diff --git a/initial_sizing/initial_sizing_conf.xml b/initial_sizing/initial_sizing_conf.xml
index 896dd1d245d056804f185a9c03473b14701b4b90..678f3033cdd6485cf7289c215af780d57cc440b1 100644
--- a/initial_sizing/initial_sizing_conf.xml
+++ b/initial_sizing/initial_sizing_conf.xml
@@ -57,7 +57,7 @@
</approach_selection>
<analytical_approach>
<General>
- <OswaldFactor description="Oswald factor in clean configuration" Unit="-">
+ <OswaldFactor description="Oswald efficency factor in clean configuration" Unit="-">
<value>0.85</value>
<default>0.85</default>
</OswaldFactor>
@@ -73,13 +73,13 @@
<value>2</value>
<default>2</default>
</n_engines>
- <Cf description="friction coefficient" Unit="count">
+ <Cf description="equivalent friction coefficient" Unit="count">
<value>0.002</value>
<default>0.002</default>
</Cf>
</General>
<Constants>
- <SFC_kerosene description="Specific Fuel Consumption Factor for Kerosene">
+ <SFC_kerosene description="Specific Fuel Consumption factor for Kerosene">
<value>0.0001389</value>
<default>0.0001389</default>
</SFC_kerosene>
@@ -111,7 +111,7 @@
<value>0.956</value>
<default>0.956</default>
</mcr_mto>
- <optimalCL description="maximum CL at initial cruise">
+ <optimalCL description="design CL for initial cruise">
<value>0.57</value>
<default>0.57</default>
</optimalCL>
@@ -127,16 +127,16 @@
</LD_initial_loiter>
</LiftToDragRatios>
<Masses description="mass estimation methodology">
- <Fractions description="mass fractions">
+ <Fractions description="fuel mass fractions">
<mf_warmup description="Warmup (according to Raymer: 0.97(A340)-0.99(A320))" Unit="-" Default="0.99">
<value>0.99</value>
<default>0.99</default>
</mf_warmup>
- <mf_taxi description="Warmup (according to Raymer: 0.97(A340)-0.99(A320))" Unit="-" Default="0.99">
+ <mf_taxi description="Taxi (according to Raymer: 0.97(A340)-0.99(A320))" Unit="-" Default="0.99">
<value>0.99</value>
<default>0.99</default>
</mf_taxi>
- <mf_to description="Taxi and Takeoff (according to Raymer: 0.97(A340)-0.99(A320))" Unit="-" Default="0.995">
+ <mf_to description="Takeoff (according to Raymer: 0.97(A340)-0.99(A320))" Unit="-" Default="0.995">
<value>0.995</value>
<default>0.995</default>
</mf_to>
@@ -148,11 +148,11 @@
<value>0.99</value>
<default>0.99</default>
</mf_descent>
- <mf_missedandclimb description="Landing and Taxi Back (according to Raymer: 0.992(A340)-0.997(A320))" Unit="-" Default="0.988">
+ <mf_missedandclimb description="missed approach and climb to alternate airport (according to Raymer: 0.992(A340)-0.997(A320))" Unit="-" Default="0.988">
<value>0.988</value>
<default>0.988</default>
</mf_missedandclimb>
- <mf_land description="Landing and Taxi Back (according to Raymer: 0.992(A340)-0.997(A320))" Unit="-" Default="0.995">
+ <mf_land description="Landing and Taxi out (according to Raymer: 0.992(A340)-0.997(A320))" Unit="-" Default="0.995">
<value>0.995</value>
<default>0.995</default>
</mf_land>
diff --git a/initial_sizing/src/main.cpp b/initial_sizing/src/main.cpp
index 7a4d0a0bb546f28933fdba21061c4e741c412f02..c6e9c6d58a802f84f6acf2b72efa83317977c35b 100644
--- a/initial_sizing/src/main.cpp
+++ b/initial_sizing/src/main.cpp
@@ -15,11 +15,6 @@
along with UNICADO. If not, see <http://www.gnu.org/licenses/>.
*/
-/** \mainpage initialSizing
-* The program sizes the aircraft and estimates a required wing loading and thrust-to-weight ratio.
-*
-*/
-
/* The following statements import necessary libraries */
#include <cstdlib> //system()/exit() // Import c++ standard library for using cstdlib
#include <exception> // Import c++ standard library for using exception
diff --git a/initial_sizing/src/taw/analytical/TawAnalytical.cpp b/initial_sizing/src/taw/analytical/TawAnalytical.cpp
index 598cfc96e13b5b115e7ae0b4d91569f2c850956a..724a5263821d97c4c34e982d2b1c3adfc3c1d20e 100644
--- a/initial_sizing/src/taw/analytical/TawAnalytical.cpp
+++ b/initial_sizing/src/taw/analytical/TawAnalytical.cpp
@@ -157,8 +157,8 @@ void TawAnalytical::calculatePayloadAndCrew() {
// Calculate crew weight
crewWeight = (data_->data.Accommodation.massPassenger + data_->data.Accommodation.massLuggage) * numCrew;
- // Calculate total payload and crew weight
- Payload = passengerWeight + cargoWeight + crewWeight;
+ // Calculate total payload
+ Payload = passengerWeight + cargoWeight;
std::cout << "Passenger Weight: " << passengerWeight << std::endl;
std::cout << "Crew Number: " << numCrew << std::endl;
@@ -232,7 +232,7 @@ void TawAnalytical::calculateFuelFraction() {
void TawAnalytical::calculateMassEstimation() {
// Constants
- mo_iteration = 5.5 *(passengerWeight + cargoWeight);
+ mo_iteration = 5.5 * Payload;
c_kerosine = 0.55;
c_LH2 = 0.44;
mo_iteration = mo_initial;
@@ -249,7 +249,7 @@ void TawAnalytical::calculateMassEstimation() {
me_mo = c_fuel * cos(0.0000012 * mo_iteration);
// Calculate new mo_iteration
- mo_iteration = (passengerWeight + cargoWeight) / (1 - (FuelFraction) - (me_mo));
+ mo_iteration = (Payload + crewWeight) / (1 - (FuelFraction) - (me_mo));
// Debug new mo_iteration
} while (!checkConvergence(mo_iteration, mo_iteration_previous)); // Loop until convergence is achieved