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A WIND TUNNEL INVESTIGATION OF PANEL RESPONSE T BOUNDARY LAYER PRESSURE FLUCTUATIONS AT MACH 1.4 AND MACH 3.5

Tersimpan di:
Main Author: NASA, WASHINGTON DC, MAY 1966
Format: NASA-CR Book
Terbitan: NULL
Online Access: http://kinerja.lib.itb.ac.id/ftmd/index.php/bibliografi/detail/2495
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Lihat Juga

  • ASSESSMENT OF A TRANSITIONAL BOUNDARY LAYER THEORY AT LOW HYPERSONIC MACH NUMBERS
    oleh: NASA, WASHINGTON DC, NOVEMBER 1972
  • WIND TUNNEL AND ANALYTICAL INVESTIGATION OF OVER-WING PROPULSION/AIRFRAME INTERFERENCES FOR A SHORT-HAUL AIRCRAFT AT MACH NUMBERS FROM 0.6 TO 0.78
    oleh: NASA, WASHINGTON DC, SEPTEMBER 1977
  • A METHOD FOR PREDICTING FULL SCALE BUFFET RESPONSE WITH RIGID WIND TUNNEL MODEL FLUCTUATING PRESSURE DATA VOL I
    oleh: NASA, WASHINGTON DC, NOVEMBER 1978
  • A STUDY OF SURFACE PRESSURE FLUCTUATIONS IN HYPERSONIC TURBULENT BOUNDARY LAYERS
    oleh: NASA, WASHINGTON DC, FEBRUARY 1974
  • A METHOD FOR PREDICTING FULL SCALE BUFFET RESPONSE WITH RIGID WIND TUNNEL MODEL FLUCTUATING PRESSURE DATA VOLUME I: PREDICTION METHOD DEVELOPMENT AND ASSESMENT
    oleh: NASA, WASHINGTON DC, NOVEMBER 1978

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