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The experimental pressure distribution data from low speed wind tunnel tests at zero angle of attack on two different conical noses attached to a cylindrical after‐body are compared with theory. The simplified theoretical equation used is a higher order approximation valid up to the order r4 lnr. It is shown that the conical nose with a vertex angle of 20 degrees is in agreement but the larger cone with a vertex angle of 30 degrees shows a discrepancy between the measured pressures and the approximate theory. In both cases, however, the theory is in excellent agreement with the surface pressures on the cylindrical after‐body.