",30]
["Area",180,{"$nulls":9},"Area",270]
["AR",4,"3-6:1",{"$nulls":8},"AR",3.3333333333333335,":1"]
["Canard Loading (oz/sq.ft.)",63.2,{"$nulls":9},"Canard Loading (oz/sq.ft.)",53.333333333333336]
["Elevator",{"$nulls":10},"Elevator"]
["% of Total Chord",0.29,"28-30%",{"$nulls":8},"% of Total Chord",0.29]
["Chord",1.945379140424817,{"$nulls":9},"Chord",2.61]
[]
["Distance A to B:",30,"2 -4 times Aftplane MAC",{"$nulls":8},"Distance A to B:",34.64]
["Static of Margin",0.2,"15-25% (The higher, the more stable)",{"$nulls":8},"Static of Margin",0.2]
["Neutral Point (NP)",7.5,"Fwd of wing's aerodynamic center",{"$nulls":8},"Neutral Point (NP)",9.44569272049039]
["CG Location",9.5,"Fwd of wing's aerodynamic center",{"$nulls":8},"CG Location",11.75569272049039]
[]
[]
["AFTPLANE",{"$nulls":10},"AFTPLANE"]
["Tip Chord",10,{"$nulls":9},"Tip Chord",10.55]
["Root Chord",10,{"$nulls":9},"Root Chord",12.55]
["Wing Span",60,{"$nulls":9},"Wing Span",69.28]
["Mean Air Chord (MAC)",10,{"$nulls":9},"Mean Air Chord (MAC)",11.55]
["Area ",600,{"$nulls":9},"Area ",800.1840000000001]
["Aspect Ration (AR)",6,":1",{"$nulls":8},"Aspect Ration (AR)",5.998268398268398,":1"]
["Estimated Weight",79,{"$nulls":9},"Estimated Weight",100]
["Wing Loading (oz/sq.ft.)",18.959999999999997,{"$nulls":9},"Wing Loading (oz/sq.ft.)",17.995860951981044]
["Ailerons",{"$nulls":10},"Ailerons"]
["Strip",{"$nulls":10},"Strip"]
["Chord",1,{"$nulls":9},"Chord",1.155]
["Length",27,{"$nulls":9},"Length",31.176]
["Area ",27,{"$nulls":9},"Area ",36.00828]
["Barn Door",{"$nulls":10},"Barn Door"]
["Chord",2.5,{"$nulls":9},"Chord",2.8875]
["Length",14.4,{"$nulls":9},"Length",16.6272]
["Area ",36,{"$nulls":9},"Area ",48.01104]
[]
["VERTICAL STAB",{"$nulls":10},"VERTICAL STAB"]
["Height",10.014275524755362,{"$nulls":9},"Height",12.86]
["Total Tip Chord",4.005710209902145,{"$nulls":9},"Total Tip Chord",5.15]
["X Height for Root Chord",1.15," 100-125% Height",{"$nulls":8},"X Height for Root Chord",1.15," 100-125% Height"]
["Total Root Chord",11.516416853468666,{"$nulls":9},"Total Root Chord",14.788999999999998]
["% of Wing Area",0.09,"7-12%Ttl Wing Area",{"$nulls":8},"Area",128.20776999999998]
["Target Area",70.2,{"$nulls":9},"Rudder"]
["Rudder",{"$nulls":10},"% of Total Tip Chord",0.4,"30-50%"]
["% of Total Tip Chord",0.4,"30-50%",{"$nulls":8},"Tip Chord",2.06]
["Tip Chord",1.602284083960858,{"$nulls":9},"% of Total Root Chord",0.4,"30-50%"]
["% of Total Root Chord",0.4,"30-50% ",{"$nulls":8},"Root Chord",5.9155999999999995]
["Root Chord",4.606566741387467,{"$nulls":9},"Area",51.283108]
["Area",31.08857142857143]
[]
["Fuselage",{"$nulls":10},"Engine Size",0.45]
["Engine Size",0.4,{"$nulls":9},"Prop Diameter",10]
["Prop Diameter",10,{"$nulls":9},"Landing Gear"]
["Landing Gear",{"$nulls":10}," Height (D)",7.2]
[" Height (A)",7.2,"Axle 20-25% longer than prop radius",{"$nulls":8},"Spread",17.32]
["Spread",15,"25% Wing Span",{"$nulls":8},"Gear Location"]
["Gear Location",{"$nulls":10},"Trike Front","Axle in line with firewall"]
["Trike Front",null,"Axle in line with firewall",{"$nulls":8},"Trike Main",2.2680000000000007,"behind CG"]
["Trike Main",2.2680000000000007,"1.5\"-2\" behind CG"]
{"$rows_empty":23}
["NOTES: "]
["Foreplane:  A canard foreplane must stall before the aftplane or the plane will become unstable at low speeds.  The smaller the canard, the higher it's loading and the more  "]
["positive angle of attack it must have.  For a slab canard, incidence of +3 degrees is normal.  For a lifting airfoil canard, +1 degree should be acceptable.  The larger the canard, the "]
["more forward the CG location will be.  The foreplane is normally in-line or above the aftplane, this is because of downwash from the canard."]
["Aftplane:  The aftplane is usually set at 0-+1 degree positive incidence to the thrust line."]
["Engine:  A fore mounted engine will enable easier CG adjustment.  A pusher configuration will require a long nose moment and a lot of ballast to bring the CG into range."]
[]
[{"$nulls":11},"Airplane Design Calculator ©"]
[{"$nulls":11},"V1.4, Aug 98"]
[{"$nulls":11},"Lee B. Van Tassle"]
[{"$nulls":11},"lee.van@mailexcite.com"]

{"sheet":"Floats","index":5,"n_rows":57,"n_cols":11,"rows_kept":57,"cut":false,"hidden":false,"merged":[],"flags":["formulas_cached_only"]}
[]
[]
[{"$nulls":4},"FLOAT DESIGN"]
[]
[null,null,"Target Float",null,"Norms",{"$nulls":4},"Your Float"]
[null,null,"Engine Size",0.4,{"$nulls":5},"Engine Size",0.45]
[null,null,"Length (A)",31.5,"75% Fuse Length",null,null,"Width",null,"Length (A)",40]
[null,null,"Tip to Step (B)",16.695,"53% Length",null,null,".10 - .25 (2\")",null,"Tip to Step (B)",21.200000000000003]
[null,null,"Step to Stern (C)",14.805,"47% Length",null,null,".30 - .40 (3\")",null,"Step to Stern (C)",18.799999999999997]
[null,null,"Curve to Tip (D)",4.41,"14% Length",null,null,".45 - .60 (4\")",null,"Curve to Tip (D)",5.6000000000000005]
[null,null,"Height (E)",2.52,"8% Length",null,null,".90 - 1.2 (5\")",null,"Height (E)",3.2]
{"$rows_empty":36}
[null,"NOTES:"]
[null,"Floats can be flat bottom for ease of construction, built from foam, balsa, ply or any combination thereof."]
[null,"Wing should be 2 - 3 degrees positive incidence to top line float or you'll have a hard time 'unsticking' from the water."]
[null,"Float spread is the same as landing gear spread for the same size land plane."]
[null,"Water rudder can be either attached to rudder or placed on the back of either/both floats."]
[]
[{"$nulls":10},"Airplane Design Calculator ©"]
[{"$nulls":10},"V1.4, Aug 98"]
[{"$nulls":10},"Lee B. Van Tassle"]
[{"$nulls":10},"lee.van@mailexcite.com"]