ONERA OA212 AIRFOIL (oa212-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: ONERA OA212 AIRFOIL (oa212-il) Reynolds number: 100,000 Max Cl/Cd: 45.59 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-oa212-il-100000-n5.txt Download as CSV file: xf-oa212-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5456 0.09248 0.08761 -0.0148 1.0000 0.0430
-9.500 -0.5552 0.08440 0.07954 -0.0221 1.0000 0.0431
-9.250 -0.5719 0.07504 0.07013 -0.0315 1.0000 0.0430
-9.000 -0.5951 0.06679 0.06171 -0.0365 1.0000 0.0430
-8.750 -0.6195 0.05754 0.05202 -0.0399 0.9849 0.0432
-8.500 -0.6352 0.04876 0.04250 -0.0413 0.9741 0.0436
-8.250 -0.6222 0.04605 0.03958 -0.0414 0.9664 0.0441
-8.000 -0.6075 0.04374 0.03707 -0.0412 0.9591 0.0446
-7.750 -0.5937 0.04123 0.03426 -0.0406 0.9522 0.0454
-7.500 -0.5791 0.03876 0.03144 -0.0398 0.9449 0.0465
-7.250 -0.5647 0.03601 0.02820 -0.0387 0.9384 0.0483
-7.000 -0.5488 0.03314 0.02468 -0.0375 0.9316 0.0501
-6.750 -0.5269 0.03213 0.02361 -0.0370 0.9259 0.0512
-6.500 -0.5046 0.03087 0.02215 -0.0364 0.9197 0.0525
-6.250 -0.4829 0.02959 0.02062 -0.0354 0.9144 0.0544
-6.000 -0.4586 0.02808 0.01870 -0.0350 0.9082 0.0572
-5.750 -0.4353 0.02745 0.01808 -0.0344 0.9027 0.0591
-5.500 -0.4108 0.02659 0.01709 -0.0339 0.8973 0.0615
-5.250 -0.3852 0.02558 0.01582 -0.0335 0.8914 0.0646
-5.000 -0.3613 0.02496 0.01522 -0.0328 0.8865 0.0675
-4.750 -0.3352 0.02433 0.01452 -0.0325 0.8809 0.0712
-4.500 -0.3089 0.02358 0.01362 -0.0322 0.8752 0.0752
-4.250 -0.2847 0.02311 0.01321 -0.0315 0.8704 0.0794
-4.000 -0.2582 0.02257 0.01254 -0.0312 0.8649 0.0848
-3.750 -0.2322 0.02204 0.01209 -0.0310 0.8589 0.0901
-3.500 -0.2073 0.02162 0.01160 -0.0302 0.8541 0.0969
-3.250 -0.1820 0.02115 0.01119 -0.0297 0.8489 0.1037
-3.000 -0.1550 0.02079 0.01078 -0.0296 0.8424 0.1123
-2.750 -0.1307 0.02035 0.01043 -0.0288 0.8373 0.1214
-2.500 -0.1060 0.01996 0.01006 -0.0280 0.8321 0.1318
-2.250 -0.0802 0.01960 0.00971 -0.0275 0.8235 0.1446
-2.000 -0.0591 0.01910 0.00925 -0.0254 0.8166 0.1591
-1.750 -0.0339 0.01864 0.00887 -0.0247 0.8049 0.1788
-1.500 -0.0116 0.01809 0.00847 -0.0231 0.7971 0.2080
-1.250 0.0136 0.01751 0.00822 -0.0226 0.7879 0.2749
-1.000 0.0282 0.01588 0.00789 -0.0198 0.7822 0.5633
-0.750 0.0512 0.01595 0.00886 -0.0154 0.7740 0.8822
-0.500 0.0770 0.01608 0.00888 -0.0136 0.7669 0.9229
-0.250 0.1175 0.01615 0.00882 -0.0150 0.7593 0.9515
0.000 0.1758 0.01611 0.00866 -0.0202 0.7509 0.9735
0.250 0.2581 0.01590 0.00832 -0.0305 0.7424 1.0000
0.500 0.2822 0.01577 0.00811 -0.0297 0.7321 1.0000
0.750 0.3066 0.01567 0.00793 -0.0290 0.7213 1.0000
1.000 0.3291 0.01551 0.00767 -0.0277 0.7114 1.0000
1.250 0.3544 0.01546 0.00757 -0.0273 0.6982 1.0000
1.500 0.3787 0.01538 0.00743 -0.0265 0.6852 1.0000
1.750 0.4024 0.01529 0.00726 -0.0255 0.6720 1.0000
2.000 0.4262 0.01521 0.00711 -0.0245 0.6576 1.0000
2.250 0.4505 0.01517 0.00700 -0.0237 0.6414 1.0000
2.500 0.4748 0.01515 0.00691 -0.0229 0.6237 1.0000
2.750 0.4995 0.01517 0.00686 -0.0222 0.6039 1.0000
3.000 0.5239 0.01521 0.00683 -0.0215 0.5827 1.0000
3.250 0.5481 0.01528 0.00680 -0.0207 0.5604 1.0000
3.500 0.5721 0.01539 0.00679 -0.0199 0.5378 1.0000
3.750 0.5964 0.01555 0.00686 -0.0193 0.5145 1.0000
4.000 0.6203 0.01576 0.00695 -0.0186 0.4926 1.0000
4.250 0.6441 0.01601 0.00708 -0.0179 0.4730 1.0000
4.500 0.6678 0.01629 0.00726 -0.0172 0.4554 1.0000
4.750 0.6914 0.01659 0.00748 -0.0166 0.4399 1.0000
5.000 0.7148 0.01692 0.00774 -0.0159 0.4260 1.0000
5.250 0.7380 0.01726 0.00800 -0.0152 0.4139 1.0000
5.500 0.7611 0.01762 0.00833 -0.0145 0.4021 1.0000
5.750 0.7842 0.01798 0.00868 -0.0138 0.3912 1.0000
6.000 0.8069 0.01838 0.00901 -0.0131 0.3817 1.0000
6.250 0.8301 0.01875 0.00945 -0.0125 0.3712 1.0000
6.500 0.8531 0.01917 0.00982 -0.0118 0.3623 1.0000
6.750 0.8764 0.01957 0.01029 -0.0112 0.3521 1.0000
7.000 0.8998 0.02002 0.01074 -0.0107 0.3430 1.0000
7.250 0.9232 0.02044 0.01122 -0.0102 0.3328 1.0000
7.500 0.9465 0.02089 0.01171 -0.0098 0.3222 1.0000
7.750 0.9693 0.02135 0.01215 -0.0093 0.3108 1.0000
8.000 0.9915 0.02177 0.01267 -0.0088 0.2965 1.0000
8.250 1.0131 0.02222 0.01318 -0.0083 0.2810 1.0000
8.500 1.0342 0.02270 0.01370 -0.0078 0.2649 1.0000
8.750 1.0548 0.02321 0.01428 -0.0073 0.2488 1.0000
9.000 1.0746 0.02378 0.01490 -0.0067 0.2320 1.0000
9.250 1.0930 0.02444 0.01557 -0.0060 0.2140 1.0000
9.500 1.1108 0.02518 0.01635 -0.0052 0.1929 1.0000
9.750 1.1252 0.02613 0.01724 -0.0043 0.1699 1.0000
10.000 1.1375 0.02727 0.01831 -0.0032 0.1453 1.0000
10.250 1.1459 0.02868 0.01962 -0.0019 0.1227 1.0000
10.500 1.1498 0.03027 0.02111 -0.0001 0.1050 1.0000
10.750 1.1532 0.03205 0.02284 0.0015 0.0919 1.0000
11.000 1.1567 0.03393 0.02473 0.0028 0.0819 1.0000
11.250 1.1600 0.03592 0.02675 0.0040 0.0746 1.0000
11.500 1.1609 0.03817 0.02902 0.0049 0.0694 1.0000
11.750 1.1633 0.04040 0.03136 0.0057 0.0649 1.0000
12.000 1.1618 0.04307 0.03406 0.0062 0.0618 1.0000
12.250 1.1635 0.04555 0.03667 0.0066 0.0585 1.0000
12.500 1.1632 0.04831 0.03953 0.0067 0.0559 1.0000
12.750 1.1605 0.05141 0.04268 0.0066 0.0540 1.0000
13.000 1.1606 0.05432 0.04571 0.0066 0.0521 1.0000
13.250 1.1605 0.05731 0.04882 0.0063 0.0503 1.0000
13.500 1.1597 0.06044 0.05204 0.0060 0.0487 1.0000
13.750 1.1584 0.06368 0.05534 0.0054 0.0474 1.0000
14.000 1.1583 0.06682 0.05855 0.0050 0.0461 1.0000
14.250 1.1593 0.06999 0.06188 0.0045 0.0447 1.0000
14.500 1.1597 0.07327 0.06528 0.0038 0.0433 1.0000
14.750 1.1603 0.07654 0.06863 0.0031 0.0422 1.0000
15.000 1.1619 0.07964 0.07177 0.0024 0.0413 1.0000
15.250 1.1663 0.08222 0.07433 0.0023 0.0404 1.0000
15.500 1.1661 0.08588 0.07821 0.0014 0.0396 1.0000
15.750 1.1645 0.08980 0.08232 0.0002 0.0388 1.0000
16.000 1.1622 0.09391 0.08659 -0.0013 0.0380 1.0000
16.250 1.1588 0.09827 0.09111 -0.0030 0.0373 1.0000
16.500 1.1555 0.10268 0.09564 -0.0048 0.0366 1.0000
16.750 1.1531 0.10691 0.09997 -0.0066 0.0360 1.0000
17.000 1.1535 0.11058 0.10368 -0.0081 0.0353 1.0000
17.250 1.1500 0.11513 0.10833 -0.0101 0.0348 1.0000
17.500 1.1355 0.12229 0.11574 -0.0142 0.0345 1.0000
17.750 1.1182 0.13029 0.12399 -0.0189 0.0343 1.0000
18.000 1.0963 0.13973 0.13368 -0.0248 0.0342 1.0000
18.250 1.0645 0.15232 0.14654 -0.0329 0.0342 1.0000
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