diff --git a/gpkitmodels/GP/aircraft/motor/motor_test.py b/gpkitmodels/GP/aircraft/motor/motor_test.py
index 71e4c178..80ad8a8d 100644
--- a/gpkitmodels/GP/aircraft/motor/motor_test.py
+++ b/gpkitmodels/GP/aircraft/motor/motor_test.py
@@ -20,7 +20,7 @@ def propulsor_test():
     test = Propulsor_Test()
     #sol = test.debug()
     sol = test.solve()
-    #print sol.table()
+    print sol.table()
 
 class Motor_P_Test(Model):
     def setup(self):
@@ -62,4 +62,4 @@ def test():
     propulsor_test()
     
 if __name__ == "__main__":
-    test()
\ No newline at end of file
+    test()
diff --git a/gpkitmodels/GP/aircraft/prop/propeller.py b/gpkitmodels/GP/aircraft/prop/propeller.py
index 34b7400c..c6066f1d 100644
--- a/gpkitmodels/GP/aircraft/prop/propeller.py
+++ b/gpkitmodels/GP/aircraft/prop/propeller.py
@@ -16,7 +16,7 @@ class Propeller(Model):
     def setup(self):
         exec parse_variables(Propeller.__doc__)
 
-        constraints = [W == K*T_m_static*R**2]
+        constraints = [W >= K*T_m_static*R**2]
 
         return constraints
 
@@ -59,13 +59,13 @@ def setup(self,parent,  state):
 
 
         constraints = [eta <= etav*etai,
-                Tc == T/(0.5*rho*V**2*pi*R**2),
+                Tc >= T/(0.5*rho*V**2*pi*R**2),
                 z2 >= Tc + 1,
                 etai*(z1 + z2**0.5/etaadd) <= 2,
-                lam == V/(omega*R),
-                CT == Tc*lam**2,
-                CP == Q*omega/(.5*rho*(omega*R)**3*pi*R**2),
-                eta == CT*lam/CP, 
+                lam >= V/(omega*R),
+                CT >= Tc*lam**2,
+                CP <= Q*omega/(.5*rho*(omega*R)**3*pi*R**2),
+                eta >= CT*lam/CP, 
                 omega <= omega_max,
                 P_shaft == Q*omega,
                 (M_tip*a)**2 >= (omega*R)**2 + V**2