ONERA OA212 AIRFOIL (oa212-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: ONERA OA212 AIRFOIL (oa212-il) Reynolds number: 1,000,000 Max Cl/Cd: 87.03 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-oa212-il-1000000-n5.txt Download as CSV file: xf-oa212-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -1.4335 0.04891 0.04579 -0.0163 0.9062 0.0139
-16.000 -1.4542 0.04409 0.04077 -0.0166 0.9034 0.0139
-15.750 -1.4657 0.04089 0.03740 -0.0152 0.9007 0.0140
-15.500 -1.4720 0.03838 0.03474 -0.0133 0.8981 0.0140
-15.250 -1.4756 0.03634 0.03256 -0.0107 0.8950 0.0141
-15.000 -1.4767 0.03470 0.03079 -0.0077 0.8918 0.0142
-14.750 -1.4701 0.03321 0.02916 -0.0057 0.8890 0.0143
-14.500 -1.4599 0.03183 0.02766 -0.0039 0.8865 0.0144
-14.250 -1.4472 0.03055 0.02624 -0.0024 0.8843 0.0145
-14.000 -1.4320 0.02936 0.02494 -0.0012 0.8817 0.0146
-13.750 -1.4151 0.02828 0.02375 -0.0001 0.8788 0.0147
-13.500 -1.3969 0.02730 0.02266 0.0009 0.8760 0.0148
-13.250 -1.3777 0.02639 0.02164 0.0019 0.8734 0.0149
-13.000 -1.3576 0.02556 0.02069 0.0028 0.8708 0.0150
-12.750 -1.3393 0.02445 0.01947 0.0038 0.8682 0.0152
-12.500 -1.3184 0.02350 0.01844 0.0045 0.8655 0.0154
-12.250 -1.2962 0.02268 0.01755 0.0051 0.8624 0.0156
-12.000 -1.2734 0.02195 0.01674 0.0057 0.8592 0.0158
-11.750 -1.2501 0.02128 0.01600 0.0062 0.8561 0.0160
-11.500 -1.2263 0.02065 0.01529 0.0067 0.8532 0.0162
-11.250 -1.2019 0.02006 0.01463 0.0071 0.8504 0.0164
-11.000 -1.1768 0.01947 0.01398 0.0074 0.8470 0.0166
-10.750 -1.1515 0.01891 0.01336 0.0078 0.8434 0.0168
-10.500 -1.1261 0.01838 0.01275 0.0081 0.8399 0.0171
-10.250 -1.1005 0.01787 0.01216 0.0084 0.8364 0.0173
-10.000 -1.0745 0.01739 0.01160 0.0086 0.8331 0.0175
-9.750 -1.0479 0.01692 0.01108 0.0088 0.8295 0.0178
-9.500 -1.0211 0.01649 0.01058 0.0089 0.8256 0.0179
-9.250 -0.9949 0.01594 0.00998 0.0091 0.8215 0.0183
-9.000 -0.9682 0.01549 0.00947 0.0093 0.8177 0.0187
-8.750 -0.9408 0.01509 0.00904 0.0093 0.8142 0.0190
-8.500 -0.9132 0.01471 0.00863 0.0094 0.8102 0.0194
-8.250 -0.8855 0.01437 0.00825 0.0094 0.8058 0.0199
-8.000 -0.8578 0.01405 0.00787 0.0094 0.8015 0.0204
-7.750 -0.8298 0.01374 0.00751 0.0094 0.7977 0.0208
-7.500 -0.8015 0.01343 0.00716 0.0094 0.7937 0.0211
-7.250 -0.7734 0.01306 0.00676 0.0093 0.7891 0.0217
-7.000 -0.7452 0.01274 0.00642 0.0093 0.7845 0.0223
-6.750 -0.7167 0.01246 0.00611 0.0092 0.7806 0.0229
-6.500 -0.6880 0.01219 0.00582 0.0090 0.7765 0.0235
-6.250 -0.6592 0.01194 0.00554 0.0089 0.7718 0.0242
-6.000 -0.6303 0.01171 0.00527 0.0088 0.7672 0.0247
-5.750 -0.6016 0.01144 0.00498 0.0086 0.7631 0.0256
-5.500 -0.5725 0.01120 0.00474 0.0084 0.7590 0.0267
-5.250 -0.5433 0.01099 0.00452 0.0082 0.7542 0.0278
-5.000 -0.5141 0.01081 0.00430 0.0080 0.7490 0.0287
-4.750 -0.4848 0.01058 0.00406 0.0078 0.7428 0.0301
-4.500 -0.4554 0.01038 0.00385 0.0076 0.7340 0.0315
-4.250 -0.4258 0.01023 0.00366 0.0073 0.7256 0.0329
-4.000 -0.3963 0.01004 0.00347 0.0070 0.7171 0.0348
-3.750 -0.3666 0.00989 0.00329 0.0067 0.7088 0.0371
-3.500 -0.3368 0.00973 0.00312 0.0064 0.6994 0.0395
-3.250 -0.3069 0.00959 0.00297 0.0060 0.6906 0.0423
-3.000 -0.2770 0.00945 0.00283 0.0057 0.6824 0.0453
-2.750 -0.2470 0.00933 0.00270 0.0053 0.6755 0.0491
-2.500 -0.2171 0.00919 0.00258 0.0049 0.6676 0.0535
-2.250 -0.1869 0.00910 0.00247 0.0045 0.6590 0.0577
-2.000 -0.1569 0.00898 0.00237 0.0041 0.6510 0.0630
-1.750 -0.1266 0.00889 0.00228 0.0037 0.6420 0.0684
-1.500 -0.0964 0.00880 0.00220 0.0032 0.6318 0.0739
-1.250 -0.0660 0.00872 0.00212 0.0027 0.6212 0.0803
-1.000 -0.0355 0.00866 0.00205 0.0022 0.6099 0.0866
-0.750 -0.0051 0.00859 0.00199 0.0017 0.5983 0.0952
-0.500 0.0255 0.00854 0.00193 0.0011 0.5838 0.1042
-0.250 0.0563 0.00852 0.00189 0.0005 0.5668 0.1148
0.000 0.0870 0.00849 0.00186 -0.0001 0.5493 0.1283
0.250 0.1179 0.00846 0.00183 -0.0008 0.5276 0.1486
0.500 0.1490 0.00846 0.00182 -0.0016 0.4997 0.1767
0.750 0.1802 0.00843 0.00183 -0.0026 0.4679 0.2263
1.000 0.2112 0.00830 0.00185 -0.0035 0.4409 0.3063
1.250 0.2421 0.00808 0.00186 -0.0045 0.4165 0.4183
1.500 0.2692 0.00680 0.00196 -0.0050 0.3972 0.8499
1.750 0.2983 0.00694 0.00208 -0.0051 0.3819 0.8741
2.000 0.3280 0.00707 0.00217 -0.0054 0.3696 0.8871
2.250 0.3579 0.00722 0.00227 -0.0058 0.3582 0.8977
2.500 0.3864 0.00737 0.00239 -0.0058 0.3476 0.9069
2.750 0.4158 0.00751 0.00249 -0.0061 0.3397 0.9152
3.000 0.4427 0.00765 0.00262 -0.0057 0.3308 0.9230
3.250 0.4708 0.00780 0.00275 -0.0056 0.3236 0.9310
3.500 0.5000 0.00790 0.00281 -0.0059 0.3160 0.9334
3.750 0.5300 0.00800 0.00288 -0.0064 0.3090 0.9343
4.000 0.5598 0.00810 0.00296 -0.0068 0.3027 0.9354
4.250 0.5898 0.00823 0.00305 -0.0073 0.2953 0.9363
4.500 0.6197 0.00833 0.00314 -0.0078 0.2896 0.9372
4.750 0.6497 0.00845 0.00324 -0.0084 0.2826 0.9381
5.000 0.6796 0.00859 0.00334 -0.0089 0.2758 0.9391
5.250 0.7094 0.00871 0.00345 -0.0094 0.2686 0.9402
5.500 0.7391 0.00888 0.00358 -0.0100 0.2594 0.9412
5.750 0.7688 0.00910 0.00372 -0.0106 0.2438 0.9420
6.000 0.7983 0.00937 0.00389 -0.0112 0.2234 0.9429
6.250 0.8278 0.00961 0.00407 -0.0118 0.2088 0.9437
6.500 0.8570 0.00988 0.00426 -0.0124 0.1943 0.9445
6.750 0.8860 0.01018 0.00448 -0.0130 0.1776 0.9454
7.250 0.9420 0.01097 0.00505 -0.0139 0.1374 0.9474
7.500 0.9689 0.01146 0.00541 -0.0142 0.1143 0.9484
7.750 0.9954 0.01199 0.00581 -0.0145 0.0924 0.9494
8.000 1.0216 0.01251 0.00622 -0.0148 0.0737 0.9504
8.250 1.0475 0.01302 0.00665 -0.0149 0.0591 0.9515
8.500 1.0734 0.01349 0.00706 -0.0151 0.0487 0.9526
8.750 1.0992 0.01394 0.00746 -0.0152 0.0414 0.9537
9.000 1.1248 0.01437 0.00787 -0.0153 0.0360 0.9550
9.250 1.1503 0.01479 0.00828 -0.0154 0.0321 0.9564
9.500 1.1754 0.01523 0.00870 -0.0154 0.0291 0.9579
9.750 1.2004 0.01566 0.00913 -0.0154 0.0268 0.9591
10.000 1.2247 0.01609 0.00958 -0.0153 0.0250 0.9604
10.250 1.2481 0.01652 0.01002 -0.0151 0.0235 0.9619
10.500 1.2706 0.01702 0.01053 -0.0148 0.0221 0.9637
10.750 1.2931 0.01748 0.01102 -0.0144 0.0212 0.9656
11.000 1.3148 0.01798 0.01155 -0.0141 0.0201 0.9677
11.250 1.3355 0.01857 0.01216 -0.0137 0.0191 0.9701
11.750 1.3722 0.01979 0.01346 -0.0123 0.0178 0.9773
12.250 1.4043 0.02123 0.01498 -0.0106 0.0166 1.0000
12.500 1.4201 0.02211 0.01589 -0.0099 0.0161 1.0000
12.750 1.4347 0.02309 0.01691 -0.0092 0.0156 1.0000
13.000 1.4499 0.02405 0.01791 -0.0086 0.0153 1.0000
13.250 1.4644 0.02505 0.01897 -0.0080 0.0149 1.0000
13.500 1.4781 0.02615 0.02013 -0.0074 0.0146 1.0000
13.750 1.4907 0.02734 0.02137 -0.0068 0.0143 1.0000
14.000 1.5022 0.02865 0.02273 -0.0063 0.0139 1.0000
14.250 1.5126 0.03009 0.02421 -0.0057 0.0136 1.0000
14.500 1.5214 0.03168 0.02586 -0.0052 0.0133 1.0000
14.750 1.5285 0.03348 0.02772 -0.0047 0.0130 1.0000
15.000 1.5346 0.03542 0.02973 -0.0044 0.0127 1.0000
15.250 1.5413 0.03734 0.03173 -0.0041 0.0126 1.0000
15.500 1.5466 0.03946 0.03392 -0.0039 0.0124 1.0000
15.750 1.5507 0.04176 0.03630 -0.0039 0.0122 1.0000
16.000 1.5532 0.04428 0.03891 -0.0039 0.0121 1.0000
16.250 1.5546 0.04704 0.04176 -0.0041 0.0119 1.0000
16.500 1.5546 0.05008 0.04488 -0.0046 0.0118 1.0000
16.750 1.5533 0.05336 0.04825 -0.0052 0.0116 1.0000
17.000 1.5505 0.05695 0.05194 -0.0060 0.0115 1.0000
17.250 1.5458 0.06093 0.05601 -0.0071 0.0114 1.0000
17.500 1.5396 0.06520 0.06039 -0.0084 0.0113 1.0000
17.750 1.5311 0.06990 0.06519 -0.0099 0.0112 1.0000
18.000 1.5214 0.07489 0.07029 -0.0116 0.0111 1.0000
18.250 1.5096 0.08032 0.07582 -0.0136 0.0110 1.0000
18.500 1.4964 0.08596 0.08157 -0.0157 0.0109 1.0000
18.750 1.4818 0.09193 0.08766 -0.0181 0.0109 1.0000
19.000 1.4671 0.09796 0.09380 -0.0205 0.0108 1.0000
19.250 1.4509 0.10425 0.10019 -0.0230 0.0107 1.0000
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