【matlab】【Datcom】气动解算软件win10报错解决办法及运行交互示例
2024-04-03 03:54:15
版本说明
免费版本仍然可用。尚未使用Datcom + Pro版本的功能进行更新。没有大量的工作，我无法生成新的分发程序包，并且我现在对此不感兴趣。建议您观看教程视频，以了解使用新的Datcom + Pro有多么容易。 您将看到这个新软件包的功能强大，并节省了免费版本的时间。您会发现， 与免费版本相比，使用Datcom + Pro软件包更有效。
一旦安装，运行DATCOM +或DATCOM + Pro程序，你只要在DATCOM一个输入文件双击（用。DCM在Examples目录扩展名）。如果仅尝试单独运行digdat.exe程序，它将无法正确运行，并显示错误消息，例如“打开：没有这样的文件或目录”和“表观状态：名为for005.dat的单元5”。
WIN10报错解决办法
一些在Windows 10下运行免费版Datcom +的用户报告了问题，当他们双击.DCM文件时出现一条消息，提示“文件中存在错误：Citation.dcm ”，但并非所有用户都遇到此问题。我还没有弄清楚什么时候被触发的。如果您遇到这种情况，请按照下列步骤操作：
安装Datcom +软件包后，按Windows键+ r。键入“ SystemPropertiesAdvanced.exe”。
单击环境变量框。
更改DATCOMROOT的环境变量，删除前导和尾随双引号。保存并摆脱困境。
在桌面上的Datcom \ bin目录中，编辑Datcom.bat文件。在第14、15和16行上，删除双引号（前导和尾随）。
设置 PREDAT_PROGRAM = “ predat ”
设置 DATCOM_PROGRAM = “ digdat ”
集 DATCOM_MODELER_PROGRAM = “ DATCOM -modeler ”
- 您现在应该可以运行程序了。
手册
这些是Datcom原始手册的PDF文件，Digital Datcom程序基于3070页的方程式和方法。并非所有纸质手册都在计算机程序中表示。
DATCOM 1978年的完整手册（3070页，76 Meg）
安装及运行截图
ASW-20运行输出
THIS SOFTWARE AND ANY ACCOMPANYING DOCUMENTATIONIS RELEASED "AS IS". THE U.S. GOVERNMENT MAKES NOWARRANTY OF ANY KIND, EXPRESS OR IMPLIED, CONCERNINGTHIS SOFTWARE AND ANY ACCOMPANYING DOCUMENTATION,INCLUDING, WITHOUT LIMITATION, ANY WARRANTIES OFMERCHANTABILITY OR FITNESS FOR A PARTICULAR PURPOSE.IN NO EVENT WILL THE U.S. GOVERNMENT BE LIABLE FOR ANYDAMAGES, INCLUDING LOST PROFITS, LOST SAVINGS OR OTHERINCIDENTAL OR CONSEQUENTIAL DAMAGES ARISING OUT OF THE USE, OR INABILITY TO USE, THIS SOFTWARE OR ANYACCOMPANYING DOCUMENTATION, EVEN IF INFORMED IN ADVANCEOF THE POSSIBILITY OF SUCH DAMAGES.***************************************************** USAF STABILITY AND CONTROL DIGITAL DATCOM ** PROGRAM REV. JAN 96 DIRECT INQUIRIES TO: ** WRIGHT LABORATORY (WL/FIGC) ATTN: W. BLAKE ** WRIGHT PATTERSON AFB, OHIO 45433 ** PHONE (513) 255-6764, FAX (513) 258-4054 *****************************************************
1 CONERR - INPUT ERROR CHECKING
0 ERROR CODES - N* DENOTES THE NUMBER OF OCCURENCES OF EACH ERROR
0 A - UNKNOWN VARIABLE NAME
0 B - MISSING EQUAL SIGN FOLLOWING VARIABLE NAME
0 C - NON-ARRAY VARIABLE HAS AN ARRAY ELEMENT DESIGNATION - (N)
0 D - NON-ARRAY VARIABLE HAS MULTIPLE VALUES ASSIGNED
0 E - ASSIGNED VALUES EXCEED ARRAY DIMENSION
0 F - SYNTAX ERROR0****************************** INPUT DATA CARDS ******************************$FLTCON NMACH=1.,MACH=.1,VINF=100.,TINF(1)=511.57,RNNUB(1)=.624E6, NALPHA=5.,ALSCHD(1)=-2.,0.,1.,2.,4.,NALT=1.,ALT(1)=1000., GAMMA=0.,PINF=1967.6$ $OPTINS BLREF=24.60,SREF=113.0,CBARR=2.554$ $SYNTHS XW=7.236,ZW=.958,XH=21.494,ZH=4.256,XCG=9.045,ZCG=.532, ZV=0.0,XV=20.324,ALIW=0.,ALIH=0.$ $BODY NX=20.0,ITYPE=1.0,BNOSE=2.,BTAIL=2., X(1)=0.,0.638,1.383,2.075,2.788,3.458,4.150,4.895,5.533,6.278,6.917, 7.661,8.406,9.790,11.173,11.918,12.556,13.993,14.684,22.400, R(1)=0.053,.292,.532,.718,.824,.931,1.010,1.064,1.090,1.090,1.064, .984,.904,.771,.665,.631,.596,.562,.528,.186, ZU(1)=.085,.479,.798,1.100,1.330,1.543,1.702,1.808,1.883,1.926, 1.883,1.862,1.755,1.543,1.321,1.219,1.102,.957,.883,.160, ZL(1)=-.021,-.319,-.532,-.691,-.809,-.904,-.957,-1.01,-1.01,-.957, -.872,-.745,-.638,-.479,-.340,-.287,-.234,-.160,-.16,-.212$ $WGPLNF CHRDR=2.897,CHRDTP=1.249,CHRDBP=2.247,SSPN=24.67,SSPNOP=9.089, DHDADI=3.,DHDADO=3.,CHSTAT=.25,TWISTA=0.,SSPNDD=9.089,TYPE=1., SSPNE=23.67,SAVSI=0.,SAVSO=0.$ $SYMFLP FTYPE=1.0,NDELTA=9.0,DELTA(1)=-40.,-30.,-20.,-10.,0.,10.,20.,30., 40.,SPANFI=.0,SPANFO=9.089,CHRDFI=.532,CHRDFO=.372,NTYPE=1.0, CB=.452,TC=.20,PHETE=.003,PHETEP=.002$ $VTPLNF CHRDR=3.322,CHRDTP=2.039,SAVSI=14.,SSPN=4.243,SSPNOP=0., SSPNE=4.1,CHRDBP=0.,SAVSO=0.,CHSTAT=.25,TYPE=1.,SVWB=18., SVB=9.,SVHB=1.$ $HTPLNF CHRDR=1.809,CHRDTP=1.171,SSPN=3.618,SAVSI=4., SSPNE=3.400,CHSTAT=.25,TWISTA=0., DHDADI=0.,TYPE=1.,DHDADO=0.$ NACA-W-6-643-212 NACA-H-6-631-012 NACA-V-6-631-012 DAMP DERIV RAD PART CASEID TOTAL: TOTAL: ASW-20 Sailplane
1 THE FOLLOWING IS A LIST OF ALL INPUT CARDS FOR THIS CASE.
0$FLTCON NMACH=1.,MACH=.1,VINF=100.,TINF(1)=511.57,RNNUB(1)=.624E6, NALPHA=5.,ALSCHD(1)=-2.,0.,1.,2.,4.,NALT=1.,ALT(1)=1000., GAMMA=0.,PINF=1967.6$ $OPTINS BLREF=24.60,SREF=113.0,CBARR=2.554$ $SYNTHS XW=7.236,ZW=.958,XH=21.494,ZH=4.256,XCG=9.045,ZCG=.532, ZV=0.0,XV=20.324,ALIW=0.,ALIH=0.$ $BODY NX=20.0,ITYPE=1.0,BNOSE=2.,BTAIL=2., X(1)=0.,0.638,1.383,2.075,2.788,3.458,4.150,4.895,5.533,6.278,6.917, 7.661,8.406,9.790,11.173,11.918,12.556,13.993,14.684,22.400, R(1)=0.053,.292,.532,.718,.824,.931,1.010,1.064,1.090,1.090,1.064, .984,.904,.771,.665,.631,.596,.562,.528,.186, ZU(1)=.085,.479,.798,1.100,1.330,1.543,1.702,1.808,1.883,1.926, 1.883,1.862,1.755,1.543,1.321,1.219,1.102,.957,.883,.160, ZL(1)=-.021,-.319,-.532,-.691,-.809,-.904,-.957,-1.01,-1.01,-.957, -.872,-.745,-.638,-.479,-.340,-.287,-.234,-.160,-.16,-.212$ $WGPLNF CHRDR=2.897,CHRDTP=1.249,CHRDBP=2.247,SSPN=24.67,SSPNOP=9.089, DHDADI=3.,DHDADO=3.,CHSTAT=.25,TWISTA=0.,SSPNDD=9.089,TYPE=1., SSPNE=23.67,SAVSI=0.,SAVSO=0.$ $SYMFLP FTYPE=1.0,NDELTA=9.0,DELTA(1)=-40.,-30.,-20.,-10.,0.,10.,20.,30., 40.,SPANFI=.0,SPANFO=9.089,CHRDFI=.532,CHRDFO=.372,NTYPE=1.0, CB=.452,TC=.20,PHETE=.003,PHETEP=.002$ $VTPLNF CHRDR=3.322,CHRDTP=2.039,SAVSI=14.,SSPN=4.243,SSPNOP=0., SSPNE=4.1,CHRDBP=0.,SAVSO=0.,CHSTAT=.25,TYPE=1.,SVWB=18., SVB=9.,SVHB=1.$ $HTPLNF CHRDR=1.809,CHRDTP=1.171,SSPN=3.618,SAVSI=4., SSPNE=3.400,CHSTAT=.25,TWISTA=0., DHDADI=0.,TYPE=1.,DHDADO=0.$ NACA-W-6-643-212 NACA-H-6-631-012 NACA-V-6-631-012 DAMP DERIV RAD PART CASEID TOTAL: TOTAL: ASW-20 Sailplane
0ERROR ** FLAP INBOARD SPAN, SPANI = .00000E+00, IT IS INSIDE THE BODY AS DEFINED BY SSPN AND SSPNESPANI IS REDEFINED, SPANI = SSPN-SSPNE = .21800E+000 INPUT DIMENSIONS ARE IN FT, SCALE FACTOR IS 1.00001 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM WING SECTION DEFINITIONNACA 64,3-212UPPER ABSCISSA UPPER ORDINATE LOWER ABSCISSA LOWER ORDINATE X-FRACTION CHORD MEAN LINE THICKNESS.00000 .00000 .00000 .00000 .00000 .00000 .00000.00053 .00443 .00147 -.00418 .00100 .00013 .00865.00141 .00624 .00259 -.00579 .00200 .00023 .01209.00233 .00763 .00367 -.00698 .00300 .00033 .01467.00327 .00878 .00473 -.00795 .00400 .00042 .01680.00422 .00979 .00578 -.00879 .00500 .00050 .01865.00518 .01070 .00682 -.00954 .00600 .00058 .02030.00614 .01153 .00786 -.01020 .00700 .00066 .02180.00711 .01230 .00889 -.01082 .00800 .00074 .02319.00809 .01302 .00991 -.01138 .00900 .00082 .02447.00906 .01369 .01094 -.01191 .01000 .00089 .02567.01892 .01902 .02108 -.01590 .02000 .00156 .03498.02885 .02297 .03115 -.01868 .03000 .00214 .04171.03881 .02622 .04119 -.02088 .04000 .00267 .04716.04879 .02905 .05121 -.02273 .05000 .00316 .05184.05878 .03158 .06122 -.02436 .06000 .00361 .05599.06877 .03390 .07123 -.02582 .07000 .00404 .05977.07877 .03605 .08123 -.02718 .08000 .00444 .06327.08878 .03807 .09122 -.02844 .09000 .00482 .06655.09878 .03998 .10122 -.02963 .10000 .00517 .06966.10879 .04181 .11121 -.03078 .11000 .00551 .07262.11880 .04355 .12120 -.03187 .12000 .00584 .07546.12882 .04523 .13118 -.03293 .13000 .00615 .07820.13883 .04685 .14117 -.03396 .14000 .00645 .08085.14885 .04842 .15115 -.03496 .15000 .00673 .08341.15887 .04993 .16113 -.03594 .16000 .00700 .08590.16889 .05140 .17111 -.03689 .17000 .00726 .08831.17891 .05282 .18109 -.03781 .18000 .00750 .09065.18893 .05419 .19107 -.03871 .19000 .00774 .09293.19895 .05552 .20105 -.03959 .20000 .00796 .09513.20897 .05680 .21103 -.04044 .21000 .00818 .09727.21900 .05804 .22100 -.04127 .22000 .00839 .09933.22903 .05923 .23097 -.04207 .23000 .00858 .10132.23905 .06038 .24095 -.04284 .24000 .00877 .10323.24908 .06148 .25092 -.04358 .25000 .00895 .10507.25911 .06252 .26089 -.04428 .26000 .00912 .10682.26914 .06352 .27086 -.04495 .27000 .00928 .10848.27917 .06446 .28083 -.04558 .28000 .00944 .11005.28921 .06534 .29079 -.04618 .29000 .00958 .11153.29924 .06617 .30076 -.04673 .30000 .00972 .11291.34942 .06935 .35058 -.04875 .35000 .01030 .11811.39961 .07071 .40039 -.04929 .40000 .01071 .12000.44981 .06999 .45019 -.04809 .45000 .01095 .11808.50000 .06739 .50000 -.04533 .50000 .01103 .11272.55017 .06320 .54983 -.04130 .55000 .01095 .10450.60030 .05772 .59970 -.03630 .60000 .01071 .09403.65040 .05125 .64960 -.03064 .65000 .01030 .08189.70046 .04405 .69954 -.02461 .70000 .00972 .06867.75048 .03643 .74952 -.01853 .75000 .00895 .05497.80046 .02865 .79954 -.01272 .80000 .00796 .04139.82044 .02556 .81956 -.01055 .82000 .00750 .03612.84041 .02249 .83959 -.00849 .84000 .00700 .03100.86038 .01947 .85962 -.00658 .86000 .00645 .02606.88034 .01651 .87966 -.00483 .88000 .00584 .02136.90030 .01363 .89970 -.00328 .90000 .00517 .01692.92025 .01082 .91975 -.00195 .92000 .00444 .01278.94020 .00810 .93980 -.00087 .94000 .00361 .00898.96014 .00545 .95986 -.00010 .96000 .00267 .00556.98008 .00283 .97992 .00029 .98000 .00156 .002551.00000 .00000 1.00000 .00000 1.00000 .00000 .00000
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM WING SECTION DEFINITION
0 IDEAL ANGLE OF ATTACK = .00000 DEG.ZERO LIFT ANGLE OF ATTACK = -1.56111 DEG.IDEAL LIFT COEFFICIENT = .20000ZERO LIFT PITCHING MOMENT COEFFICIENT = -.04398MACH ZERO LIFT-CURVE-SLOPE = .10116 /DEG.LEADING EDGE RADIUS = .00993 FRACTION CHORDMAXIMUM AIRFOIL THICKNESS = .12000 FRACTION CHORDDELTA-Y = 2.28110 PERCENT CHORD0 MACH= .1000 LIFT-CURVE-SLOPE = .10428 /DEG. XAC = .26132
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM HORIZONTAL TAIL SECTION DEFINITIONNACA 63,1-012UPPER ABSCISSA UPPER ORDINATE LOWER ABSCISSA LOWER ORDINATE X-FRACTION CHORD MEAN LINE THICKNESS.00000 .00000 .00000 .00000 .00000 .00000 .00000.00100 .00440 .00100 -.00440 .00100 .00000 .00880.00200 .00619 .00200 -.00619 .00200 .00000 .01239.00300 .00756 .00300 -.00756 .00300 .00000 .01511.00400 .00870 .00400 -.00870 .00400 .00000 .01739.00500 .00969 .00500 -.00969 .00500 .00000 .01939.00600 .01059 .00600 -.01059 .00600 .00000 .02118.00700 .01141 .00700 -.01141 .00700 .00000 .02283.00800 .01217 .00800 -.01217 .00800 .00000 .02435.00900 .01289 .00900 -.01289 .00900 .00000 .02577.01000 .01356 .01000 -.01356 .01000 .00000 .02711.02000 .01887 .02000 -.01887 .02000 .00000 .03775.03000 .02284 .03000 -.02284 .03000 .00000 .04569.04000 .02612 .04000 -.02612 .04000 .00000 .05224.05000 .02896 .05000 -.02896 .05000 .00000 .05791.06000 .03148 .06000 -.03148 .06000 .00000 .06296.07000 .03376 .07000 -.03376 .07000 .00000 .06752.08000 .03586 .08000 -.03586 .08000 .00000 .07171.09000 .03779 .09000 -.03779 .09000 .00000 .07559.10000 .03960 .10000 -.03960 .10000 .00000 .07920.11000 .04129 .11000 -.04129 .11000 .00000 .08258.12000 .04287 .12000 -.04287 .12000 .00000 .08575.13000 .04437 .13000 -.04437 .13000 .00000 .08874.14000 .04578 .14000 -.04578 .14000 .00000 .09155.15000 .04710 .15000 -.04710 .15000 .00000 .09421.16000 .04836 .16000 -.04836 .16000 .00000 .09672.17000 .04954 .17000 -.04954 .17000 .00000 .09909.18000 .05066 .18000 -.05066 .18000 .00000 .10132.19000 .05171 .19000 -.05171 .19000 .00000 .10342.20000 .05270 .20000 -.05270 .20000 .00000 .10539.21000 .05362 .21000 -.05362 .21000 .00000 .10724.22000 .05448 .22000 -.05448 .22000 .00000 .10896.23000 .05528 .23000 -.05528 .23000 .00000 .11056.24000 .05602 .24000 -.05602 .24000 .00000 .11204.25000 .05670 .25000 -.05670 .25000 .00000 .11339.26000 .05731 .26000 -.05731 .26000 .00000 .11462.27000 .05787 .27000 -.05787 .27000 .00000 .11573.28000 .05836 .28000 -.05836 .28000 .00000 .11672.29000 .05879 .29000 -.05879 .29000 .00000 .11758.30000 .05915 .30000 -.05915 .30000 .00000 .11831.35000 .06000 .35000 -.06000 .35000 .00000 .12000.40000 .05917 .40000 -.05917 .40000 .00000 .11834.45000 .05684 .45000 -.05684 .45000 .00000 .11368.50000 .05324 .50000 -.05324 .50000 .00000 .10648.55000 .04862 .55000 -.04862 .55000 .00000 .09724.60000 .04321 .60000 -.04321 .60000 .00000 .08641.65000 .03724 .65000 -.03724 .65000 .00000 .07448.70000 .03096 .70000 -.03096 .70000 .00000 .06193.75000 .02461 .75000 -.02461 .75000 .00000 .04922.80000 .01841 .80000 -.01841 .80000 .00000 .03683.82000 .01604 .82000 -.01604 .82000 .00000 .03207.84000 .01374 .84000 -.01374 .84000 .00000 .02747.86000 .01153 .86000 -.01153 .86000 .00000 .02306.88000 .00943 .88000 -.00943 .88000 .00000 .01887.90000 .00746 .90000 -.00746 .90000 .00000 .01492.92000 .00563 .92000 -.00563 .92000 .00000 .01126.94000 .00395 .94000 -.00395 .94000 .00000 .00790.96000 .00244 .96000 -.00244 .96000 .00000 .00489.98000 .00112 .98000 -.00112 .98000 .00000 .002241.00000 .00000 1.00000 .00000 1.00000 .00000 .00000
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM HORIZONTAL TAIL SECTION DEFINITION
0 IDEAL ANGLE OF ATTACK = .00000 DEG.ZERO LIFT ANGLE OF ATTACK = .00000 DEG.IDEAL LIFT COEFFICIENT = .00000ZERO LIFT PITCHING MOMENT COEFFICIENT = .00000MACH ZERO LIFT-CURVE-SLOPE = .10244 /DEG.LEADING EDGE RADIUS = .00993 FRACTION CHORDMAXIMUM AIRFOIL THICKNESS = .12000 FRACTION CHORDDELTA-Y = 2.61808 PERCENT CHORD0 MACH= .1000 LIFT-CURVE-SLOPE = .10229 /DEG. XAC = .25883
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM VERTICAL TAIL SECTION DEFINITIONNACA 63,1-012UPPER ABSCISSA UPPER ORDINATE LOWER ABSCISSA LOWER ORDINATE X-FRACTION CHORD MEAN LINE THICKNESS.00000 .00000 .00000 .00000 .00000 .00000 .00000.00100 .00440 .00100 -.00440 .00100 .00000 .00880.00200 .00619 .00200 -.00619 .00200 .00000 .01239.00300 .00756 .00300 -.00756 .00300 .00000 .01511.00400 .00870 .00400 -.00870 .00400 .00000 .01739.00500 .00969 .00500 -.00969 .00500 .00000 .01939.00600 .01059 .00600 -.01059 .00600 .00000 .02118.00700 .01141 .00700 -.01141 .00700 .00000 .02283.00800 .01217 .00800 -.01217 .00800 .00000 .02435.00900 .01289 .00900 -.01289 .00900 .00000 .02577.01000 .01356 .01000 -.01356 .01000 .00000 .02711.02000 .01887 .02000 -.01887 .02000 .00000 .03775.03000 .02284 .03000 -.02284 .03000 .00000 .04569.04000 .02612 .04000 -.02612 .04000 .00000 .05224.05000 .02896 .05000 -.02896 .05000 .00000 .05791.06000 .03148 .06000 -.03148 .06000 .00000 .06296.07000 .03376 .07000 -.03376 .07000 .00000 .06752.08000 .03586 .08000 -.03586 .08000 .00000 .07171.09000 .03779 .09000 -.03779 .09000 .00000 .07559.10000 .03960 .10000 -.03960 .10000 .00000 .07920.11000 .04129 .11000 -.04129 .11000 .00000 .08258.12000 .04287 .12000 -.04287 .12000 .00000 .08575.13000 .04437 .13000 -.04437 .13000 .00000 .08874.14000 .04578 .14000 -.04578 .14000 .00000 .09155.15000 .04710 .15000 -.04710 .15000 .00000 .09421.16000 .04836 .16000 -.04836 .16000 .00000 .09672.17000 .04954 .17000 -.04954 .17000 .00000 .09909.18000 .05066 .18000 -.05066 .18000 .00000 .10132.19000 .05171 .19000 -.05171 .19000 .00000 .10342.20000 .05270 .20000 -.05270 .20000 .00000 .10539.21000 .05362 .21000 -.05362 .21000 .00000 .10724.22000 .05448 .22000 -.05448 .22000 .00000 .10896.23000 .05528 .23000 -.05528 .23000 .00000 .11056.24000 .05602 .24000 -.05602 .24000 .00000 .11204.25000 .05670 .25000 -.05670 .25000 .00000 .11339.26000 .05731 .26000 -.05731 .26000 .00000 .11462.27000 .05787 .27000 -.05787 .27000 .00000 .11573.28000 .05836 .28000 -.05836 .28000 .00000 .11672.29000 .05879 .29000 -.05879 .29000 .00000 .11758.30000 .05915 .30000 -.05915 .30000 .00000 .11831.35000 .06000 .35000 -.06000 .35000 .00000 .12000.40000 .05917 .40000 -.05917 .40000 .00000 .11834.45000 .05684 .45000 -.05684 .45000 .00000 .11368.50000 .05324 .50000 -.05324 .50000 .00000 .10648.55000 .04862 .55000 -.04862 .55000 .00000 .09724.60000 .04321 .60000 -.04321 .60000 .00000 .08641.65000 .03724 .65000 -.03724 .65000 .00000 .07448.70000 .03096 .70000 -.03096 .70000 .00000 .06193.75000 .02461 .75000 -.02461 .75000 .00000 .04922.80000 .01841 .80000 -.01841 .80000 .00000 .03683.82000 .01604 .82000 -.01604 .82000 .00000 .03207.84000 .01374 .84000 -.01374 .84000 .00000 .02747.86000 .01153 .86000 -.01153 .86000 .00000 .02306.88000 .00943 .88000 -.00943 .88000 .00000 .01887.90000 .00746 .90000 -.00746 .90000 .00000 .01492.92000 .00563 .92000 -.00563 .92000 .00000 .01126.94000 .00395 .94000 -.00395 .94000 .00000 .00790.96000 .00244 .96000 -.00244 .96000 .00000 .00489.98000 .00112 .98000 -.00112 .98000 .00000 .002241.00000 .00000 1.00000 .00000 1.00000 .00000 .00000
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM VERTICAL TAIL SECTION DEFINITION
0 IDEAL ANGLE OF ATTACK = .00000 DEG.ZERO LIFT ANGLE OF ATTACK = .00000 DEG.IDEAL LIFT COEFFICIENT = .00000ZERO LIFT PITCHING MOMENT COEFFICIENT = .00000MACH ZERO LIFT-CURVE-SLOPE = .10244 /DEG.LEADING EDGE RADIUS = .00993 FRACTION CHORDMAXIMUM AIRFOIL THICKNESS = .12000 FRACTION CHORDDELTA-Y = 2.61808 PERCENT CHORD0 MACH= .1000 LIFT-CURVE-SLOPE = .10631 /DEG. XAC = .25849WARNING*** BODY ALONE DYNAMIC DERIVATIVE METHOD VALID FOR NOSE CYLINDER ONLYTAIL EFFECTS IGNORED]
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOMCHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIPWING-BODY-VERTICAL TAIL-HORIZONTAL TAIL CONFIGURATIONTOTAL: TOTAL: ASW-20 Sailplane----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTERNUMBER NUMBER AREA LONG. LAT. HORIZ VERTFT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT
0 .100 1000.00 110.87 1.9676E+03 511.570 6.2400E+05 113.000 2.554 24.600 9.045 .532
0 -------------------DERIVATIVE (PER RADIAN)-------------------
0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB
0-2.0 .016 -.057 .0308 -.057 .014 -.537 5.922E+00 8.846E-01 -4.192E-01 1.133E-01 -2.133E-01.0 .016 .154 .0610 .154 .016 .397 6.138E+00 8.904E-01 -2.101E-011.0 .017 .262 .0768 .262 .013 .293 6.244E+00 9.066E-01 -2.086E-012.0 .018 .372 .0927 .372 .005 .249 6.342E+00 8.936E-01 -2.070E-014.0 .023 .596 .1227 .596 -.019 .206 6.527E+00 8.246E-01 -2.040E-01
0 ALPHA Q/QINF EPSLON D(EPSLON)/D(ALPHA)
0-2.0 1.000 -.088 .203.0 1.000 .317 .2061.0 1.000 .524 .2082.0 1.000 .734 .2114.0 1.000 1.161 .213
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOMDYNAMIC DERIVATIVESWING-BODY-VERTICAL TAIL-HORIZONTAL TAIL CONFIGURATIONTOTAL: TOTAL: ASW-20 Sailplane----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTERNUMBER NUMBER AREA LONG. LAT. HORIZ VERTFT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT
0 .100 1000.00 110.87 1.9676E+03 511.570 6.2400E+05 113.000 2.554 24.600 9.045 .532DYNAMIC DERIVATIVES (PER RADIAN)
0 -------PITCHING------- -----ACCELERATION------ --------------ROLLING-------------- --------YAWING--------
0 ALPHA CLQ CMQ CLAD CMAD CLP CYP CNP CNR CLR
0-2.00 2.171E+00 -2.199E+01 8.487E-01 -4.333E+00 -1.991E+00 -1.564E-01 2.631E-02 -1.620E-01 1.224E-02.00 8.607E-01 -4.394E+00 -2.071E+00 -1.949E-01 -7.571E-02 -1.653E-01 5.334E-021.00 8.727E-01 -4.456E+00 -2.111E+00 -2.149E-01 -1.280E-01 -1.694E-01 7.455E-022.00 8.833E-01 -4.510E+00 -2.147E+00 -2.353E-01 -1.812E-01 -1.754E-01 9.615E-024.00 8.924E-01 -4.557E+00 -2.216E+00 -2.772E-01 -2.896E-01 -1.930E-01 1.404E-01
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOMCONFIGURATION AUXILIARY AND PARTIAL OUTPUTWING-BODY-VERTICAL TAIL-HORIZONTAL TAIL CONFIGURATIONTOTAL: TOTAL: ASW-20 Sailplane----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTERNUMBER NUMBER AREA LONG. LAT. HORIZ VERTFT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT
0 .100 1000.00 110.87 1.9676E+03 511.570 6.2400E+05 113.000 2.554 24.600 9.045 .532BASIC BODY PROPERTIESWETTED AREA XCG ZCG BASE AREA ZERO LIFT DRAG BASE DRAG FRICTION DRAG PRESSURE DRAG.8814E+02 9.05 .53 1.1198 .2977E-02 .5848E-03 .2393E-02 NA XCG RELATIVE TO THEORETICAL LEADING EDGE MAC= 1.68BASIC PLANFORM PROPERTIESTAPER ASPECT QUARTER CHORD QUARTER CHORD ZERO LIFT FRICTIONAREA RATIO RATIO SWEEP MAC X(MAC) Y(MAC) DRAG COEFFICIENT
0 WINGTOTAL THEORITICAL
+ .1119E+03 .431 .2175E+02 NDM .236E+01 .796E+01 .109E+02 TOTAL EXPOSED
+ .1062E+03 .437 .2111E+02 NDM .233E+01 .797E+01 .115E+02 .972E-02 .415E-02
0 HORIZONTAL TAILTOTAL THEORITICAL
+ .1078E+02 .647 .4856E+01 4.000 .151E+01 .221E+02 .168E+01 TOTAL EXPOSED
+ .1000E+02 .661 .4623E+01 4.000 .149E+01 .221E+02 .180E+01 .993E-03 .450E-02
0 VERTICAL TAILTOTAL THEORITICAL
+ .1137E+02 .614 .1583E+01 14.000 .273E+01 .216E+02 .195E+01 TOTAL EXPOSED
+ .1090E+02 .622 .1542E+01 14.000 .271E+01 .217E+02 .203E+01 .967E-03 .404E-02
0*** NDM PRINTED WHEN NO DATCOM METHODS EXIST
0*** NA PRINTED WHEN METHOD NOT APPLICABLE
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOMCONFIGURATION AUXILIARY AND PARTIAL OUTPUTWING-BODY-VERTICAL TAIL-HORIZONTAL TAIL CONFIGURATIONTOTAL: TOTAL: ASW-20 Sailplane----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTERNUMBER NUMBER AREA LONG. LAT. HORIZ VERTFT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT
0 .100 1000.00 110.87 1.9676E+03 511.570 6.2400E+05 113.000 2.554 24.600 9.045 .532
0 CLA-B(W)= 4.718E-03 CLA-W(B)= 9.244E-02 K-B(W)= 5.270E-02 K-W(B)= 1.032E+00 XAC/C-B(W)= 2.795E-01
0 CLA-B(H)= 4.975E-04 CLA-H(B)= 6.657E-03 K-B(H)= 7.833E-02 K-H(B)= 1.048E+00 XAC/C-B(H)= 1.838E-01
0 SIDEWASH, (1 + D(SIGMA)/D(BETA))QV/Q = 9.4277376E-01ALPHA IV-B(W) IV-W(H) IV-B(H) GAMMA/ GAMMA/2*PI*ALPHA*V*R (2*PI*ALPHA*V*R)T-2.000 .0000E+00 -.3809E+00 .0000E+00 .0000E+00 .0000E+00.000 .0000E+00 -.3844E+00 .0000E+00 .0000E+00 .0000E+001.000 .0000E+00 -.3860E+00 .0000E+00 .0000E+00 .0000E+002.000 .0000E+00 -.3875E+00 .0000E+00 .0000E+00 .0000E+004.000 .0000E+00 -.3902E+00 .0000E+00 .0000E+00 .0000E+00DYNAMIC DERIVATIVE INCREMENTALSCLP(GAMMA=CL=0) =-5.0319E-01 CLP(GAMMA)/CLP (GAMMA=0) = 9.9819E-01 CNP/THETA = 1.9629E-03CYP/GAMMA =-7.8861E-02 CYP/CL (CL=0) =-1.3902E-01CLB/GAMMA (CMO/THETA)W (CMO/THETA)HNA NA NA
0*** NA PRINTED WHEN METHOD NOT APPLICABLE
1
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOMCHARACTERISTICS OF HIGH LIFT AND CONTROL DEVICESTAIL PLAIN TRAILING-EDGE FLAP CONFIGURATIONTOTAL: TOTAL: ASW-20 Sailplane----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTERNUMBER NUMBER AREA LONG. LAT. HORIZ VERTFT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT
0 .100 1000.00 110.87 1.9676E+03 511.570 6.2400E+05 113.000 2.554 24.600 9.045 .532
0 ---------INCREMENTS DUE TO DEFLECTION--------- ---DERIVATIVES (PER DEGREE)---
0 DELTA D(CL) D(CM) D(CL MAX) D(CD MIN) (CLA)D (CH)A (CH)D-40.0 -.090 .4466 .130 .01812 NDM 6.651E-03 2.647E-02-30.0 -.076 .3741 .114 .01094 NDM 2.593E-02-20.0 -.066 .3214 .085 .00497 NDM 2.441E-02-10.0 -.043 .2192 .049 .00174 NDM 2.192E-02.0 .000 -.0002 .000 .00000 NDM 2.192E-0210.0 .043 -.2192 .049 .00174 NDM 2.192E-0220.0 .066 -.3214 .085 .00497 NDM 2.441E-0230.0 .076 -.3741 .114 .01094 NDM 2.593E-0240.0 .090 -.4467 .130 .01812 NDM 2.647E-02
0 *** NOTE * HINGE MOMENT DERIVATIVES ARE BASED ON TWICE THE AREA-MOMENT OF THE CONTROL ABOUT ITS HINGE LINE0 --------- INDUCED DRAG COEFFICIENT INCREMENT , D(CDI) , DUE TO DEFLECTION ---------
0 DELTA = -40.0 -30.0 -20.0 -10.0 .0 10.0 20.0 30.0 40.0ALPHA
0-2.0 6.35E-03 4.49E-03 3.36E-03 1.62E-03 -1.40E-07 1.34E-03 2.94E-03 4.01E-03 5.77E-03.0 5.05E-03 3.40E-03 2.42E-03 9.79E-04 5.03E-07 1.98E-03 3.88E-03 5.10E-03 7.07E-031.0 4.40E-03 2.86E-03 1.95E-03 6.59E-04 8.23E-07 2.30E-03 4.35E-03 5.64E-03 7.72E-032.0 3.75E-03 2.32E-03 1.49E-03 3.40E-04 1.14E-06 2.62E-03 4.81E-03 6.18E-03 8.37E-034.0 2.47E-03 1.24E-03 5.62E-04 -2.94E-04 1.78E-06 3.25E-03 5.74E-03 7.25E-03 9.65E-03
0***NDM PRINTED WHEN NO DATCOM METHODS EXIST
1 END OF JOB.matlab与dacom交互代码示例
% datcom软件接口测试
% 程序路径D:\OneDrive - 徐州开放大学\NPU\program\datcomexec\Data\exwin
% 采用下载好的示例.out文件
% Jun 22 2020 Mon Jonny Su
clc;
close all;
clear all;
cd ('D:\OneDrive - 徐州开放大学\NPU\program\Morphing\Datcom_cmd'); %切换至自己的目录下
path(path,'exwin') %修改文件的搜索路径
% 以下是USAF Digital DATCOM的示例输入文件，其机翼-水平-水平尾部-垂直尾部配置在五个alpha，
% 两个马赫数和两个高度上运行，并计算静态和动态导数。
type astdatcom.in
% USAF Digital DATCOM针对在5个alpha，两个Mach数和两个高度上运行的相同机翼-水平-水平尾部-垂直尾部配置生成的输出文件
type astdatcom.out% 使用datcomimport函数将Digital DATCOM数据带入MATLAB环境。
alldata = datcomimport('astdatcom.out', true, 0);
ex1data = datcomimport('ex1.out', true, 0);
data = alldata{1}; %数据提取
% 默认情况下，缺少的数据点设置为99999，而数据点设置为NaN在不存在DATCOM方法或该方法不适用的情况下。
% 可以在Digital DATCOM输出文件中看到并检查导入的数据，发现C仅在第一个alpha值中包含数据。 这是导入的数据值。
% data.cyb;% 丢失的数据点将使用第一个alpha值填充，因为这些数据点将用于所有alpha值。
% 替换示例
aerotab = {'cyb' 'cnb' 'clq' 'cmq'};for k = 1:length(aerotab)for m = 1:data.nmachfor h = 1:data.naltdata.(aerotab{k})(:,m,h) = data.(aerotab{k})(1,m,h);endend
end
% data.cyb; %这里已经被替换过了%绘图
%升力
h1 = figure;
figtitle = {'Lift Curve' ''};
for k=1:2subplot(2,1,k)plot(data.alpha,permute(data.cl(:,k,:),[1 3 2]),'linewidth',1.5)gridylabel(['Lift Coefficient (Mach =' num2str(data.mach(k)) ')'])
% ylabel('$C_{L_{\alpha, Ma}}$','FontName','Times New Roman','FontSize',14,'Interpreter','latex');title(figtitle{k});set(gca,'FontName','Times New Roman','FontSize',14,'linewidth',1.5);
end
% xlabel('$\alpha(^\circ)$','FontName','Times New Roman','FontSize',14,'Interpreter','latex')
xlabel('Angle of Attack (deg)')
%阻力
h2 = figure;
figtitle = {'Drag Polar' ''};
for k=1:2subplot(2,1,k)plot(permute(data.cd(:,k,:),[1 3 2]),permute(data.cl(:,k,:),[1 3 2]),'linewidth',1.5)gridylabel(['Lift Coefficient (Mach =' num2str(data.mach(k)) ')'])title(figtitle{k})set(gca,'FontName','Times New Roman','FontSize',14,'linewidth',1.5);
end
xlabel('Drag Coefficient')
%俯仰力矩
h3 = figure;
figtitle = {'Pitching Moment' ''};
for k=1:2subplot(2,1,k)plot(permute(data.cm(:,k,:),[1 3 2]),permute(data.cl(:,k,:),[1 3 2]),'linewidth',1.5)gridylabel(['Lift Coefficient (Mach =' num2str(data.mach(k)) ')'])title(figtitle{k})set(gca,'FontName','Times New Roman','FontSize',14,'linewidth',1.5);
end
xlabel('Pitching Moment Coefficient')
相关资源链接
Datcom_Windows_2.8.5.exe
exwin.zip
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