Cleaned up many warnings

[sw/motorsim] / src / com / billkuker / rocketry / motorsim / Burn.java

diff --git a/src/com/billkuker/rocketry/motorsim/Burn.java b/src/com/billkuker/rocketry/motorsim/Burn.java
index 046dca2f5c66ae1e40b6055df492eb9557d86ce2..ef2474b39d0291e82e9d47f7553c2716a66671ab 100644 (file)
--- a/src/com/billkuker/rocketry/motorsim/Burn.java
+++ b/src/com/billkuker/rocketry/motorsim/Burn.java
@@ -146,7 +146,7 @@ public class Burn {
                        //log.debug("Mass Gen Rate: " + mGenRate);\r
                        \r
                        //Calculate specific gas constant\r
-                       Amount specificGasConstant = Constants.R.divide(motor.getFuel().getCombustionProduct().getEffectiveMolarWeight());\r
+                       Amount<?> specificGasConstant = Constants.R.divide(motor.getFuel().getCombustionProduct().getEffectiveMolarWeight());\r
                        //This unit conversion helps JScience to convert nozzle flow rate to\r
                        //kg/s a little later on I verified the conversion by hand and\r
                        //JScience checks it too.\r
@@ -162,7 +162,7 @@ public class Burn {
                                Amount<Area> aStar = motor.getNozzle().throatArea();\r
                                double k = motor.getFuel().getCombustionProduct().getRatioOfSpecificHeats();\r
                                double kSide = Math.sqrt(k) * Math.pow((2/(k+1)) , (((k+1)/2)/(k-1)));\r
-                               Amount sqrtPart = specificGasConstant.times(chamberTemp).sqrt();\r
+                               Amount<?> sqrtPart = specificGasConstant.times(chamberTemp).sqrt();\r
                                mNozzle = pDiff.times(aStar).times(kSide).divide(sqrtPart).to(MassFlowRate.UNIT);\r
                                //log.debug("Mass Exit Rate: " + mNozzle.to(MassFlowRate.UNIT));                \r
                        }\r