DOUGLAS LA203A AIRFOIL (la203a-il)
DOUGLAS LA203A AIRFOIL - Douglas/Liebeck LA203A high lift airfoil
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(la203a-il) DOUGLAS LA203A AIRFOIL Douglas/Liebeck LA203A high lift airfoil Max thickness 15.7% at 34.3% chord. Max camber 5.5% at 46% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
DOUGLAS LA203A AIRFOIL 51. 51. 0.000000 0.000000 0.000887 0.006000 0.003544 0.015836 0.007963 0.023336 0.014127 0.030677 0.022015 0.038031 0.031599 0.045492 0.042846 0.053047 0.055715 0.060636 0.070162 0.068190 0.086135 0.075641 0.103579 0.082919 0.122432 0.089956 0.142628 0.096688 0.164095 0.103048 0.186758 0.108970 0.210538 0.114389 0.235350 0.119234 0.261106 0.123424 0.287718 0.126854 0.315090 0.129435 0.343127 0.131182 0.371729 0.132075 0.400796 0.132090 0.430226 0.131219 0.459916 0.129436 0.489759 0.126743 0.519653 0.123176 0.549490 0.118770 0.579167 0.113566 0.608579 0.107640 0.637621 0.101087 0.666193 0.094063 0.694194 0.086797 0.721524 0.079995 0.748087 0.072292 0.773791 0.065291 0.798545 0.058545 0.822261 0.052086 0.844856 0.045936 0.866250 0.040113 0.886369 0.034630 0.905141 0.029490 0.922500 0.024700 0.938385 0.020258 0.952740 0.016162 0.965516 0.012408 0.976665 0.008985 0.986151 0.005883 0.993938 0.003044 1.000000 0.000000 0.000000 0.000000 0.000887 -.008018 0.003544 -.015137 0.007963 -.021544 0.014127 -.026516 0.022015 -.029638 0.031599 -.031320 0.042846 -.032209 0.055715 -.032676 0.070162 -.032867 0.086135 -.032657 0.103579 -.032692 0.122432 -.032407 0.142628 -.032024 0.164095 -.031557 0.186758 -.031016 0.210538 -.030405 0.235350 -.029724 0.261106 -.028967 0.287718 -.028125 0.315090 -.027184 0.343127 -.026124 0.371729 -.024919 0.400796 -.023512 0.430226 -.021826 0.459916 -.019830 0.489759 -.017533 0.519653 -.014947 0.549490 -.012099 0.579167 -.009052 0.608579 -.005917 0.637621 -.002822 0.666193 0.000143 0.694194 0.002917 0.721524 0.005448 0.748087 0.007686 0.773791 0.009596 0.798545 0.011145 0.822261 0.012313 0.844856 0.013087 0.866250 0.013484 0.886369 0.013448 0.905141 0.013056 0.922500 0.012302 0.938385 0.011218 0.952740 0.009838 0.965516 0.008211 0.976665 0.006392 0.986151 0.004425 0.993938 0.002384 1.000000 0.000000 |
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Polars for DOUGLAS LA203A AIRFOIL (la203a-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| la203a-il | 50,000 | 9 | 6 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| la203a-il | 50,000 | 5 | 13.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| la203a-il | 100,000 | 9 | 30.6 at α=12.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| la203a-il | 100,000 | 5 | 46.5 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| la203a-il | 200,000 | 9 | 82.4 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| la203a-il | 200,000 | 5 | 85.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| la203a-il | 500,000 | 9 | 127.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| la203a-il | 500,000 | 5 | 124 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| la203a-il | 1,000,000 | 9 | 160.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| la203a-il | 1,000,000 | 5 | 151.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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