[coefficients] Removing xcpLon and xcpLat from plots

simulator/mainSimulator.m

@@ -90,5 +90,5 @@ toc(tStart)
 
 if settings.simulator.prints, prints(ascent, descent, environment); end
 if settings.simulator.plots, stdPlots(ascent, descent, rocket, environment, settings); end
-if settings.simulator.SMonly, designPlots(ascent, descent, rocket, environment, settings); end
+%if settings.simulator.SMonly, designPlots(ascent, descent, rocket, environment, settings); end
 end
\ No newline at end of file

simulator/src/prints.m

@@ -67,9 +67,9 @@ maxTemperature = (externalTemp*(1+(((gamma-1)/2)*(mach(iMaxV)^2))))-273.15;
 % end
 
 % longitudinal XCPs
-lonXCPs = -ascent.coeff.XCPlon(~isnan(ascent.coeff.XCPlon));
-latXCPs = -ascent.coeff.XCPlat(~isnan(ascent.coeff.XCPlat));
-totXCPs = ascent.coeff.XCPtot(~isnan(ascent.coeff.XCPtot));
+% lonXCPs = -ascent.coeff.XCPlon(~isnan(ascent.coeff.XCPlon));
+% latXCPs = -ascent.coeff.XCPlat(~isnan(ascent.coeff.XCPlat));
+totXCPs = ascent.coeff.xcp(~isnan(ascent.coeff.xcp));
 
 % DATA RECORD (display)
 disp(' ')
@@ -101,7 +101,8 @@ fprintf('speed at launch pad exit: %g [m/s] \n', absV(iExit))
 % else
 %     fprintf('Stability margin at launchpad exit [-]:\n Lon: %g\n Lat: %g\n Tot: %g\n', lonXCPs(1), latXCPs(1), totXCPs(1))
 % end
-fprintf('Stability margin at launchpad exit [-]:\n Lon: %g\n Lat: %g\n Tot: %g\n', lonXCPs(1), latXCPs(1), totXCPs(1))
+% fprintf('Stability margin at launchpad exit [-]:\n Lon: %g\n Lat: %g\n Tot: %g\n', lonXCPs(1), latXCPs(1), totXCPs(1))
+fprintf('Stability margin at launchpad exit [-]:\n Lon: %g\n Lat: %g\n Tot: %g\n', totXCPs(1))
 fprintf('time: %g [sec] \n\n', time(iExit))
 
 fprintf('latitude of landing point: %10.8f [deg] \n', lat(end));