NACA 64(1)-212 MOD B (n64212mb-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64(1)-212 MOD B (n64212mb-il) Reynolds number: 100,000 Max Cl/Cd: 35.07 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n64212mb-il-100000-n5.txt Download as CSV file: xf-n64212mb-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64(1)-212 MOD B
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
------ -------- --------- --------- -------- -------- --------
-11.750 -0.5813 0.09850 0.09302 -0.0228 1.0000 0.0349
-11.500 -0.5857 0.09230 0.08684 -0.0262 1.0000 0.0346
-11.250 -0.5969 0.08496 0.07949 -0.0309 1.0000 0.0342
-11.000 -0.6170 0.07712 0.07159 -0.0365 1.0000 0.0338
-10.750 -0.6417 0.07016 0.06452 -0.0413 1.0000 0.0335
-10.500 -0.6650 0.06469 0.05892 -0.0442 1.0000 0.0333
-10.250 -0.6866 0.06032 0.05440 -0.0451 1.0000 0.0332
-10.000 -0.7050 0.05687 0.05077 -0.0442 1.0000 0.0330
-9.750 -0.7166 0.05339 0.04706 -0.0430 1.0000 0.0329
-9.500 -0.7229 0.04993 0.04331 -0.0417 1.0000 0.0329
-9.250 -0.7237 0.04670 0.03977 -0.0403 1.0000 0.0329
-9.000 -0.7204 0.04371 0.03645 -0.0387 1.0000 0.0331
-8.750 -0.7137 0.04097 0.03338 -0.0372 1.0000 0.0334
-8.500 -0.7053 0.03846 0.03048 -0.0354 1.0000 0.0341
-8.250 -0.6956 0.03621 0.02776 -0.0334 1.0000 0.0348
-8.000 -0.6815 0.03445 0.02592 -0.0319 1.0000 0.0355
-7.750 -0.6671 0.03299 0.02437 -0.0303 1.0000 0.0361
-7.500 -0.6526 0.03152 0.02277 -0.0286 1.0000 0.0367
-7.250 -0.6385 0.03014 0.02126 -0.0266 1.0000 0.0372
-7.000 -0.6243 0.02887 0.01986 -0.0246 1.0000 0.0378
-6.750 -0.6101 0.02770 0.01855 -0.0225 1.0000 0.0386
-6.500 -0.5830 0.02635 0.01705 -0.0227 0.9959 0.0396
-6.250 -0.5494 0.02507 0.01559 -0.0241 0.9894 0.0413
-6.000 -0.5157 0.02397 0.01457 -0.0258 0.9834 0.0436
-5.750 -0.4831 0.02301 0.01357 -0.0271 0.9763 0.0464
-5.500 -0.4494 0.02202 0.01252 -0.0285 0.9704 0.0488
-5.250 -0.4177 0.02111 0.01169 -0.0299 0.9634 0.0521
-5.000 -0.3838 0.02036 0.01089 -0.0314 0.9575 0.0573
-4.750 -0.3536 0.01960 0.01017 -0.0323 0.9498 0.0629
-4.500 -0.3209 0.01888 0.00945 -0.0336 0.9437 0.0720
-4.250 -0.2926 0.01820 0.00882 -0.0341 0.9352 0.0857
-4.000 -0.2611 0.01726 0.00814 -0.0354 0.9294 0.1261
-3.750 -0.2421 0.01561 0.00747 -0.0351 0.9196 0.3064
-3.500 -0.2164 0.01484 0.00758 -0.0348 0.9135 0.5118
-3.250 -0.1911 0.01483 0.00769 -0.0339 0.9048 0.5691
-3.000 -0.1626 0.01498 0.00795 -0.0332 0.8980 0.6253
-2.750 -0.1397 0.01535 0.00845 -0.0308 0.8874 0.6736
-2.500 -0.1125 0.01552 0.00859 -0.0294 0.8759 0.7008
-2.250 -0.0836 0.01541 0.00837 -0.0286 0.8621 0.7094
-2.000 -0.0570 0.01525 0.00809 -0.0277 0.8463 0.7186
-1.750 -0.0314 0.01515 0.00790 -0.0266 0.8313 0.7259
-1.500 -0.0047 0.01501 0.00765 -0.0260 0.8175 0.7345
-1.250 0.0217 0.01492 0.00751 -0.0251 0.8049 0.7403
-1.000 0.0487 0.01480 0.00729 -0.0244 0.7920 0.7479
-0.750 0.0747 0.01469 0.00712 -0.0236 0.7773 0.7551
-0.500 0.1004 0.01460 0.00699 -0.0227 0.7617 0.7623
-0.250 0.1268 0.01450 0.00682 -0.0221 0.7455 0.7702
0.000 0.1521 0.01442 0.00670 -0.0210 0.7274 0.7771
0.250 0.1781 0.01434 0.00653 -0.0202 0.7055 0.7864
0.500 0.2023 0.01427 0.00641 -0.0189 0.6777 0.7934
0.750 0.2274 0.01423 0.00623 -0.0179 0.6414 0.8025
1.000 0.2507 0.01425 0.00608 -0.0163 0.5854 0.8100
1.250 0.2689 0.01474 0.00579 -0.0141 0.4182 0.8200
1.500 0.2863 0.01554 0.00599 -0.0122 0.3307 0.8287
1.750 0.3087 0.01597 0.00620 -0.0113 0.3009 0.8390
2.000 0.3315 0.01629 0.00640 -0.0103 0.2822 0.8486
2.250 0.3545 0.01658 0.00659 -0.0094 0.2690 0.8589
2.500 0.3782 0.01683 0.00679 -0.0086 0.2586 0.8708
2.750 0.4013 0.01709 0.00699 -0.0075 0.2511 0.8819
3.000 0.4256 0.01731 0.00720 -0.0067 0.2440 0.8939
3.250 0.4499 0.01760 0.00741 -0.0060 0.2382 0.9072
3.500 0.4762 0.01785 0.00765 -0.0057 0.2324 0.9212
3.750 0.5046 0.01813 0.00791 -0.0059 0.2267 0.9356
4.000 0.5362 0.01850 0.00820 -0.0067 0.2218 0.9500
4.250 0.5714 0.01890 0.00858 -0.0084 0.2175 0.9643
4.500 0.6086 0.01931 0.00901 -0.0105 0.2132 0.9807
4.750 0.6410 0.01974 0.00942 -0.0119 0.2093 1.0000
5.000 0.6651 0.02021 0.00982 -0.0116 0.2061 1.0000
5.250 0.6906 0.02078 0.01029 -0.0116 0.2030 1.0000
5.500 0.7168 0.02124 0.01084 -0.0116 0.1998 1.0000
5.750 0.7432 0.02178 0.01143 -0.0116 0.1968 1.0000
6.000 0.7698 0.02235 0.01203 -0.0117 0.1940 1.0000
6.250 0.7963 0.02294 0.01263 -0.0117 0.1913 1.0000
6.500 0.8228 0.02358 0.01324 -0.0118 0.1886 1.0000
6.750 0.8492 0.02431 0.01397 -0.0119 0.1860 1.0000
7.000 0.8748 0.02497 0.01480 -0.0118 0.1832 1.0000
7.250 0.9004 0.02571 0.01568 -0.0117 0.1806 1.0000
7.500 0.9256 0.02642 0.01651 -0.0116 0.1777 1.0000
7.750 0.9507 0.02711 0.01725 -0.0115 0.1748 1.0000
8.000 0.9762 0.02784 0.01799 -0.0114 0.1722 1.0000
8.250 1.0010 0.02874 0.01895 -0.0113 0.1697 1.0000
8.500 1.0229 0.02958 0.02008 -0.0108 0.1662 1.0000
8.750 1.0452 0.03035 0.02104 -0.0104 0.1623 1.0000
9.000 1.0682 0.03097 0.02174 -0.0100 0.1588 1.0000
9.250 1.0925 0.03155 0.02227 -0.0099 0.1558 1.0000
9.500 1.1115 0.03251 0.02354 -0.0091 0.1519 1.0000
9.750 1.1303 0.03335 0.02463 -0.0083 0.1474 1.0000
10.000 1.1510 0.03382 0.02517 -0.0077 0.1435 1.0000
10.250 1.1742 0.03414 0.02541 -0.0074 0.1403 1.0000
10.500 1.1866 0.03531 0.02703 -0.0060 0.1353 1.0000
10.750 1.2033 0.03589 0.02777 -0.0050 0.1308 1.0000
11.000 1.2230 0.03602 0.02787 -0.0042 0.1273 1.0000
11.250 1.2333 0.03724 0.02945 -0.0027 0.1224 1.0000
11.500 1.2457 0.03794 0.03033 -0.0013 0.1178 1.0000
11.750 1.2609 0.03805 0.03042 -0.0001 0.1143 1.0000
12.000 1.2635 0.03958 0.03230 0.0020 0.1092 1.0000
12.250 1.2697 0.04034 0.03319 0.0039 0.1050 1.0000
12.500 1.2762 0.04106 0.03395 0.0055 0.1015 1.0000
12.750 1.2742 0.04305 0.03624 0.0071 0.0966 1.0000
13.000 1.2775 0.04425 0.03750 0.0083 0.0928 1.0000
13.250 1.2751 0.04641 0.03982 0.0091 0.0892 1.0000
13.500 1.2688 0.04915 0.04276 0.0096 0.0854 1.0000
13.750 1.2656 0.05155 0.04521 0.0096 0.0824 1.0000
14.000 1.2546 0.05525 0.04905 0.0090 0.0799 1.0000
14.250 1.2334 0.06071 0.05476 0.0072 0.0778 1.0000
14.500 1.2033 0.06807 0.06236 0.0036 0.0767 1.0000
14.750 1.1073 0.08920 0.08385 -0.0097 0.0796 1.0000
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