E392 (10.15%) (e392-il)
E392 (10.15%) - Eppler E392 low Reynolds number airfoil
| Details | Dat file | Parser | |
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(e392-il) E392 (10.15%) Eppler E392 low Reynolds number airfoil Max thickness 10.1% at 31.6% chord. Max camber 3.7% at 45.3% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
E392 (10.15%) 1.00000 0.00000 0.99676 0.00056 0.98727 0.00233 0.97208 0.00537 0.95169 0.00949 0.92641 0.01440 0.89649 0.01996 0.86230 0.02615 0.82432 0.03289 0.78311 0.04006 0.73922 0.04751 0.69325 0.05505 0.64581 0.06247 0.59751 0.06954 0.54900 0.07592 0.50073 0.08119 0.45301 0.08506 0.40613 0.08736 0.36037 0.08800 0.31598 0.08694 0.27316 0.08429 0.23222 0.08027 0.19359 0.07509 0.15765 0.06889 0.12476 0.06181 0.09525 0.05401 0.06938 0.04565 0.04738 0.03690 0.02942 0.02799 0.01564 0.01913 0.00607 0.01068 0.00080 0.00315 0.00065 -0.00254 0.00631 -0.00696 0.01756 -0.01090 0.03413 -0.01407 0.05588 -0.01641 0.08268 -0.01793 0.11428 -0.01870 0.15039 -0.01879 0.19060 -0.01829 0.23449 -0.01728 0.28155 -0.01583 0.33122 -0.01398 0.38297 -0.01175 0.43632 -0.00920 0.49071 -0.00646 0.54559 -0.00370 0.60029 -0.00112 0.65408 0.00113 0.70625 0.00296 0.75608 0.00432 0.80289 0.00516 0.84603 0.00549 0.88489 0.00533 0.91889 0.00474 0.94753 0.00377 0.97031 0.00254 0.98677 0.00129 0.99669 0.00035 1.00000 0.00000 |
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Polars for E392 (10.15%) (e392-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e392-il | 50,000 | 9 | 37.2 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e392-il | 50,000 | 5 | 37.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e392-il | 100,000 | 9 | 61.2 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e392-il | 100,000 | 5 | 61.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e392-il | 200,000 | 9 | 86.2 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e392-il | 200,000 | 5 | 84.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e392-il | 500,000 | 9 | 120.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e392-il | 500,000 | 5 | 113.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e392-il | 1,000,000 | 9 | 146.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e392-il | 1,000,000 | 5 | 134 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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