Rocket Center of Pressure Calculator

Number of Fins -
Shape of Nose -
Length of Nose: LN cm
Diameter of Base of Nose: d cm
Diameter in Front of Transition: dF cm
Diameter in Rear of Transition: dR cm
Length of Transition: LT cm
Distance from Tip of Nose to Front of Transition: XP cm
Fin Root Chord: CR cm
Fin Tip Chord: CT cm
Fin Semispan: S cm
Length of Fin Mid-Chord Line: LF cm
Radius of Body Rear End: R cm
Distance Between Fin Root Leading Edge and Fin Tip Leading Edge Parallel to Body: XR cm
Distance from Nose Tip to Fin Root Chord Leading Edge: XB cm
Distance from Nose Tip to Center of Pressure cm

This calculator and image is derived from Appendix II of the Handbook of Model Rocketry by G. Harry Stine. In March, 1967, James S. Barrowman of the National Aeronautics and Space Administration's Sounding Rocket Branch submitted a document entitled 'The Practical Calculation of the Aerodynamic Characteristics of Slender Finned Vehicles' as his Master's thesis to the School of Engineering and Architecture of the Catholic University of America. The document included, among other things, the simple algebraic method used by the calculator above, capable of determining the center of pressure of a rocket flying subsonically and at small angles of attack to a high order of accuracy.