ONERA OA213 AIRFOIL (oa213-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: ONERA OA213 AIRFOIL (oa213-il) Reynolds number: 200,000 Max Cl/Cd: 54.03 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-oa213-il-200000.txt Download as CSV file: xf-oa213-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: ONERA OA213 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4080 0.08998 0.08712 -0.0147 0.9107 0.0456
-8.000 -0.4124 0.08400 0.08113 -0.0235 0.9034 0.0468
-7.750 -0.4303 0.07811 0.07499 -0.0321 0.8961 0.0478
-7.500 -0.4340 0.07241 0.06910 -0.0350 0.8899 0.0484
-7.250 -0.4246 0.06942 0.06622 -0.0330 0.8853 0.0491
-7.000 -0.4127 0.06667 0.06346 -0.0329 0.8799 0.0501
-6.750 -0.4025 0.06374 0.06047 -0.0331 0.8741 0.0514
-6.500 -0.3962 0.06080 0.05739 -0.0325 0.8693 0.0532
-6.250 -0.3865 0.05577 0.05165 -0.0352 0.8626 0.0582
-6.000 -0.3723 0.05227 0.04824 -0.0345 0.8575 0.0592
-5.750 -0.3606 0.05006 0.04600 -0.0327 0.8534 0.0606
-5.500 -0.3379 0.04743 0.04325 -0.0338 0.8466 0.0638
-5.250 -0.3232 0.04423 0.03949 -0.0327 0.8414 0.0703
-5.000 -0.3083 0.04184 0.03711 -0.0310 0.8376 0.0721
-4.750 -0.2821 0.03966 0.03481 -0.0319 0.8304 0.0764
-4.500 -0.2634 0.03720 0.03194 -0.0306 0.8253 0.0845
-4.250 -0.2454 0.03530 0.02998 -0.0288 0.8217 0.0878
-4.000 -0.2076 0.02599 0.01872 -0.0257 0.8157 0.0403
-3.750 -0.1821 0.02428 0.01674 -0.0246 0.8103 0.0402
-3.500 -0.1594 0.02234 0.01464 -0.0228 0.8065 0.0409
-3.250 -0.1305 0.02116 0.01344 -0.0230 0.7997 0.0426
-3.000 -0.1046 0.02046 0.01267 -0.0222 0.7940 0.0463
-2.750 -0.0819 0.01938 0.01149 -0.0203 0.7900 0.0492
-2.500 -0.0537 0.01854 0.01073 -0.0203 0.7822 0.0534
-2.250 -0.0312 0.01766 0.00981 -0.0185 0.7759 0.0599
-2.000 -0.0067 0.01699 0.00912 -0.0172 0.7681 0.0685
-1.750 0.0165 0.01606 0.00826 -0.0157 0.7603 0.0839
-1.500 0.0403 0.01520 0.00753 -0.0145 0.7537 0.1175
-1.250 0.0540 0.01238 0.00693 -0.0127 0.7459 0.6257
-1.000 0.0611 0.01196 0.00716 -0.0055 0.7410 0.8731
-0.750 0.0823 0.01208 0.00728 -0.0022 0.7316 0.9289
-0.500 0.1366 0.01220 0.00719 -0.0048 0.7255 0.9715
-0.250 0.2385 0.01229 0.00705 -0.0184 0.7146 0.9987
0.000 0.2654 0.01206 0.00667 -0.0181 0.7063 1.0000
0.250 0.2906 0.01186 0.00636 -0.0177 0.6959 1.0000
0.500 0.3162 0.01170 0.00610 -0.0174 0.6853 1.0000
0.750 0.3403 0.01151 0.00578 -0.0167 0.6755 1.0000
1.000 0.3661 0.01137 0.00555 -0.0164 0.6632 1.0000
1.250 0.3918 0.01126 0.00536 -0.0161 0.6502 1.0000
1.500 0.4171 0.01117 0.00517 -0.0157 0.6366 1.0000
1.750 0.4425 0.01110 0.00500 -0.0153 0.6221 1.0000
2.000 0.4679 0.01105 0.00485 -0.0150 0.6062 1.0000
2.250 0.4934 0.01104 0.00473 -0.0147 0.5885 1.0000
2.500 0.5189 0.01106 0.00464 -0.0143 0.5693 1.0000
2.750 0.5443 0.01113 0.00457 -0.0140 0.5484 1.0000
3.000 0.5702 0.01124 0.00456 -0.0139 0.5229 1.0000
3.250 0.5958 0.01141 0.00459 -0.0138 0.4943 1.0000
3.500 0.6215 0.01166 0.00466 -0.0138 0.4618 1.0000
3.750 0.6470 0.01201 0.00479 -0.0138 0.4276 1.0000
4.000 0.6721 0.01244 0.00500 -0.0139 0.3954 1.0000
4.250 0.6969 0.01291 0.00527 -0.0139 0.3684 1.0000
4.500 0.7217 0.01340 0.00557 -0.0139 0.3463 1.0000
4.750 0.7465 0.01389 0.00590 -0.0139 0.3286 1.0000
5.000 0.7717 0.01436 0.00626 -0.0140 0.3138 1.0000
5.250 0.7970 0.01482 0.00663 -0.0140 0.3010 1.0000
5.500 0.8223 0.01531 0.00702 -0.0140 0.2898 1.0000
5.750 0.8472 0.01583 0.00741 -0.0140 0.2798 1.0000
6.000 0.8730 0.01623 0.00784 -0.0141 0.2703 1.0000
6.250 0.8978 0.01681 0.00828 -0.0141 0.2626 1.0000
6.500 0.9236 0.01722 0.00872 -0.0142 0.2551 1.0000
6.750 0.9484 0.01778 0.00919 -0.0141 0.2487 1.0000
7.000 0.9738 0.01826 0.00972 -0.0141 0.2426 1.0000
7.250 0.9989 0.01873 0.01018 -0.0141 0.2367 1.0000
7.500 1.0235 0.01940 0.01075 -0.0141 0.2314 1.0000
7.750 1.0485 0.01984 0.01130 -0.0141 0.2261 1.0000
8.000 1.0732 0.02035 0.01182 -0.0141 0.2214 1.0000
8.250 1.0980 0.02106 0.01244 -0.0140 0.2173 1.0000
8.500 1.1225 0.02164 0.01313 -0.0139 0.2136 1.0000
8.750 1.1468 0.02220 0.01378 -0.0139 0.2097 1.0000
9.000 1.1712 0.02279 0.01440 -0.0138 0.2063 1.0000
9.250 1.1961 0.02350 0.01508 -0.0138 0.2032 1.0000
9.500 1.2206 0.02434 0.01597 -0.0137 0.2003 1.0000
9.750 1.2433 0.02498 0.01678 -0.0136 0.1972 1.0000
10.000 1.2657 0.02555 0.01744 -0.0134 0.1934 1.0000
10.250 1.2885 0.02608 0.01796 -0.0133 0.1897 1.0000
10.500 1.3114 0.02690 0.01878 -0.0132 0.1858 1.0000
10.750 1.3297 0.02748 0.01957 -0.0127 0.1822 1.0000
11.000 1.3493 0.02807 0.02027 -0.0124 0.1788 1.0000
11.250 1.3701 0.02867 0.02091 -0.0121 0.1758 1.0000
11.500 1.3942 0.02955 0.02171 -0.0121 0.1724 1.0000
11.750 1.4070 0.03023 0.02266 -0.0112 0.1697 1.0000
12.000 1.4210 0.03099 0.02360 -0.0105 0.1666 1.0000
12.250 1.4338 0.03169 0.02439 -0.0095 0.1637 1.0000
12.500 1.4484 0.03237 0.02511 -0.0087 0.1611 1.0000
12.750 1.4656 0.03322 0.02596 -0.0081 0.1578 1.0000
13.000 1.4680 0.03432 0.02731 -0.0066 0.1550 1.0000
13.250 1.4742 0.03538 0.02854 -0.0056 0.1518 1.0000
13.500 1.4819 0.03635 0.02960 -0.0049 0.1484 1.0000
13.750 1.4934 0.03730 0.03049 -0.0043 0.1446 1.0000
14.000 1.4938 0.03899 0.03249 -0.0036 0.1416 1.0000
14.250 1.4952 0.04067 0.03436 -0.0032 0.1370 1.0000
14.500 1.4982 0.04236 0.03607 -0.0031 0.1325 1.0000
14.750 1.4989 0.04458 0.03854 -0.0032 0.1273 1.0000
15.000 1.4985 0.04704 0.04111 -0.0037 0.1207 1.0000
15.250 1.4991 0.04971 0.04397 -0.0043 0.1121 1.0000
15.500 1.4976 0.05281 0.04718 -0.0051 0.1020 1.0000
16.000 1.4712 0.06247 0.05683 -0.0079 0.0660 1.0000
16.250 1.4451 0.06935 0.06369 -0.0101 0.0552 1.0000
16.500 1.4204 0.07642 0.07084 -0.0127 0.0506 1.0000
16.750 1.3961 0.08373 0.07828 -0.0155 0.0487 1.0000
17.000 1.3710 0.09149 0.08621 -0.0187 0.0476 1.0000
17.250 1.3445 0.09974 0.09463 -0.0223 0.0471 1.0000
17.500 1.3167 0.10847 0.10354 -0.0261 0.0470 1.0000
17.750 1.2883 0.11753 0.11278 -0.0303 0.0471 1.0000
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