propeller.m

用MATLAB编写关于飞机设计的matlab程序

PropDemo=' (beta = 25 deg at 75 %)';    %  - a title for the prop
  N=9;                                   %- the number of spanwise data points
 %--------------r/R        c/R       t/c    blade angle
    propdata=[ 0.2121,     0.1255,     0.2802,    51.7943;	 %- r/R, c/R,t/c,blade angle (deg)
               0.3333,     0.1473,     0.1432,    38.9558;	     %- for each point along the blade
               0.3939,     0.1503,     0.1258,    34.3769;	     %- there must be at least 3 but no
               0.5152,     0.1469,     0.1073,    27.6164;	     %-more than 9 spanwise locations in
               0.5758,     0.1400,     0.1074,    25.0835;	     %-the data file
               0.6970,     0.1255,     0.1082,    21.1404;
               0.8182,     0.1006,     0.1108,    18.2315;
               0.8788,     0.0842,     0.1108,    17.0495;
               0.9394,     0.0576,     0.1074,    16.0076;];
 NB=2;                                      %- number of blades 
 Radius=6.5;                                %- radius (inches)
 pitch=11;                                   %- pitch  (inches)
 PROPNAME='13*11';
 %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%14*9.5%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
%  r/R=[0.2531    0.3656    0.4218    0.4781    0.5343    0.5906    0.6468    0.7030    0.7593    0.8155    0.8718    0.9280    0.9843]
 % c/R=[0.1485    0.1556    0.1504    0.1457    0.1414    0.1384    0.1339    0.1264    0.1214    0.1162    0.1069    0.0902    0.0728]
  %t/c=[0.1697,   0.1302,   0.1234,   0.1189,   0.1114,    0.1081,  0.1092 ,  0.1094,   0.1112,   0.1133,   0.1126,   0.1160 ,  0.1221]
 %Beta=[40.4782   30.5760   27.1149   24.3141   22.0112   20.0902   18.4667   17.0787   15.8797   14.8345   13.9158   13.1024   12.3775]

 %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%13*11%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 
% r/R=[0.2121    0.2727    0.3333    0.3939    0.4545    0.5152    0.5758    0.6364    0.6970    0.7576    0.8182    0.8788    0.9394];
% c/R=[0.1255    0.1400    0.1473    0.1503    0.1497    0.1469    0.1400    0.1339    0.1255    0.1133    0.1006    0.0842    0.0576];
 %t/c=[0.2802    0.1714    0.1432    0.1258    0.1117    0.1073    0.1074    0.1068    0.1082    0.1091    0.1108    0.1108    0.1074];
%beta=[51.7943   44.6592   38.9558   34.3769   30.6639   27.6164   25.0835   22.9528   21.1404   19.5827   18.2315   17.0495   16.0076];