NACA 64(1)-212 (n64212-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 64(1)-212 (n64212-il) Reynolds number: 1,000,000 Max Cl/Cd: 91.16 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n64212-il-1000000.txt Download as CSV file: xf-n64212-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.8830 0.05972 0.05753 -0.0460 1.0000 0.0105
-13.500 -0.9400 0.04844 0.04587 -0.0522 1.0000 0.0103
-13.250 -0.9597 0.04343 0.04066 -0.0539 1.0000 0.0103
-13.000 -0.9703 0.03991 0.03697 -0.0545 1.0000 0.0103
-12.750 -0.9704 0.03783 0.03480 -0.0544 1.0000 0.0105
-12.500 -0.9815 0.03474 0.03152 -0.0536 1.0000 0.0106
-12.250 -0.9861 0.03254 0.02915 -0.0522 1.0000 0.0107
-12.000 -0.9862 0.03101 0.02749 -0.0503 1.0000 0.0109
-11.750 -0.9856 0.02969 0.02606 -0.0478 1.0000 0.0111
-11.500 -0.9811 0.02797 0.02415 -0.0458 1.0000 0.0113
-11.250 -0.9698 0.02671 0.02274 -0.0444 1.0000 0.0115
-11.000 -0.9544 0.02588 0.02179 -0.0433 1.0000 0.0117
-10.750 -0.9382 0.02503 0.02083 -0.0423 1.0000 0.0119
-10.500 -0.9321 0.02212 0.01760 -0.0404 1.0000 0.0122
-10.250 -0.9178 0.02058 0.01595 -0.0391 1.0000 0.0126
-10.000 -0.8992 0.01978 0.01510 -0.0382 1.0000 0.0129
-9.750 -0.8798 0.01918 0.01446 -0.0373 1.0000 0.0132
-9.500 -0.8612 0.01853 0.01375 -0.0361 1.0000 0.0135
-9.250 -0.8348 0.01784 0.01300 -0.0365 0.9957 0.0139
-9.000 -0.8022 0.01702 0.01209 -0.0382 0.9887 0.0144
-8.750 -0.7683 0.01626 0.01125 -0.0401 0.9819 0.0149
-8.500 -0.7337 0.01585 0.01077 -0.0420 0.9728 0.0153
-8.250 -0.7050 0.01461 0.00940 -0.0430 0.9599 0.0159
-8.000 -0.6812 0.01369 0.00840 -0.0428 0.9441 0.0165
-7.750 -0.6578 0.01324 0.00789 -0.0422 0.9294 0.0170
-7.500 -0.6341 0.01287 0.00746 -0.0416 0.9163 0.0176
-7.250 -0.6102 0.01250 0.00701 -0.0410 0.9041 0.0183
-7.000 -0.5858 0.01213 0.00657 -0.0405 0.8931 0.0189
-6.750 -0.5606 0.01187 0.00623 -0.0401 0.8825 0.0195
-6.500 -0.5360 0.01142 0.00571 -0.0397 0.8722 0.0202
-6.250 -0.5123 0.01081 0.00501 -0.0392 0.8627 0.0215
-6.000 -0.4864 0.01052 0.00469 -0.0390 0.8531 0.0226
-5.750 -0.4600 0.01026 0.00438 -0.0389 0.8443 0.0239
-5.250 -0.4073 0.00964 0.00363 -0.0386 0.8271 0.0273
-5.000 -0.3805 0.00941 0.00337 -0.0385 0.8187 0.0299
-4.750 -0.3530 0.00923 0.00316 -0.0385 0.8100 0.0320
-4.500 -0.3262 0.00893 0.00282 -0.0384 0.8020 0.0367
-4.250 -0.2987 0.00875 0.00261 -0.0384 0.7937 0.0407
-4.000 -0.2714 0.00850 0.00237 -0.0385 0.7859 0.0508
-3.750 -0.2445 0.00814 0.00213 -0.0385 0.7777 0.0848
-3.500 -0.2182 0.00760 0.00188 -0.0386 0.7700 0.1610
-3.250 -0.1929 0.00681 0.00156 -0.0388 0.7618 0.2934
-3.000 -0.1675 0.00601 0.00132 -0.0389 0.7540 0.4503
-2.750 -0.1397 0.00584 0.00124 -0.0390 0.7458 0.4985
-2.500 -0.1113 0.00574 0.00119 -0.0392 0.7382 0.5255
-2.250 -0.0829 0.00570 0.00115 -0.0393 0.7305 0.5438
-2.000 -0.0543 0.00565 0.00111 -0.0395 0.7231 0.5603
-1.750 -0.0258 0.00563 0.00108 -0.0396 0.7156 0.5759
-1.500 0.0028 0.00560 0.00107 -0.0398 0.7084 0.5970
-1.250 0.0311 0.00557 0.00108 -0.0399 0.7010 0.6194
-1.000 0.0598 0.00556 0.00108 -0.0400 0.6939 0.6313
-0.750 0.0885 0.00557 0.00107 -0.0402 0.6864 0.6398
-0.500 0.1172 0.00557 0.00106 -0.0404 0.6795 0.6475
-0.250 0.1460 0.00558 0.00106 -0.0406 0.6725 0.6553
0.000 0.1746 0.00559 0.00107 -0.0407 0.6661 0.6621
0.250 0.2035 0.00560 0.00108 -0.0409 0.6594 0.6692
0.500 0.2320 0.00564 0.00110 -0.0411 0.6528 0.6760
0.750 0.2609 0.00563 0.00112 -0.0413 0.6456 0.6833
1.250 0.3181 0.00568 0.00119 -0.0416 0.6306 0.6983
1.750 0.3751 0.00574 0.00126 -0.0419 0.6128 0.7140
2.000 0.4034 0.00579 0.00130 -0.0420 0.5987 0.7216
2.250 0.4311 0.00587 0.00133 -0.0420 0.5788 0.7297
2.500 0.4591 0.00594 0.00139 -0.0420 0.5629 0.7375
2.750 0.4871 0.00602 0.00146 -0.0421 0.5472 0.7458
3.000 0.5153 0.00608 0.00154 -0.0422 0.5337 0.7538
3.250 0.5431 0.00618 0.00162 -0.0422 0.5153 0.7626
3.500 0.5706 0.00630 0.00173 -0.0422 0.4927 0.7710
3.750 0.5971 0.00655 0.00186 -0.0420 0.4503 0.7799
4.000 0.6185 0.00739 0.00220 -0.0413 0.3281 0.7884
4.250 0.6394 0.00834 0.00266 -0.0405 0.2111 0.7972
4.500 0.6615 0.00911 0.00307 -0.0399 0.1272 0.8063
4.750 0.6850 0.00969 0.00343 -0.0394 0.0758 0.8152
5.000 0.7096 0.01013 0.00376 -0.0390 0.0492 0.8248
5.250 0.7348 0.01044 0.00406 -0.0387 0.0394 0.8343
5.500 0.7602 0.01074 0.00438 -0.0383 0.0339 0.8441
5.750 0.7854 0.01103 0.00469 -0.0380 0.0301 0.8544
6.000 0.8098 0.01136 0.00508 -0.0374 0.0267 0.8645
6.250 0.8346 0.01162 0.00538 -0.0370 0.0244 0.8754
6.500 0.8566 0.01216 0.00597 -0.0360 0.0214 0.8879
7.000 0.9034 0.01268 0.00663 -0.0345 0.0195 0.9158
7.250 0.9243 0.01299 0.00699 -0.0333 0.0185 0.9328
7.500 0.9432 0.01335 0.00742 -0.0316 0.0176 0.9585
7.750 0.9669 0.01423 0.00839 -0.0315 0.0166 1.0000
8.000 0.9914 0.01463 0.00883 -0.0312 0.0162 1.0000
8.250 1.0153 0.01506 0.00929 -0.0308 0.0157 1.0000
8.500 1.0381 0.01556 0.00982 -0.0303 0.0151 1.0000
8.750 1.0602 0.01610 0.01039 -0.0297 0.0146 1.0000
9.000 1.0817 0.01666 0.01098 -0.0290 0.0142 1.0000
9.250 1.1020 0.01729 0.01165 -0.0281 0.0138 1.0000
9.500 1.1199 0.01811 0.01250 -0.0269 0.0134 1.0000
9.750 1.1332 0.01934 0.01381 -0.0251 0.0130 1.0000
10.000 1.1457 0.02074 0.01532 -0.0233 0.0127 1.0000
10.250 1.1621 0.02153 0.01617 -0.0218 0.0126 1.0000
10.500 1.1769 0.02226 0.01698 -0.0201 0.0125 1.0000
10.750 1.1905 0.02309 0.01790 -0.0184 0.0123 1.0000
11.000 1.2031 0.02404 0.01893 -0.0166 0.0121 1.0000
11.250 1.2163 0.02477 0.01973 -0.0150 0.0118 1.0000
11.500 1.2276 0.02582 0.02086 -0.0134 0.0115 1.0000
11.750 1.2383 0.02693 0.02206 -0.0118 0.0114 1.0000
12.000 1.2485 0.02804 0.02325 -0.0103 0.0111 1.0000
12.250 1.2577 0.02927 0.02458 -0.0088 0.0110 1.0000
12.500 1.2654 0.03071 0.02611 -0.0074 0.0108 1.0000
12.750 1.2736 0.03199 0.02747 -0.0063 0.0106 1.0000
13.000 1.2804 0.03349 0.02904 -0.0051 0.0104 1.0000
13.250 1.2850 0.03528 0.03093 -0.0041 0.0103 1.0000
13.500 1.2875 0.03738 0.03313 -0.0031 0.0102 1.0000
13.750 1.2861 0.04002 0.03590 -0.0022 0.0100 1.0000
14.000 1.2740 0.04412 0.04022 -0.0013 0.0098 1.0000
14.250 1.2591 0.04864 0.04498 -0.0010 0.0098 1.0000
14.500 1.2382 0.05407 0.05067 -0.0014 0.0097 1.0000
14.750 1.2281 0.05828 0.05505 -0.0023 0.0097 1.0000
15.000 1.2279 0.06122 0.05810 -0.0033 0.0096 1.0000
15.250 1.2208 0.06539 0.06240 -0.0049 0.0095 1.0000
15.500 1.2033 0.07153 0.06872 -0.0074 0.0095 1.0000
15.750 1.1930 0.07688 0.07421 -0.0101 0.0095 1.0000
16.000 1.1709 0.08477 0.08229 -0.0144 0.0095 1.0000
16.250 1.1421 0.09470 0.09241 -0.0203 0.0095 1.0000
16.500 1.1184 0.10459 0.10247 -0.0265 0.0095 1.0000
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