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Conference vmszoo::rc

Title:	Welcome To The Radio Control Conference
Notice:	dir's in 11, who's who in 4, sales in 6, auctions 19
Moderator:	VMSSG::FRIEDRICHS

Created:	Tue Jan 13 1987
Last Modified:	Thu Jun 05 1997
Last Successful Update:	Fri Jun 06 1997
Number of topics:	1706
Total number of notes:	27193

1205.0. "Program to Determine some basic calculations" by CSC32::M_ANTRY () Mon Apr 23 1990 20:03

    Well not owning any kind of a PC or the such to run fancy Aerodynamic
    calculatins I thought I would gather up all of the Data I could find
    and write my own.  I basicaly want to know what all the particulars on
    a certain plane and to further prove that it will fly.  I wrote the
    following program based upon a spread sheet dump that I got from a
    friend of mine, Barry Welch.  The calculations are pretty straight
    forward Math.  The pitch stability calculations are derived from some
    formulas that a free flighter in our club came up with and also from
    observed.  The formula I put in the program was derived from a chart
    that had a line drawn on it and I just calculated the formula for the
    line and called it good.
    
    I wrote this in as Basic Basic as I could basicaly come up with so that
    it would work on the easyeast basic as possible.  No subroutines,
    functions or anything like that.
    
    Let me know if I can answer any questions or help out.  If people need
    .OBJ or .EXE's let me know and I can make those available.
    
    The Program can handle wings with up to 3 different panels.  It wants
    the root cord, tip cord, offset, and span for up to 3 panels.  It will
    ask for weight and then if you do stab calculatins it will ask for the
    stab dimensions and for pitch stability it will ask for the CG percent
    and the Leading edge to Leading edge measurement for wing to Stab.
    
    Here is the source, have at it!@!!!!!!!

T.R	Title	User	Personal Name	Date	Lines
1205.1	And here it is.....	CSC32::M_ANTRY		`Mon Apr 23 1990 20:05`	152
	50 rem Program: SAIL 60 rem This program was written by Mark Antry April 1990 100 print "This program will Calculate the Mean Aerodynamic Chord," 120 print "its position, Area and Aspect Ratio of Wings along with" 125 print "optional Stab and Pitch Stability Calculations." 130 print "NOTE: All dimensions are in decimal inches and weight in OZ's." 140 print\print 200 print "How many different sections does this wing have?" 220 print "A single taper flat wing would have 1, a polyhedrel plane" 240 print "will probably have 2, Schuman 3, etc." 260 input "Number of sections ",NUMSEC 280 print\print 300 print " First Section" 320 print\print 340 input "What is the length of the root chord of this section ",FROOT 360 input "What is the length of the tip chord of this section ",FTIP 380 print\print "The offset is how far the Leading edge of the tip is" 400 print "back from the Leading edge of root. Example: If you had a" 420 print "10in root and a 6in tip and the leading edge was square the " 440 print "offset would 4in...." 460 input "What is the offset of the Tip chord from the Root Chord ",FOFF 480 input "What is the span of this section ",FSPAN 499 if numsec < 2 then goto 5000 500 print\print " Second Section" 520 print\print 540 input "What is the length of the root chord of this section ",SROOT 550 input "What is the length of the tip chord of this section ",STIP 560 input "What is the offset of the Tip chord from the Root Chord ",SOFF 570 input "What is the span of this section ",SSPAN 599 if numsec < 3 then goto 5000 600 print\print " Third Section" 620 print\print 640 input "What is the length of the root chord of this section ",TROOT 650 input "What is the length of the tip chord of this section ",TTIP 660 input "What is the offset of the Tip chord from the Root Chord ",TOFF 670 input "What is the span of this section ",TSPAN 5000 print\print\Input "What does the model weigh (oz's) ",weight 5005 REM CALCULATE DATA 5010 REM COMPUTE ALL MAC'S 5020 FMAC = (2(FROOT^2+FROOTFTIP+FTIP^2))/(3(FROOT+FTIP)) 5030 if numsec > 1 then SMAC = (2(SROOT^2+SROOTSTIP+STIP^2))/(3(SROOT+STIP)) 5060 if numsec > 2 then TMAC = (2(TROOT^2+TROOTTTIP+TTIP^2))/(3(TROOT+TTIP)) 5100 REM COMPUTE ALL MAC OFFSET'S 5120 FMACO = (FOFF(FROOT-FMAC)/(FROOT-FTIP+0.00000001)) 5140 if numsec > 1 then SMACO = (SOFF(SROOT-SMAC)/(SROOT-STIP+0.00000001)) 5160 if numsec > 2 then TMACO = (TOFF(TROOT-TMAC)/(TROOT-TTIP+0.00000001)) 5200 REM COMPUTE ALL AREA'S 5210 FAREA = (FSPAN(FROOT+FTIP)/2) 5220 if numsec > 1 then SAREA = (SSPAN(SROOT+STIP)/2) 5240 if numsec > 2 then TAREA = (TSPAN(TROOT+TTIP)/2) 5300 REM COMPUTE TOTAL WING VALUES 5305 TOTAREA = FAREA+SAREA+TAREA 5310 WMAC = (FMACFAREA+SMACSAREA+TMAC+TAREA)/TOTAREA 5320 WOFF = (FMACOFAREA+(FOFF+SMACO)SAREA+(FOFF+SOFF+TMACO)TAREA)/TOTAREA 5340 WAREA = (FAREA+SAREA+TAREA)2 5360 WASPECT = (2(FSPAN+SSPAN+TSPAN))^2/WAREA 5380 WSPAN = (2(FSPAN+SSPAN+TSPAN)) 5400 REM Compute Wing Loading 5420 WLOAD = WAREA / WEIGHT 5600 REM Stab data 5605 print\print 5610 Input "Do you wish to do Stab Calculations (Y/N)",QSTAB$ 5620 If QSTAB$ <> "Y" and QSTAB$ <> "y" then goto 6000 5630 print\print 5640 input "What is the length of the root chord of this stab ",STROOT 5650 input "What is the length of the tip chord of this stab ",STTIP 5660 input "What is the offset of the Tip chord from the Root Chord ",STOFF 5670 input "What is the span of this stab ",STSPAN 5690 STMAC = (2(STROOT^2+STROOTSTTIP+STTIP^2))/(3(STROOT+STTIP)) 5700 STMACO = (STOFF(STROOT-STMAC)/(STROOT-STTIP+0.00000001)) 5720 STAREA = (2(STSPAN(STROOT+STTIP)/2)) 5730 STASPECT = (2(STSPAN))^2/STAREA 5740 STSPANT = STSPAN2 5800 REM Stab calculations 5820 print\print 5840 Input "Do you wish to do Pitch Stability Calculations (Y/N)",QPITCH$ 5860 If QPITCH$ <> "Y" and QPITCH$ <> "y" then goto 6000 5880 print "What is the lenght from the Leading edge of the Wing to" 5900 input "the leading edge of the STAB ",LENLELE 5910 input "At what percent of the CG will this plane be balanced at ",WCG 5920 PITCHLEN = LENLELE-WOFF-STMACO-(STMAC-(STMAC0.25)) 5940 TVFAC = (STAREA/WAREA) * (PITCHLEN/WMAC) 5960 YINTERSECT = 2.2 * (WCG * .01) + (- .49) 6000 REM PRINT OUT RESULTS 6020 PRINT\PRINT\PRINT\PRINT\PRINT 6060 print "The Total Wing summary is:" 6080 print " MAC ";WMAC 6090 print " MAC offset ";WOFF;" from Leading edge of the root" 6100 print " Area ";WAREA;" sq in" 6110 print " Aspect Ratio ";WASPECT;" to 1" 6120 print " Wing Span ";WSPAN 6130 print " Wing Loading ";WLOAD;" oz/sq inch" 6140 print "NOTE: CG would be calculated as CG % * MAC + MAC offset" 6150 print " measured from leading edge of the root" 6200 print\print\print 6210 print "The First Section summary is:" 6220 print " MAC ";FMAC 6240 print " MAC offset ";FMACO 6260 print " Area ";FAREA;" sq in" 6280 if numsec < 2 then goto 7000 6305 print\print\print 6310 print "The Second Section summary is:" 6320 print " MAC ";SMAC 6340 print " MAC offset ";SMACO 6360 print " Area ";SAREA;" sq in" 6380 if numsec < 3 then goto 7000 6405 print\print\print 6410 print "The Third Section summary is:" 6420 print " MAC ";TMAC 6440 print " MAC offset ";TMACO 6460 print " Area ";TAREA;" sq in" 7000 rem Print Stab results if needed 7020 If QSTAB$ <> "Y" and QSTAB$ <> "y" then goto 8000 7300 print\print\print 7320 print "The Stab Section summary is:" 7340 print " MAC ";STMAC 7360 print " MAC offset ";STMACO 7380 print " Area ";STAREA;" sq in" 7370 print " Aspect ratio ";STASPECT;" to 1" 7400 print " Span ";STSPANT 8000 rem Do we do pitch calculation PRINTS 8020 If QPITCH$ <> "Y" and QPITCH$ <> "y" then goto 9000 8040 print\print 8060 print "The pitch stability summary is:" 8080 print " Effective Tail Volume Factor ";TVFAC 8100 if TVFAC >= YINTERSECT then print " Model WILL be stable in Pitch" 8110 goto 9000 8120 print "Model WILL !!NOT!! be stable in Pitch" 8140 print "In order for Model to be stable the " 8160 print "Effective Tail Volume Factor would have to be ";YINTERSECT 9000 rem
1205.2	I made two misteaks	CSC32::M_ANTRY		`Tue May 01 1990 14:58`	16
	Gee I am crushed that noone has been using this program...Boo Hoo... Oh well. Anyway, I found two errors in the program, please make the following changes. NEW 5420 WLOAD = WEIGHT / (WAREA / 144) OLD 5420 WLOAD = WAREA / WEIGHT NEW 6130 print " Wing Loading ";WLOAD;" oz/sq foot" OLD 6130 print " Wing Loading ";WLOAD;" oz/sq inch" Sorry about the goof!
1205.3	I did	SALEM::PISTEY		`Tue May 01 1990 15:37`	6
	I noticed the mistakes, but since I have a program that does the same thing (IBM basic) I figured it out (last night actually) kevin p
1205.4	Thankx for the bug-fix	HAMPS::WARWICK_B	Stay young -- keep your wheels in motion	`Wed May 02 1990 14:48`	10
	I have a copy of your program -- thankx. I have not used it yet as I am on one of those stupid ALL-IN-1 captive clusters and I find it difficult to get to compilers. Don't be discouraged -- I'm sure someone will be glad of your program someday. Brian
1205.5	ModelCad????	CXDOCS::TAVARES	Have Pen, Will Travel	`Thu Nov 11 1993 15:25`	3
	Could've sworn there was a topic in here on ModelCad...but if there isn't one, does anybody use it and can give some feedback. If there is a discussion on it, just point me there and thank you.
1205.6		TINCUP::OSWALD	TANSTAAFL!	`Thu Nov 11 1993 20:42`	7
	John, It used to be here 'cause I replied to it. Don't waste your time with modelcad. Spend the buck$ and get DesignCad 2D. Its by the same company, but has all of the features that you'll wish you had after about 40 hours of working with Modelcad. Randy