MH 82 13.31% (mh82-il)
MH 82 13.31% - Martin Hepperle MH 82 for flying wings (hang glider)
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(mh82-il) MH 82 13.31% Martin Hepperle MH 82 for flying wings (hang glider) Max thickness 13.3% at 24.6% chord. Max camber 3.9% at 24.6% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
MH 82 13.31% 1.00000000 0.00000000 0.99661459 0.00010716 0.98648759 0.00057417 0.96976242 0.00167959 0.94674359 0.00367565 0.91787545 0.00675919 0.88371761 0.01105153 0.84491677 0.01659048 0.80217789 0.02332527 0.75623764 0.03112511 0.70784007 0.03978495 0.65771739 0.04904355 0.60657341 0.05859424 0.55507239 0.06810553 0.50383005 0.07723291 0.45340892 0.08563711 0.40431563 0.09299494 0.35700062 0.09901144 0.31186073 0.10342997 0.26924218 0.10603084 0.22944828 0.10664471 0.19275386 0.10507496 0.15919742 0.10111480 0.12865471 0.09486478 0.10114620 0.08660842 0.07670830 0.07665259 0.05541508 0.06541510 0.03742189 0.05331020 0.02286177 0.04072192 0.01180557 0.02807192 0.00430956 0.01589603 0.00048929 0.00484950 0.00007086 0.00175419 0.00002622 -0.00101996 0.00034816 -0.00353243 0.00078039 -0.00502846 0.00143495 -0.00631603 0.00242331 -0.00744430 0.00376965 -0.00852044 0.00632469 -0.01007170 0.00946271 -0.01156191 0.01867771 -0.01481702 0.03671504 -0.01897587 0.05993648 -0.02230735 0.08812913 -0.02462698 0.12123607 -0.02596768 0.15896894 -0.02658615 0.20083798 -0.02664454 0.24631809 -0.02624375 0.29484983 -0.02546371 0.34584166 -0.02437799 0.39867639 -0.02304567 0.45271686 -0.02152507 0.50731291 -0.01986154 0.56180823 -0.01809995 0.61554743 -0.01627195 0.66788318 -0.01440561 0.71818292 -0.01251060 0.76584748 -0.01056846 0.81037800 -0.00854699 0.85134987 -0.00650607 0.88832129 -0.00457027 0.92082546 -0.00287905 0.94837899 -0.00154846 0.97049733 -0.00064794 0.98672053 -0.00016877 0.99665170 -0.00001402 1.00000000 0.00000000 |
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Polars for MH 82 13.31% (mh82-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh82-il | 50,000 | 9 | 11.1 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh82-il | 50,000 | 5 | 23.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh82-il | 100,000 | 9 | 29.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh82-il | 100,000 | 5 | 42.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh82-il | 200,000 | 9 | 53.7 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh82-il | 200,000 | 5 | 61.7 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh82-il | 500,000 | 9 | 87.1 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh82-il | 500,000 | 5 | 90.5 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh82-il | 1,000,000 | 9 | 115.3 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh82-il | 1,000,000 | 5 | 115.2 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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