def thrustpowerReq_compute(self):
try:
thrReq = acalculate()
cd = acalculate()
k = acalculate()
k = k.kFactor(wingspan=float(wingspan.text()), wingarea=float(wingarea.text()), oef=float(oef_db.value()))
cl = acalculate()
cl = cl.liftcoefficient_C(v=float(thrustpowerReq_vel.text()), weight=float(weight.text()), wingarea=float(wingarea.text()), rho=float(rho.text()))
cd = cd.dragcoefficient(cd0=float(cd0.text()), k=k, cl= cl)
thrReq = thrReq.thrustReq_C(v=float(thrustpowerReq_vel.text()), wingarea=float(wingarea.text()), rho=float(rho.text()), cd=cd)
thrustReq_edit.setText("""
<html>
<head/>
<body>
<p><span style=" font-size:14pt; color:#3465a4;">{0:.1f} N</span></p>
</body>
</html>""".format(thrReq))
powReq = acalculate()
powReq = powReq.powerReq_C(v=float(thrustpowerReq_vel.text()), wingarea=float(wingarea.text()), rho=float(rho.text()), cd=cd)
powerReq_edit.setText("""
<html>
<head/>
<body>
<p><span style=" font-size:14pt; color:#3465a4;">{0:.1f} W</span></p>
</body>
</html>""".format(powReq))
except (ValueError, ZeroDivisionError) as error:
if len(error.args) > 0 and error.args[0] == 'could not convert string to float: ':
self.showValueError()
else:
self.showZeroDivisionError()
def toandLandingData_compute(self):
try:
todistance = acalculate()
todistance = todistance.takeoffDistance(weight=float(weight.text()), wingspan=float(wingspan.text()), wingarea=float(wingarea.text()), rho=float(rho.text()), cd0=float(cd0.text()), rfriction_coef=float(rfc.text()), availthrust=float(avthr.text()), max_cl=float(maxcl_db.value()), oef=float(oef_db.value()))
toDist_edit.setText("""
<html>
<head/>
<body>
<p><span style=" font-size:14pt; color:#3465a4;">{0:.1f} m</span></p>
</body>
</html>""".format(todistance))
tospeed = acalculate()
tospeed = tospeed.takeoffSpeed(weight=float(weight.text()), wingarea=float(wingarea.text()), rho=float(rho.text()), max_cl=float(maxcl_db.value()))
toSpeed_edit.setText("""
<html>
<head/>
<body>
<p><span style=" font-size:14pt; color:#3465a4;">{0:.1f} m/s</span></p>
</body>
</html>""".format(tospeed))
landingdistance = acalculate()
landingdistance = landingdistance.landingDistance(weight=float(weight.text()), wingspan=float(wingspan.text()), wingarea=float(wingarea.text()), rho=float(rho.text()), cd0=float(cd0.text()), rfriction_coef=float(rfc.text()), max_cl=float(maxcl_db.value()))
landingDist_edit.setText("""
<html>
<head/>
<body>
<p><span style=" font-size:14pt; color:#3465a4;">{0:.1f} m</span></p>
</body>
</html>""".format(landingdistance))
landingspeed = acalculate()
landingspeed = landingspeed.landingSpeed(weight=float(weight.text()), wingarea=float(wingarea.text()), rho=float(rho.text()), max_cl=float(maxcl_db.value()))
landingSpeed_edit.setText("""
<html>
<head/>
<body>
<p><span style=" font-size:14pt; color:#3465a4;">{0:.1f} m/s</span></p>
</body>
</html>""".format(landingspeed))
except (ValueError, ZeroDivisionError) as error:
if len(error.args) > 0 and error.args[0] == 'could not convert string to float: ':
self.showValueError()
else:
self.showZeroDivisionError()
def apply(self):
cl = acalculate()
cl = cl.liftcoefficient(float(cl_minv_edit.text()), float(cl_maxv_edit.text()), self.weight, self.wingarea, self.rho)
if cl_exportdata_checkbox.isChecked():
cl_export_xlsx = aeroexport()
cl_export_xlsx.clvsVelocity(cl, np.arange(float(cl_minv_edit.text()), float(cl_maxv_edit.text()), 0.1))
cl_info_msg = QtWidgets.QMessageBox()
cl_info_msg.setIcon(QtWidgets.QMessageBox.Information)
cl_info_msg.setText("All data have been exported inside 'XLSX Workbooks' folder.")
cl_info_msg.setWindowTitle("DATA HAVE BEEN EXPORTED SUCCESSFULLY")
cl_info_msg.setStyleSheet("QMessageBox {font: 12pt Ubuntu}")
cl_button = cl_info_msg.addButton(QtWidgets.QMessageBox.Ok)
cl_button.setIcon(QtGui.QIcon("icons/check.png"))
cl_button.setFixedSize(75, 35)
cl_button.setStyleSheet("QPushButton {font: 10pt Ubuntu}")
cl_info_msg.setDefaultButton(cl_button)
cl_info_msg.exec_()
else:
pass
plotcl_velocity = agplot()
plotcl_velocity.clvsvelocity(cl, float(cl_minv_edit.text()), float(cl_maxv_edit.text()), 0.1, colors.get(cl_linecolor_combo.currentText()), int(cl_lineweight_spin.value()), True)
cl_minv_edit.clear()
cl_maxv_edit.clear()
self.close()
def apply(self):
avthr_k = acalculate()
avthr_oef = acalculate()
avthr_cd = acalculate()
avthr_cl = acalculate()
avthr_cd = avthr_cd.dragcoefficient(self.cd0, avthr_k.kFactor(self.wingspan, self.wingarea, avthr_oef.oef_estimate(self.wingspan, self.wingarea)), avthr_cl.liftcoefficient(float(avthr_minv_edit.text()), float(avthr_maxv_edit.text()), self.weight, self.wingarea, self.rho))
avthr_thrustReq = acalculate()
avthr_thrustReq = avthr_thrustReq.thrustReq(float(avthr_minv_edit.text()), float(avthr_maxv_edit.text()), self.wingarea, self.rho, avthr_cd, 0.1)
plotthr_vel = agplot()
plotthr_vel.thrustavailablevsthrustrequired(float(avthr_availablethr_edit.text()), avthr_thrustReq, float(avthr_minv_edit.text()), float(avthr_maxv_edit.text()), 0.1, colors.get(avthr_firstlinecolor_combo.currentText()), colors.get(avthr_secondlinecolor_combo.currentText()), int(avthr_lineweight_spin.value()), True)
avthr_minv_edit.clear()
avthr_maxv_edit.clear()
self.close()
def wingLoadingandAr():
wl = acalculate()
wl = wl.wingLoading(weight=float(weight.text()), wingarea=float(wingarea.text()))
wingLoading_edit.setText("""
<html>
<head/>
<body>
<p><span style=" font-size:14pt; color:#3465a4;">{0:.1f} kg/m</span>
<span style=" font-size:14pt; color:#3465a4; vertical-align:super;">2</span></p>
</body>
</html>""".format(wl))
ar = acalculate()
ar = ar.aspectRatio(wingspan=float(wingspan.text()), wingarea=float(wingarea.text()))
aspectRatio_edit.setText("""
<html>
<head/>
<body>
<p><span style=" font-size:14pt; color:#3465a4;">{0:.1f} : 1</span></p>
</body>
</html>""".format(ar))
def apply(self):
lift2drag_k = acalculate()
lift2drag_oef = acalculate()
lift2drag_cd = acalculate()
lift2drag_cl = acalculate()
lift2drag_cd = lift2drag_cd.dragcoefficient(self.cd0, lift2drag_k.kFactor(self.wingspan, self.wingarea, lift2drag_oef.oef_estimate(self.wingspan, self.wingarea)), lift2drag_cl.liftcoefficient(float(lift2drag_minv_edit.text()), float(lift2drag_maxv_edit.text()), self.weight, self.wingarea, self.rho))
lift2drag_cl = acalculate()
lift2drag_cl = lift2drag_cl.liftcoefficient(float(lift2drag_minv_edit.text()), float(lift2drag_maxv_edit.text()), self.weight, self.wingarea, self.rho)
ltod = lift2drag_cd/lift2drag_cl
if lift2drag_exportdata_checkbox.isChecked():
lift2drag_export_xlsx = aeroexport()
lift2drag_export_xlsx.lift2dragvsVelocity(ltod, np.arange(float(lift2drag_minv_edit.text()), float(lift2drag_maxv_edit.text())))
lift2drag_info_msg = QtWidgets.QMessageBox()
lift2drag_info_msg.setIcon(QtWidgets.QMessageBox.Information)
lift2drag_info_msg.setText("All data have been exported inside 'XLSX Workbooks' folder.")
lift2drag_info_msg.setWindowTitle("DATA HAVE BEEN EXPORTED SUCCESSFULLY")
lift2drag_info_msg.setStyleSheet("QMessageBox {font: 12pt Ubuntu}")
lift2drag_button = lift2drag_info_msg.addButton(QtWidgets.QMessageBox.Ok)
lift2drag_button.setIcon(QtGui.QIcon("icons/check.png"))
lift2drag_button.setFixedSize(75, 35)
lift2drag_button.setStyleSheet("QPushButton {font: 10pt Ubuntu}")
lift2drag_info_msg.setDefaultButton(lift2drag_button)
lift2drag_info_msg.exec_()
else:
pass
plotlift2drag_vel = agplot()
plotlift2drag_vel.lift2dragvsvelocity(ltod, float(lift2drag_minv_edit.text()), float(lift2drag_maxv_edit.text()), 0.1, colors.get(lift2drag_linecolor_combo.currentText()), int(lift2drag_lineweight_spin.value()), True)
lift2drag_minv_edit.clear()
lift2drag_maxv_edit.clear()
self.close()