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    Static internal performance including thrust vectoring and reversing of two-dimensional convergent-divergent nozzles (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The effects of geometric design parameters on two dimensional convergent-divergent nozzles were investigated at nozzle pressure ratios up to 12 in the static test facility. Forward flight (dry and afterburning power settings), vectored-thrust (afterburning power setting), and reverse-thrust (dry power setting) nozzles were investigated. The nozzles had thrust vector angles from 0 deg to 20.26 deg, throat aspect ratios of 3.696 to 7.612, throat radii from sharp to 2.738 cm, expansion ratios from 1.089 to 1.797, and various sidewall lengths. The results indicate that unvectored two dimensional convergent-divergent nozzles have static internal performance comparable to axisymmetric nozzles with similar expansion ratios.
    Keywords: AERODYNAMICS
    Type: NASA-TP-2253 , L-15671 , NAS 1.60:2253
    Format: application/pdf
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