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Table 3

Effect of T0 on CD, CL, Cm and ΔS21/R for the symmetrical curved airfoil when α = 2.0 °C, M0 = 4.00 and t/C = 0.1.

  PG HT T0 (K)
  γ = 1.402 1000 2000 3000
CD (103) 0.14376 0.14138 0.12087 0.10980
CL (103) 0.27933 0.27055 0.22723 0.20630
Cm (103) 0.10603 0.10236 0.08608 0.07844
ΔS21/R 0.73606 0.68655 0.64513 0.66500

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