NACA 64(1)-112 (naca641112-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 64(1)-112 (naca641112-il) Reynolds number: 200,000 Max Cl/Cd: 54.36 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca641112-il-200000.txt Download as CSV file: xf-naca641112-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64(1)-112
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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.6188 0.09354 0.09002 -0.0198 1.0000 0.0683
-10.500 -0.6215 0.08853 0.08503 -0.0225 1.0000 0.0698
-10.250 -0.6429 0.07995 0.07647 -0.0296 1.0000 0.0706
-10.000 -0.6725 0.07275 0.06923 -0.0351 1.0000 0.0707
-9.750 -0.6992 0.06777 0.06417 -0.0374 1.0000 0.0708
-9.500 -0.7204 0.06426 0.06057 -0.0369 1.0000 0.0715
-9.250 -0.7347 0.06087 0.05702 -0.0363 1.0000 0.0735
-8.250 -0.7598 0.03769 0.03132 -0.0274 1.0000 0.0423
-8.000 -0.7443 0.03339 0.02681 -0.0265 1.0000 0.0412
-7.750 -0.7285 0.03186 0.02496 -0.0248 1.0000 0.0418
-7.500 -0.7145 0.02950 0.02229 -0.0230 1.0000 0.0423
-7.250 -0.7003 0.02708 0.01966 -0.0211 1.0000 0.0426
-7.000 -0.6870 0.02502 0.01745 -0.0188 1.0000 0.0430
-6.750 -0.6748 0.02339 0.01574 -0.0165 1.0000 0.0437
-6.500 -0.6631 0.02223 0.01454 -0.0141 1.0000 0.0446
-6.250 -0.6330 0.02103 0.01328 -0.0151 0.9965 0.0466
-6.000 -0.5941 0.01997 0.01215 -0.0177 0.9909 0.0502
-5.750 -0.5544 0.01895 0.01101 -0.0202 0.9855 0.0526
-5.500 -0.5196 0.01724 0.00941 -0.0223 0.9795 0.0571
-5.250 -0.4802 0.01647 0.00858 -0.0251 0.9736 0.0640
-5.000 -0.4439 0.01530 0.00748 -0.0276 0.9673 0.0737
-4.750 -0.4088 0.01432 0.00655 -0.0296 0.9596 0.0933
-4.500 -0.3887 0.01177 0.00531 -0.0303 0.9487 0.3259
-4.250 -0.3643 0.01094 0.00535 -0.0300 0.9394 0.5423
-4.000 -0.3355 0.01095 0.00539 -0.0298 0.9298 0.5868
-3.750 -0.3088 0.01102 0.00544 -0.0292 0.9197 0.6157
-3.500 -0.2815 0.01110 0.00546 -0.0286 0.9110 0.6372
-3.250 -0.2565 0.01121 0.00552 -0.0276 0.9006 0.6574
-3.000 -0.2325 0.01144 0.00580 -0.0261 0.8910 0.6804
-2.750 -0.2087 0.01171 0.00605 -0.0243 0.8828 0.7037
-2.500 -0.1845 0.01186 0.00620 -0.0231 0.8726 0.7188
-2.250 -0.1588 0.01188 0.00618 -0.0222 0.8642 0.7270
-2.000 -0.1327 0.01182 0.00603 -0.0218 0.8551 0.7348
-1.750 -0.1066 0.01182 0.00600 -0.0212 0.8466 0.7420
-1.500 -0.0801 0.01177 0.00588 -0.0208 0.8388 0.7502
-1.250 -0.0538 0.01177 0.00586 -0.0204 0.8300 0.7567
-1.000 -0.0269 0.01171 0.00572 -0.0201 0.8227 0.7645
-0.750 -0.0005 0.01170 0.00573 -0.0197 0.8138 0.7708
-0.500 0.0267 0.01167 0.00561 -0.0195 0.8071 0.7791
-0.250 0.0531 0.01168 0.00566 -0.0192 0.7987 0.7851
0.000 0.0804 0.01166 0.00559 -0.0190 0.7922 0.7941
0.250 0.1065 0.01169 0.00567 -0.0185 0.7840 0.8005
0.500 0.1337 0.01168 0.00562 -0.0184 0.7774 0.8095
0.750 0.1598 0.01172 0.00572 -0.0179 0.7701 0.8163
1.000 0.1868 0.01174 0.00573 -0.0177 0.7635 0.8254
1.250 0.2126 0.01179 0.00583 -0.0171 0.7569 0.8333
1.500 0.2389 0.01182 0.00590 -0.0168 0.7498 0.8424
1.750 0.2649 0.01186 0.00596 -0.0162 0.7440 0.8514
2.000 0.2902 0.01189 0.00607 -0.0156 0.7354 0.8600
2.250 0.3163 0.01191 0.00609 -0.0150 0.7292 0.8703
2.500 0.3405 0.01196 0.00625 -0.0142 0.7209 0.8795
2.750 0.3659 0.01197 0.00629 -0.0133 0.7150 0.8895
3.000 0.3899 0.01194 0.00634 -0.0123 0.7041 0.9008
3.250 0.4133 0.01172 0.00614 -0.0107 0.6886 0.9114
3.500 0.4371 0.01142 0.00578 -0.0090 0.6687 0.9223
3.750 0.4615 0.01119 0.00559 -0.0077 0.6460 0.9343
4.000 0.4892 0.01104 0.00546 -0.0073 0.6265 0.9462
4.250 0.5202 0.01095 0.00541 -0.0077 0.6045 0.9578
4.500 0.5572 0.01089 0.00540 -0.0094 0.5742 0.9666
4.750 0.5941 0.01093 0.00534 -0.0111 0.5176 0.9756
5.000 0.6184 0.01287 0.00583 -0.0122 0.2197 0.9877
5.250 0.6463 0.01515 0.00723 -0.0144 0.0841 1.0000
5.500 0.6506 0.01573 0.00779 -0.0109 0.0744 1.0000
5.750 0.6616 0.01661 0.00857 -0.0086 0.0662 1.0000
6.000 0.6817 0.01729 0.00930 -0.0077 0.0603 1.0000
6.250 0.6999 0.01840 0.01033 -0.0066 0.0557 1.0000
6.500 0.7210 0.01945 0.01141 -0.0058 0.0522 1.0000
6.750 0.7438 0.02032 0.01231 -0.0052 0.0486 1.0000
7.000 0.7666 0.02146 0.01340 -0.0047 0.0459 1.0000
7.250 0.7921 0.02392 0.01581 -0.0046 0.0438 1.0000
7.500 0.8175 0.02514 0.01721 -0.0042 0.0430 1.0000
7.750 0.8424 0.02652 0.01877 -0.0037 0.0417 1.0000
8.000 0.8662 0.02797 0.02041 -0.0032 0.0400 1.0000
8.250 0.8894 0.02993 0.02260 -0.0027 0.0392 1.0000
8.500 0.9106 0.03243 0.02540 -0.0019 0.0391 1.0000
8.750 0.9285 0.03556 0.02894 -0.0007 0.0396 1.0000
9.000 0.9420 0.03939 0.03317 0.0008 0.0409 1.0000
9.250 0.9514 0.04362 0.03775 0.0023 0.0421 1.0000
9.500 0.9695 0.04711 0.04145 0.0032 0.0453 1.0000
12.000 0.7934 0.10495 0.10148 0.0025 0.0664 1.0000
12.250 0.7638 0.11367 0.11024 -0.0049 0.0662 1.0000
12.500 0.7170 0.12912 0.12562 -0.0207 0.0641 1.0000
12.750 0.7114 0.13530 0.13177 -0.0249 0.0614 1.0000
13.000 0.7131 0.13990 0.13637 -0.0271 0.0592 1.0000
13.250 0.7201 0.14334 0.13981 -0.0281 0.0574 1.0000
13.500 0.7314 0.14606 0.14255 -0.0280 0.0561 1.0000
13.750 0.5744 0.14627 0.14313 -0.0288 0.0591 1.0000
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Polar data table (+)
Polar graphs
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