NACA 642-015A AIRFOIL (n64015a-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 642-015A AIRFOIL (n64015a-il) Reynolds number: 100,000 Max Cl/Cd: 36.81 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n64015a-il-100000-n5.txt Download as CSV file: xf-n64015a-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 642-015A AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-15.000 -0.7511 0.11842 0.11288 -0.0148 1.0000 0.0333
-14.750 -0.7867 0.10562 0.09996 -0.0228 1.0000 0.0330
-14.500 -0.8199 0.09535 0.08953 -0.0293 1.0000 0.0327
-14.250 -0.8495 0.08708 0.08106 -0.0340 1.0000 0.0325
-14.000 -0.8757 0.08015 0.07393 -0.0373 1.0000 0.0324
-13.750 -0.8987 0.07420 0.06775 -0.0396 1.0000 0.0323
-13.500 -0.9188 0.06903 0.06232 -0.0410 1.0000 0.0323
-13.250 -0.9358 0.06449 0.05752 -0.0416 1.0000 0.0324
-13.000 -0.9498 0.06046 0.05322 -0.0415 1.0000 0.0325
-12.750 -0.9606 0.05686 0.04931 -0.0410 1.0000 0.0327
-12.500 -0.9681 0.05362 0.04577 -0.0399 1.0000 0.0329
-12.250 -0.9722 0.05071 0.04254 -0.0387 1.0000 0.0332
-12.000 -0.9719 0.04808 0.03963 -0.0372 1.0000 0.0336
-11.750 -0.9620 0.04587 0.03732 -0.0364 1.0000 0.0341
-11.500 -0.9522 0.04404 0.03540 -0.0354 1.0000 0.0348
-11.250 -0.9424 0.04240 0.03366 -0.0343 1.0000 0.0357
-11.000 -0.9316 0.04079 0.03191 -0.0331 1.0000 0.0368
-10.750 -0.9186 0.03916 0.03008 -0.0319 1.0000 0.0381
-10.500 -0.9023 0.03751 0.02823 -0.0310 1.0000 0.0394
-10.250 -0.8834 0.03595 0.02644 -0.0301 1.0000 0.0405
-10.000 -0.8641 0.03443 0.02495 -0.0295 1.0000 0.0417
-9.750 -0.8476 0.03317 0.02369 -0.0286 1.0000 0.0431
-9.500 -0.8321 0.03203 0.02250 -0.0274 1.0000 0.0451
-9.250 -0.8163 0.03096 0.02132 -0.0261 1.0000 0.0476
-9.000 -0.8020 0.02982 0.02015 -0.0246 1.0000 0.0499
-8.750 -0.7908 0.02879 0.01915 -0.0227 1.0000 0.0522
-8.500 -0.7799 0.02784 0.01818 -0.0206 1.0000 0.0549
-8.250 -0.7688 0.02702 0.01725 -0.0183 1.0000 0.0584
-8.000 -0.7616 0.02606 0.01638 -0.0156 1.0000 0.0620
-7.750 -0.7532 0.02530 0.01560 -0.0128 1.0000 0.0665
-7.500 -0.7476 0.02453 0.01485 -0.0095 1.0000 0.0713
-7.250 -0.7432 0.02385 0.01420 -0.0060 1.0000 0.0772
-7.000 -0.7404 0.02323 0.01360 -0.0022 1.0000 0.0840
-6.750 -0.7294 0.02252 0.01292 -0.0001 0.9968 0.0951
-6.500 -0.7004 0.02138 0.01195 -0.0017 0.9866 0.1203
-6.250 -0.6737 0.02012 0.01099 -0.0030 0.9760 0.1690
-6.000 -0.6517 0.01859 0.01001 -0.0037 0.9646 0.2620
-5.750 -0.6341 0.01723 0.00949 -0.0029 0.9524 0.3973
-5.500 -0.6063 0.01690 0.00945 -0.0031 0.9429 0.4872
-5.250 -0.5777 0.01681 0.00936 -0.0032 0.9324 0.5301
-5.000 -0.5490 0.01678 0.00928 -0.0033 0.9223 0.5593
-4.750 -0.5182 0.01679 0.00920 -0.0037 0.9137 0.5842
-4.500 -0.4915 0.01690 0.00927 -0.0031 0.9029 0.6069
-4.250 -0.4622 0.01708 0.00941 -0.0028 0.8947 0.6293
-4.000 -0.4353 0.01720 0.00948 -0.0022 0.8845 0.6456
-3.750 -0.4070 0.01723 0.00942 -0.0020 0.8756 0.6573
-3.500 -0.3802 0.01714 0.00920 -0.0018 0.8665 0.6680
-3.250 -0.3515 0.01714 0.00914 -0.0017 0.8575 0.6751
-3.000 -0.3248 0.01698 0.00884 -0.0016 0.8491 0.6836
-2.750 -0.2967 0.01694 0.00875 -0.0015 0.8402 0.6888
-2.500 -0.2691 0.01682 0.00853 -0.0015 0.8324 0.6956
-2.250 -0.2429 0.01672 0.00836 -0.0012 0.8234 0.7017
-2.000 -0.2145 0.01665 0.00822 -0.0012 0.8161 0.7071
-1.750 -0.1892 0.01655 0.00804 -0.0010 0.8077 0.7143
-1.500 -0.1610 0.01649 0.00795 -0.0009 0.8004 0.7195
-1.250 -0.1341 0.01645 0.00787 -0.0008 0.7927 0.7253
-1.000 -0.1082 0.01637 0.00772 -0.0005 0.7851 0.7326
-0.750 -0.0800 0.01636 0.00770 -0.0005 0.7786 0.7378
-0.500 -0.0541 0.01633 0.00766 -0.0003 0.7709 0.7447
-0.250 -0.0262 0.01629 0.00757 -0.0002 0.7652 0.7509
0.000 0.0000 0.01632 0.00764 0.0000 0.7572 0.7572
0.250 0.0263 0.01629 0.00757 0.0002 0.7509 0.7652
0.500 0.0541 0.01633 0.00766 0.0003 0.7447 0.7709
0.750 0.0801 0.01636 0.00770 0.0005 0.7378 0.7786
1.000 0.1082 0.01637 0.00772 0.0005 0.7326 0.7851
1.250 0.1341 0.01645 0.00787 0.0008 0.7253 0.7927
1.500 0.1610 0.01649 0.00795 0.0009 0.7195 0.8005
1.750 0.1892 0.01655 0.00804 0.0010 0.7143 0.8077
2.000 0.2145 0.01665 0.00822 0.0012 0.7071 0.8161
2.250 0.2429 0.01672 0.00836 0.0012 0.7017 0.8235
2.500 0.2691 0.01682 0.00853 0.0015 0.6956 0.8324
2.750 0.2967 0.01694 0.00875 0.0015 0.6888 0.8402
3.000 0.3248 0.01698 0.00884 0.0016 0.6836 0.8491
3.250 0.3515 0.01713 0.00914 0.0017 0.6751 0.8575
3.500 0.3802 0.01714 0.00920 0.0018 0.6680 0.8665
3.750 0.4070 0.01723 0.00942 0.0020 0.6573 0.8756
4.000 0.4353 0.01720 0.00947 0.0022 0.6456 0.8845
4.250 0.4622 0.01707 0.00941 0.0028 0.6293 0.8947
4.500 0.4915 0.01690 0.00927 0.0031 0.6069 0.9030
4.750 0.5182 0.01678 0.00920 0.0037 0.5842 0.9137
5.000 0.5490 0.01678 0.00928 0.0033 0.5593 0.9224
5.250 0.5777 0.01681 0.00936 0.0032 0.5300 0.9324
5.500 0.6063 0.01690 0.00944 0.0031 0.4872 0.9429
5.750 0.6342 0.01723 0.00949 0.0029 0.3973 0.9525
6.000 0.6518 0.01859 0.01000 0.0036 0.2619 0.9646
6.250 0.6738 0.02012 0.01099 0.0030 0.1690 0.9760
6.500 0.7005 0.02138 0.01194 0.0017 0.1202 0.9867
6.750 0.7295 0.02252 0.01291 0.0000 0.0951 0.9969
7.000 0.7404 0.02322 0.01359 0.0022 0.0840 1.0000
7.250 0.7432 0.02385 0.01420 0.0060 0.0772 1.0000
7.500 0.7476 0.02453 0.01484 0.0095 0.0713 1.0000
7.750 0.7533 0.02529 0.01560 0.0128 0.0665 1.0000
8.000 0.7617 0.02605 0.01637 0.0155 0.0619 1.0000
8.250 0.7690 0.02701 0.01725 0.0182 0.0583 1.0000
8.500 0.7802 0.02784 0.01818 0.0205 0.0549 1.0000
8.750 0.7911 0.02879 0.01915 0.0227 0.0522 1.0000
9.000 0.8025 0.02982 0.02015 0.0245 0.0499 1.0000
9.250 0.8168 0.03096 0.02132 0.0260 0.0475 1.0000
9.500 0.8327 0.03203 0.02250 0.0273 0.0451 1.0000
9.750 0.8482 0.03317 0.02370 0.0285 0.0431 1.0000
10.000 0.8647 0.03443 0.02496 0.0294 0.0417 1.0000
10.250 0.8841 0.03596 0.02645 0.0300 0.0405 1.0000
10.500 0.9029 0.03752 0.02824 0.0309 0.0394 1.0000
10.750 0.9192 0.03916 0.03009 0.0318 0.0381 1.0000
11.000 0.9323 0.04080 0.03192 0.0329 0.0368 1.0000
11.250 0.9431 0.04241 0.03367 0.0341 0.0357 1.0000
11.500 0.9530 0.04404 0.03541 0.0352 0.0348 1.0000
11.750 0.9629 0.04588 0.03733 0.0362 0.0341 1.0000
12.000 0.9729 0.04811 0.03965 0.0371 0.0336 1.0000
12.250 0.9729 0.05073 0.04258 0.0385 0.0332 1.0000
12.500 0.9688 0.05366 0.04582 0.0398 0.0329 1.0000
12.750 0.9614 0.05690 0.04936 0.0408 0.0327 1.0000
13.000 0.9507 0.06050 0.05327 0.0414 0.0325 1.0000
13.250 0.9367 0.06454 0.05758 0.0414 0.0324 1.0000
13.500 0.9196 0.06911 0.06241 0.0408 0.0323 1.0000
13.750 0.8995 0.07430 0.06785 0.0394 0.0323 1.0000
14.000 0.8764 0.08028 0.07406 0.0370 0.0324 1.0000
14.250 0.8501 0.08724 0.08122 0.0336 0.0325 1.0000
14.500 0.8206 0.09555 0.08973 0.0289 0.0327 1.0000
14.750 0.7872 0.10590 0.10025 0.0224 0.0330 1.0000
15.000 0.7514 0.11884 0.11330 0.0143 0.0333 1.0000
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