Cambered plate C=6% T=5% R=2.11 (cp-060-050-gn)
Cambered plate C=6% T=5% R=2.11 - HAWT pipe blade with coordinates based on top surface. Camber=6% Wall thickness=5% Radius=2.113
| Details | Dat file | Parser | |
|
(cp-060-050-gn) Cambered plate C=6% T=5% R=2.11 HAWT pipe blade with coordinates based on top surface. Camber=6% Wall thickness=5% Radius=2.113 Max thickness 10.8% at 6.3% chord. Max camber 2.7% at 52.1% chord Source Generated Source dat file The dat file is in Selig format |
Cambered plate C=6% T=5% R=2.11 1.000000 0.000000 0.978618 0.005089 0.957184 0.009955 0.935701 0.014599 0.914170 0.019018 0.892595 0.023214 0.870977 0.027184 0.849319 0.030930 0.827624 0.034450 0.805893 0.037745 0.784128 0.040813 0.762334 0.043655 0.740510 0.046270 0.718661 0.048657 0.696788 0.050818 0.674894 0.052751 0.652981 0.054456 0.631051 0.055933 0.609107 0.057182 0.587151 0.058202 0.565186 0.058994 0.543214 0.059558 0.521237 0.059893 0.499258 0.060000 0.477279 0.059878 0.455302 0.059527 0.433331 0.058948 0.411366 0.058141 0.389411 0.057105 0.367468 0.055840 0.345540 0.054348 0.323628 0.052627 0.301735 0.050679 0.279863 0.048503 0.258016 0.046100 0.236194 0.043470 0.214401 0.040613 0.192639 0.037529 0.170911 0.034220 0.149217 0.030684 0.127562 0.026923 0.105947 0.022937 0.084375 0.018727 0.062848 0.014292 0.041368 0.009634 0.035859 0.008092 0.030549 0.005963 0.025500 0.003273 0.020772 0.000053 0.016420 -0.003660 0.012494 -0.007821 0.009042 -0.012383 0.006103 -0.017291 0.003711 -0.022488 0.001896 -0.027913 0.000678 -0.033502 0.000072 -0.039191 0.000084 -0.044911 0.000714 -0.050597 0.001956 -0.056181 0.003794 -0.061599 0.006206 -0.066786 0.009166 -0.071681 0.012638 -0.076228 0.016580 -0.080373 0.020948 -0.084067 0.025690 -0.087268 0.030750 -0.089937 0.036069 -0.092043 0.041584 -0.093562 0.047231 -0.094476 0.052944 -0.094773 0.058656 -0.094452 0.064299 -0.093514 0.087202 -0.088563 0.110161 -0.083879 0.133174 -0.079463 0.156236 -0.075316 0.179345 -0.071439 0.202498 -0.067831 0.225691 -0.064494 0.248922 -0.061428 0.272186 -0.058634 0.295482 -0.056111 0.318806 -0.053860 0.342155 -0.051881 0.415248 -0.046117 0.488342 -0.040352 0.561436 -0.034588 0.634530 -0.028823 0.707624 -0.023058 0.780718 -0.017294 0.853812 -0.011529 0.926906 -0.005765 1.000000 0.000000 |
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for Cambered plate C=6% T=5% R=2.11 (cp-060-050-gn)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| cp-060-050-gn | 50,000 | 9 | 19.6 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-060-050-gn | 50,000 | 5 | 20.1 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-060-050-gn | 50,000 | 1 | 21.2 at α=11° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| cp-060-050-gn | 100,000 | 9 | 22.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-060-050-gn | 100,000 | 5 | 25 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-060-050-gn | 100,000 | 1 | 28 at α=10° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| cp-060-050-gn | 200,000 | 9 | 26.1 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-060-050-gn | 200,000 | 5 | 31.4 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-060-050-gn | 200,000 | 1 | 35.7 at α=10.5° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| cp-060-050-gn | 500,000 | 9 | 35.9 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-060-050-gn | 500,000 | 5 | 45.2 at α=12.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-060-050-gn | 500,000 | 1 | 50 at α=11° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| cp-060-050-gn | 1,000,000 | 9 | 51.4 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-060-050-gn | 1,000,000 | 5 | 60.1 at α=13° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-060-050-gn | 1,000,000 | 1 | 64.2 at α=11.5° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||