ONERA OA212 AIRFOIL (oa212-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: ONERA OA212 AIRFOIL (oa212-il) Reynolds number: 50,000 Max Cl/Cd: 31.64 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-oa212-il-50000-n5.txt Download as CSV file: xf-oa212-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: ONERA OA212 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5034 0.10083 0.09387 -0.0159 1.0000 0.0734
-9.250 -0.5042 0.09552 0.08859 -0.0202 1.0000 0.0733
-9.000 -0.5068 0.08983 0.08291 -0.0252 1.0000 0.0731
-8.750 -0.5125 0.08429 0.07736 -0.0297 1.0000 0.0728
-8.500 -0.5209 0.07928 0.07231 -0.0327 1.0000 0.0725
-8.250 -0.5279 0.07433 0.06726 -0.0350 1.0000 0.0721
-8.000 -0.5346 0.06971 0.06251 -0.0362 1.0000 0.0718
-7.750 -0.5414 0.06558 0.05821 -0.0362 1.0000 0.0716
-7.500 -0.5496 0.06202 0.05447 -0.0347 1.0000 0.0716
-7.250 -0.5584 0.05887 0.05112 -0.0321 1.0000 0.0717
-7.000 -0.5651 0.05574 0.04772 -0.0295 1.0000 0.0723
-6.750 -0.5697 0.05249 0.04410 -0.0268 1.0000 0.0733
-6.500 -0.5722 0.04899 0.04004 -0.0241 1.0000 0.0745
-6.250 -0.5510 0.04700 0.03801 -0.0247 0.9956 0.0763
-6.000 -0.5254 0.04437 0.03508 -0.0260 0.9896 0.0781
-5.750 -0.4971 0.04164 0.03193 -0.0276 0.9843 0.0808
-5.500 -0.4699 0.03889 0.02850 -0.0287 0.9782 0.0847
-5.250 -0.4380 0.03691 0.02628 -0.0304 0.9735 0.0878
-5.000 -0.4076 0.03544 0.02462 -0.0316 0.9679 0.0917
-4.750 -0.3719 0.03370 0.02231 -0.0334 0.9635 0.0977
-4.500 -0.3417 0.03250 0.02111 -0.0345 0.9575 0.1022
-4.250 -0.3056 0.03140 0.01976 -0.0363 0.9530 0.1097
-4.000 -0.2757 0.03043 0.01869 -0.0370 0.9466 0.1161
-3.750 -0.2400 0.02964 0.01773 -0.0385 0.9416 0.1256
-3.500 -0.2105 0.02895 0.01708 -0.0390 0.9350 0.1344
-3.250 -0.1746 0.02833 0.01635 -0.0404 0.9297 0.1466
-3.000 -0.1448 0.02788 0.01585 -0.0408 0.9229 0.1599
-2.750 -0.1123 0.02738 0.01541 -0.0417 0.9167 0.1761
-2.500 -0.0859 0.02697 0.01505 -0.0416 0.9091 0.1940
-2.250 -0.0575 0.02651 0.01474 -0.0419 0.9022 0.2185
-2.000 -0.0357 0.02607 0.01452 -0.0410 0.8934 0.2529
-1.750 -0.0111 0.02524 0.01423 -0.0406 0.8859 0.3346
-1.500 0.0297 0.02437 0.01545 -0.0385 0.8798 0.8987
-1.250 0.1833 0.02407 0.01460 -0.0602 0.8767 1.0000
-1.000 0.2044 0.02409 0.01444 -0.0588 0.8629 1.0000
-0.750 0.2264 0.02408 0.01426 -0.0573 0.8510 1.0000
-0.500 0.2458 0.02413 0.01419 -0.0558 0.8377 1.0000
-0.250 0.2657 0.02418 0.01413 -0.0544 0.8253 1.0000
0.000 0.2868 0.02414 0.01398 -0.0527 0.8144 1.0000
0.250 0.3069 0.02415 0.01391 -0.0512 0.8020 1.0000
0.500 0.3270 0.02419 0.01386 -0.0496 0.7891 1.0000
0.750 0.3479 0.02412 0.01372 -0.0479 0.7776 1.0000
1.000 0.3686 0.02403 0.01357 -0.0461 0.7655 1.0000
1.250 0.3887 0.02405 0.01354 -0.0445 0.7515 1.0000
1.500 0.4092 0.02401 0.01346 -0.0427 0.7380 1.0000
1.750 0.4302 0.02386 0.01326 -0.0408 0.7254 1.0000
2.000 0.4512 0.02374 0.01309 -0.0389 0.7119 1.0000
2.250 0.4717 0.02371 0.01305 -0.0372 0.6963 1.0000
2.500 0.4924 0.02366 0.01298 -0.0355 0.6803 1.0000
2.750 0.5133 0.02361 0.01291 -0.0337 0.6641 1.0000
3.000 0.5343 0.02356 0.01284 -0.0320 0.6474 1.0000
3.250 0.5555 0.02352 0.01277 -0.0302 0.6302 1.0000
3.500 0.5769 0.02351 0.01272 -0.0285 0.6128 1.0000
3.750 0.5984 0.02353 0.01271 -0.0269 0.5952 1.0000
4.000 0.6199 0.02359 0.01272 -0.0253 0.5774 1.0000
4.250 0.6415 0.02371 0.01279 -0.0238 0.5600 1.0000
4.500 0.6632 0.02388 0.01291 -0.0223 0.5430 1.0000
4.750 0.6849 0.02411 0.01310 -0.0210 0.5264 1.0000
5.000 0.7067 0.02439 0.01334 -0.0197 0.5109 1.0000
5.250 0.7287 0.02472 0.01362 -0.0185 0.4962 1.0000
5.500 0.7511 0.02505 0.01391 -0.0173 0.4826 1.0000
5.750 0.7737 0.02544 0.01427 -0.0163 0.4695 1.0000
6.000 0.7956 0.02598 0.01483 -0.0154 0.4560 1.0000
6.500 0.8418 0.02695 0.01579 -0.0137 0.4327 1.0000
6.750 0.8637 0.02760 0.01652 -0.0129 0.4205 1.0000
7.000 0.8860 0.02826 0.01724 -0.0122 0.4091 1.0000
7.250 0.9103 0.02877 0.01772 -0.0114 0.3987 1.0000
7.500 0.9309 0.02958 0.01870 -0.0108 0.3865 1.0000
7.750 0.9528 0.03031 0.01951 -0.0100 0.3751 1.0000
8.000 0.9766 0.03087 0.02007 -0.0093 0.3640 1.0000
8.250 0.9951 0.03176 0.02115 -0.0085 0.3508 1.0000
8.500 1.0143 0.03254 0.02206 -0.0076 0.3375 1.0000
8.750 1.0331 0.03323 0.02282 -0.0066 0.3235 1.0000
9.000 1.0502 0.03389 0.02355 -0.0054 0.3083 1.0000
9.250 1.0646 0.03458 0.02433 -0.0041 0.2920 1.0000
9.500 1.0760 0.03537 0.02522 -0.0026 0.2752 1.0000
9.750 1.0847 0.03628 0.02624 -0.0009 0.2582 1.0000
10.000 1.0909 0.03735 0.02744 0.0008 0.2410 1.0000
10.250 1.0944 0.03860 0.02879 0.0025 0.2240 1.0000
10.500 1.0946 0.04005 0.03031 0.0045 0.2074 1.0000
10.750 1.0945 0.04177 0.03207 0.0061 0.1902 1.0000
11.000 1.0937 0.04379 0.03407 0.0073 0.1732 1.0000
11.250 1.0918 0.04614 0.03638 0.0083 0.1575 1.0000
11.500 1.0889 0.04883 0.03903 0.0089 0.1434 1.0000
11.750 1.0858 0.05178 0.04197 0.0093 0.1312 1.0000
12.000 1.0824 0.05493 0.04512 0.0095 0.1210 1.0000
12.250 1.0787 0.05817 0.04831 0.0095 0.1131 1.0000
12.500 1.0758 0.06156 0.05176 0.0093 0.1057 1.0000
12.750 1.0735 0.06493 0.05516 0.0091 0.1000 1.0000
13.000 1.0712 0.06844 0.05875 0.0087 0.0946 1.0000
13.250 1.0705 0.07167 0.06194 0.0084 0.0904 1.0000
13.500 1.0677 0.07559 0.06610 0.0077 0.0863 1.0000
13.750 1.0670 0.07907 0.06965 0.0071 0.0828 1.0000
14.000 1.0683 0.08222 0.07277 0.0068 0.0797 1.0000
14.250 1.0615 0.08715 0.07800 0.0052 0.0771 1.0000
14.500 1.0556 0.09197 0.08301 0.0036 0.0748 1.0000
14.750 1.0525 0.09627 0.08742 0.0022 0.0727 1.0000
15.000 1.0601 0.09850 0.08957 0.0023 0.0705 1.0000
15.250 1.0417 0.10618 0.09758 -0.0015 0.0696 1.0000
15.500 1.0170 0.11561 0.10731 -0.0065 0.0690 1.0000
15.750 0.9800 0.12870 0.12069 -0.0141 0.0689 1.0000
16.000 0.9254 0.14841 0.14053 -0.0254 0.0690 1.0000
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Polar data table (+)
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