NACA 64(1)-212 (n64212-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 64(1)-212 (n64212-il) Reynolds number: 500,000 Max Cl/Cd: 80.25 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n64212-il-500000.txt Download as CSV file: xf-n64212-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64(1)-212
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.4586 0.10346 0.10127 -0.0211 1.0000 0.0288
-11.500 -0.4642 0.09767 0.09550 -0.0237 1.0000 0.0295
-10.250 -0.7956 0.04463 0.04123 -0.0484 1.0000 0.0207
-10.000 -0.7957 0.04093 0.03730 -0.0467 1.0000 0.0193
-9.750 -0.8015 0.03680 0.03285 -0.0446 1.0000 0.0191
-9.500 -0.8003 0.03332 0.02902 -0.0426 1.0000 0.0191
-9.250 -0.7939 0.03043 0.02578 -0.0407 1.0000 0.0193
-9.000 -0.7837 0.02834 0.02341 -0.0387 1.0000 0.0196
-8.500 -0.7611 0.02370 0.01829 -0.0353 0.9981 0.0207
-8.250 -0.7282 0.02224 0.01673 -0.0374 0.9931 0.0214
-8.000 -0.6951 0.02086 0.01522 -0.0392 0.9878 0.0220
-7.750 -0.6602 0.01954 0.01378 -0.0413 0.9839 0.0227
-7.500 -0.6274 0.01837 0.01247 -0.0427 0.9770 0.0235
-7.250 -0.5924 0.01746 0.01145 -0.0446 0.9712 0.0246
-7.000 -0.5598 0.01703 0.01090 -0.0458 0.9619 0.0254
-6.750 -0.5338 0.01511 0.00893 -0.0461 0.9516 0.0267
-6.500 -0.5079 0.01441 0.00819 -0.0460 0.9402 0.0278
-6.250 -0.4844 0.01387 0.00759 -0.0453 0.9278 0.0290
-6.000 -0.4612 0.01339 0.00704 -0.0445 0.9158 0.0305
-5.750 -0.4370 0.01304 0.00662 -0.0439 0.9050 0.0319
-5.500 -0.4155 0.01223 0.00572 -0.0429 0.8946 0.0344
-5.250 -0.3914 0.01179 0.00524 -0.0424 0.8843 0.0371
-5.000 -0.3661 0.01145 0.00484 -0.0419 0.8745 0.0398
-4.750 -0.3416 0.01097 0.00428 -0.0414 0.8656 0.0442
-4.500 -0.3157 0.01066 0.00393 -0.0411 0.8560 0.0501
-4.250 -0.2899 0.01027 0.00354 -0.0409 0.8475 0.0610
-4.000 -0.2650 0.00967 0.00314 -0.0406 0.8385 0.1073
-3.750 -0.2430 0.00841 0.00261 -0.0405 0.8296 0.2865
-3.500 -0.2201 0.00745 0.00232 -0.0403 0.8212 0.4746
-3.250 -0.1931 0.00726 0.00226 -0.0402 0.8125 0.5262
-3.000 -0.1656 0.00720 0.00219 -0.0401 0.8050 0.5552
-2.750 -0.1376 0.00714 0.00214 -0.0401 0.7964 0.5765
-2.500 -0.1097 0.00713 0.00208 -0.0400 0.7891 0.5933
-2.250 -0.0815 0.00710 0.00205 -0.0401 0.7805 0.6082
-2.000 -0.0540 0.00711 0.00206 -0.0399 0.7731 0.6315
-1.750 -0.0263 0.00715 0.00212 -0.0397 0.7645 0.6553
-1.500 0.0016 0.00716 0.00210 -0.0396 0.7573 0.6662
-1.250 0.0302 0.00715 0.00206 -0.0398 0.7492 0.6745
-1.000 0.0583 0.00716 0.00205 -0.0398 0.7423 0.6823
-0.750 0.0869 0.00715 0.00202 -0.0399 0.7345 0.6896
-0.500 0.1151 0.00716 0.00200 -0.0399 0.7278 0.6963
-0.250 0.1438 0.00716 0.00199 -0.0401 0.7200 0.7039
0.000 0.1719 0.00718 0.00199 -0.0401 0.7133 0.7103
0.250 0.2006 0.00719 0.00201 -0.0403 0.7058 0.7181
0.500 0.2287 0.00720 0.00203 -0.0404 0.6995 0.7250
0.750 0.2574 0.00723 0.00207 -0.0405 0.6927 0.7334
1.000 0.2855 0.00725 0.00211 -0.0406 0.6861 0.7407
1.250 0.3140 0.00730 0.00216 -0.0407 0.6796 0.7491
1.500 0.3420 0.00730 0.00221 -0.0407 0.6721 0.7564
2.000 0.3982 0.00737 0.00234 -0.0407 0.6572 0.7728
2.250 0.4262 0.00743 0.00240 -0.0408 0.6489 0.7817
2.500 0.4534 0.00744 0.00244 -0.0405 0.6357 0.7902
2.750 0.4803 0.00744 0.00245 -0.0402 0.6161 0.7989
3.000 0.5072 0.00749 0.00248 -0.0399 0.5973 0.8079
3.250 0.5341 0.00754 0.00255 -0.0397 0.5813 0.8163
3.500 0.5616 0.00762 0.00266 -0.0396 0.5679 0.8259
3.750 0.5879 0.00769 0.00276 -0.0392 0.5505 0.8346
4.000 0.6142 0.00780 0.00287 -0.0389 0.5278 0.8442
4.250 0.6396 0.00797 0.00300 -0.0384 0.4939 0.8543
4.500 0.6616 0.00839 0.00319 -0.0374 0.4174 0.8641
4.750 0.6757 0.00974 0.00378 -0.0356 0.2537 0.8753
5.000 0.6915 0.01094 0.00442 -0.0340 0.1338 0.8875
5.250 0.7092 0.01181 0.00498 -0.0325 0.0690 0.9005
5.500 0.7292 0.01229 0.00541 -0.0311 0.0514 0.9141
5.750 0.7485 0.01274 0.00587 -0.0295 0.0434 0.9299
6.000 0.7677 0.01302 0.00623 -0.0278 0.0391 0.9494
6.250 0.7929 0.01369 0.00695 -0.0277 0.0345 0.9760
6.500 0.8223 0.01418 0.00747 -0.0285 0.0315 1.0000
6.750 0.8460 0.01482 0.00810 -0.0283 0.0290 1.0000
7.000 0.8660 0.01578 0.00910 -0.0274 0.0270 1.0000
7.250 0.8890 0.01639 0.00976 -0.0269 0.0258 1.0000
7.500 0.9110 0.01706 0.01047 -0.0263 0.0246 1.0000
7.750 0.9322 0.01779 0.01122 -0.0256 0.0236 1.0000
8.000 0.9524 0.01860 0.01205 -0.0248 0.0227 1.0000
8.250 0.9698 0.01995 0.01343 -0.0236 0.0219 1.0000
8.500 0.9892 0.02148 0.01503 -0.0226 0.0213 1.0000
8.750 1.0111 0.02218 0.01582 -0.0220 0.0207 1.0000
9.000 1.0323 0.02302 0.01676 -0.0212 0.0200 1.0000
9.250 1.0532 0.02419 0.01802 -0.0205 0.0195 1.0000
9.500 1.0738 0.02541 0.01935 -0.0198 0.0190 1.0000
9.750 1.0938 0.02665 0.02068 -0.0191 0.0186 1.0000
10.000 1.1126 0.02799 0.02213 -0.0182 0.0182 1.0000
10.250 1.1303 0.02954 0.02382 -0.0173 0.0179 1.0000
10.500 1.1463 0.03102 0.02540 -0.0163 0.0176 1.0000
10.750 1.1609 0.03290 0.02741 -0.0152 0.0172 1.0000
11.000 1.1724 0.03556 0.03027 -0.0140 0.0170 1.0000
11.250 1.1685 0.03996 0.03504 -0.0113 0.0166 1.0000
11.500 1.1649 0.04162 0.03691 -0.0081 0.0165 1.0000
11.750 1.1598 0.04359 0.03910 -0.0053 0.0163 1.0000
12.000 1.1505 0.04633 0.04209 -0.0029 0.0162 1.0000
12.250 1.1384 0.04954 0.04553 -0.0011 0.0162 1.0000
12.500 1.1223 0.05353 0.04975 0.0001 0.0163 1.0000
12.750 1.1040 0.05786 0.05430 0.0006 0.0163 1.0000
13.000 1.0840 0.06274 0.05939 0.0001 0.0163 1.0000
13.250 1.0630 0.06822 0.06506 -0.0012 0.0164 1.0000
13.500 1.0396 0.07463 0.07164 -0.0036 0.0165 1.0000
13.750 0.9831 0.08774 0.08523 -0.0106 0.0177 1.0000
14.000 0.9797 0.09197 0.08950 -0.0133 0.0175 1.0000
14.250 0.9801 0.09561 0.09314 -0.0155 0.0172 1.0000
14.500 0.6658 0.14927 0.14742 -0.0455 0.0275 1.0000
14.750 0.6621 0.15478 0.15293 -0.0487 0.0274 1.0000
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