Naca23018

25/09/2022 14:23 NACA23018 Angle of Attack (deg) 25/09/2022 14:23 NACA23018 Angle of Attack (deg) 25/09/2022 14:23 NACA23018 Angle of Attack (deg) Re = 6M | 500k | 1M | 3M Lift: Cl = f(a) = -1.246e-04*a^3 + -1.998e-05*a^2 + 1.301e-01*a + 1.538e-01 Drag: Cd = f(q) = 2.012e-06*q^3 + 8.494e-05*q^2 + -1.626e-04*q + 5.717e-03 Moment: Cm = f(q) = 4.735e-07*q^3 + 3.767e-06*q^2 + -9.495e-04*q + 7.208e-03 NACA23018 Cubic curve fit of JavaFoil data for smooth airfoil at Mach 0 Section lift coefficient vs angle of attack Cl = f(q) = -1.246e-04*q^3 + -1.998e-05*q^2 + 1.301e-01*q + 1.538e-01 https://bigfoil.com/C5198543c-08ee-4b6a-960f-3ae349b1b630_inf0c.php#6M 10/13 25/09/2022 14:23 NACA23018 Re = 1M | 500k | 3M | 6M Lift: Cl = f(q) = -1.354e-04*q^3 + -1.453e-05*q^2 + 1.298e-01*q + 1.526e-01 Drag: Cd = f(q) = 3.173e-06*q^3 + 1.494e-04*q^2 + 3.118e-04*q + 4.877e-03 Moment: Cm = f(q) = 6.387e-07*q^3 + 4.881e-06*q^2 + 9.532e-04*q + -7.219e-03 NACA23018 Cubic curve fit of JavaFoil data for smooth airfoil at Mach 0 Section lift coefficient vs angle of attack Cl = f(q) = -1.354e-04*q^3 + -1.453e-05*q^2 + 1.298e-01*q + 1.526e-01 https://bigfoil.com/C5198543c-08ee-4b6a-960f-3ae349b1b630_inf0C.php#6M 4/13 25/09/2022 14:23 NACA23018 NACA23018 Cubic curve fit of JavaFoil data for smooth airfoil at Mach 0 Section drag coefficient vs angle of attack Cd = f(q) = 3.173e-06*q^3 + 1.494e-04*q^2 + 3.118e-04*q + 4.877e-03 https://bigfoil.com/C5198543c-08ee-4b6a-960f-3ae349b1b630_inf0C.php#6M 5/13 25/09/2022 14:23 NACA23018 NACA23018 Cubic curve fit of JavaFoil data for smooth airfoil at Mach 0 Section moment coefficient vs angle of attack Cm = f(q) = 6.387e-07*q^3 + 4.881e-06*q^2 + 9.532e-04*q + -7.219e-03 https://bigfoil.com/C5198543c-08ee-4b6a-960f-3ae349b1b630_inf0C.php#6M 6/13 25/09/2022 14:23 NACA23018 Re = 3M | 500k | 1M | 6M Lift: Cl = f(a) = -1.284e-04*a^3 + -1.409e-05*a^2 + 1.301e-01*a + 1.534e-01 Drag: Cd = f(a) = 2.056e-06*a^3 + 1.059e-04*a^2 + 1.773e-04*a + 5.180e-03 Moment: Cm = f(a) = 5.184e-07*a^3 + 4.344e-06*a^2 + 9.525e-04*a + -7.232e-03 NACA23018 Cubic curve fit of JavaFoil data for smooth airfoil at Mach 0 Section lift coefficient vs angle of attack Cl = f(a) = -1.284e-04*a^3 + -1.409e-05*a^2 + 1.301e-01*a + 1.534e-01 https://bigsfoil.com/C5198543c-08ee-46ba-960f-3ae349b1b630_infoC.php#6M 7/13 25/09/2022 14:23 NACA23018 NACA23018 Cubic curve fit of JavaFoil data for smooth airfoil at Mach 0 Section drag coefficient vs angle of attack Cd = f(a) = 2.056e-06*a^3 + 1.059e-04*a^2 + 1.773e-04*a + 5.180e-03 https://bigsfoil.com/C5198543c-08ee-46ba-960f-3ae349b1b630_infoC.php#6M 8/13 25/09/2022 14:23 NACA23018 NACA23018 Cubic curve fit of JavaFoil data for smooth airfoil at Mach 0 Section moment coefficient vs angle of attack Cm = f(a) = 5.184e-07*a^3 + 4.344e-06*a^2 + 9.525e-04*a + -7.232e-03 https://bigsfoil.com/C5198543c-08ee-46ba-960f-3ae349b1b630_infoC.php#6M 9/13 25/09/2022 14:23 NACA23018 Angle of Attack (deg) https://bigfoil.com/C5198543c-08ee-46ba-960f-3ae349b1b630_infoC.php#6M 13/13