NACA 64(3)-418 (naca643418-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64(3)-418 (naca643418-il) Reynolds number: 100,000 Max Cl/Cd: 42.68 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca643418-il-100000-n5.txt Download as CSV file: xf-naca643418-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64(3)-418
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
------ -------- --------- --------- -------- -------- --------
-14.750 -0.6934 0.07714 0.07070 -0.0771 1.0000 0.0420
-14.500 -0.7092 0.07239 0.06582 -0.0793 1.0000 0.0423
-14.250 -0.7265 0.06772 0.06097 -0.0812 1.0000 0.0425
-14.000 -0.7385 0.06390 0.05702 -0.0823 1.0000 0.0428
-13.750 -0.7486 0.06048 0.05344 -0.0830 1.0000 0.0431
-13.500 -0.7564 0.05742 0.05023 -0.0833 1.0000 0.0436
-13.250 -0.7631 0.05459 0.04725 -0.0832 1.0000 0.0440
-13.000 -0.7685 0.05197 0.04448 -0.0828 1.0000 0.0445
-12.750 -0.7724 0.04956 0.04189 -0.0820 1.0000 0.0450
-12.500 -0.7747 0.04740 0.03957 -0.0808 1.0000 0.0455
-12.250 -0.7762 0.04547 0.03748 -0.0793 1.0000 0.0461
-12.000 -0.7790 0.04379 0.03564 -0.0772 1.0000 0.0467
-11.750 -0.7858 0.04251 0.03420 -0.0742 1.0000 0.0473
-11.500 -0.7793 0.04132 0.03301 -0.0727 0.9965 0.0481
-11.250 -0.7516 0.03978 0.03145 -0.0748 0.9854 0.0496
-11.000 -0.7230 0.03820 0.02975 -0.0770 0.9762 0.0512
-10.750 -0.6910 0.03659 0.02792 -0.0792 0.9690 0.0531
-10.500 -0.6591 0.03518 0.02639 -0.0808 0.9608 0.0548
-10.250 -0.6279 0.03397 0.02522 -0.0828 0.9526 0.0569
-10.000 -0.5975 0.03280 0.02396 -0.0846 0.9437 0.0597
-9.750 -0.5678 0.03174 0.02279 -0.0858 0.9344 0.0624
-9.500 -0.5396 0.03065 0.02173 -0.0872 0.9255 0.0651
-9.250 -0.5165 0.02974 0.02076 -0.0875 0.9140 0.0684
-9.000 -0.4940 0.02879 0.01976 -0.0878 0.9040 0.0722
-8.750 -0.4768 0.02792 0.01887 -0.0874 0.8924 0.0761
-8.500 -0.4609 0.02716 0.01803 -0.0864 0.8810 0.0807
-8.250 -0.4484 0.02623 0.01710 -0.0852 0.8710 0.0859
-8.000 -0.4393 0.02557 0.01639 -0.0832 0.8591 0.0920
-7.750 -0.4306 0.02478 0.01560 -0.0813 0.8494 0.0990
-7.500 -0.4199 0.02403 0.01487 -0.0796 0.8393 0.1088
-7.250 -0.4080 0.02326 0.01411 -0.0781 0.8309 0.1227
-7.000 -0.3969 0.02248 0.01341 -0.0764 0.8216 0.1423
-6.750 -0.3846 0.02157 0.01261 -0.0749 0.8145 0.1733
-6.500 -0.3756 0.02062 0.01191 -0.0732 0.8051 0.2187
-6.250 -0.3653 0.01944 0.01113 -0.0716 0.7982 0.2970
-6.000 -0.3519 0.01894 0.01126 -0.0696 0.7903 0.3962
-5.750 -0.3293 0.01894 0.01130 -0.0687 0.7833 0.4568
-5.500 -0.3036 0.01898 0.01122 -0.0682 0.7781 0.4893
-5.250 -0.2802 0.01917 0.01136 -0.0673 0.7704 0.5117
-5.000 -0.2545 0.01935 0.01143 -0.0667 0.7644 0.5302
-4.750 -0.2271 0.01954 0.01150 -0.0662 0.7598 0.5461
-4.500 -0.2031 0.01980 0.01170 -0.0653 0.7525 0.5608
-4.250 -0.1774 0.02005 0.01186 -0.0646 0.7465 0.5762
-4.000 -0.1499 0.02041 0.01215 -0.0637 0.7419 0.5896
-3.750 -0.1252 0.02070 0.01242 -0.0627 0.7353 0.5985
-3.500 -0.0992 0.02071 0.01234 -0.0624 0.7295 0.6052
-3.250 -0.0719 0.02044 0.01188 -0.0628 0.7250 0.6120
-3.000 -0.0452 0.02046 0.01185 -0.0624 0.7202 0.6153
-2.750 -0.0199 0.02047 0.01181 -0.0621 0.7143 0.6193
-2.500 0.0072 0.02035 0.01159 -0.0622 0.7096 0.6242
-2.250 0.0359 0.02010 0.01117 -0.0629 0.7057 0.6302
-2.000 0.0610 0.02017 0.01123 -0.0624 0.7002 0.6332
-1.750 0.0868 0.02018 0.01121 -0.0622 0.6948 0.6367
-1.500 0.1145 0.02010 0.01106 -0.0623 0.6905 0.6409
-1.250 0.1438 0.01995 0.01079 -0.0629 0.6871 0.6457
-1.000 0.1692 0.01995 0.01076 -0.0630 0.6819 0.6497
-0.750 0.1947 0.02002 0.01084 -0.0627 0.6773 0.6526
-0.500 0.2218 0.02004 0.01083 -0.0627 0.6734 0.6563
-0.250 0.2506 0.02000 0.01073 -0.0631 0.6703 0.6605
0.000 0.2782 0.02001 0.01069 -0.0635 0.6665 0.6651
0.250 0.3029 0.02011 0.01082 -0.0634 0.6615 0.6690
0.500 0.3289 0.02019 0.01092 -0.0632 0.6573 0.6722
0.750 0.3567 0.02023 0.01094 -0.0633 0.6540 0.6762
1.000 0.3861 0.02024 0.01091 -0.0637 0.6514 0.6812
1.250 0.4110 0.02043 0.01113 -0.0638 0.6472 0.6868
1.500 0.4342 0.02067 0.01146 -0.0633 0.6430 0.6903
1.750 0.4599 0.02082 0.01165 -0.0631 0.6394 0.6945
2.000 0.4879 0.02089 0.01173 -0.0633 0.6363 0.6995
2.500 0.5402 0.02125 0.01216 -0.0633 0.6297 0.7093
2.750 0.5617 0.02159 0.01262 -0.0626 0.6253 0.7143
3.000 0.5875 0.02179 0.01286 -0.0626 0.6216 0.7205
3.250 0.6154 0.02190 0.01301 -0.0628 0.6185 0.7263
3.500 0.6437 0.02196 0.01312 -0.0628 0.6160 0.7315
3.750 0.6624 0.02242 0.01371 -0.0618 0.6107 0.7380
4.000 0.6844 0.02277 0.01415 -0.0613 0.6060 0.7445
4.250 0.7090 0.02295 0.01443 -0.0608 0.6024 0.7499
4.500 0.7381 0.02302 0.01455 -0.0610 0.5995 0.7566
4.750 0.7637 0.02326 0.01487 -0.0609 0.5960 0.7636
5.000 0.7756 0.02392 0.01573 -0.0589 0.5898 0.7704
5.250 0.8004 0.02417 0.01606 -0.0586 0.5856 0.7788
5.500 0.8287 0.02415 0.01613 -0.0585 0.5822 0.7855
5.750 0.8508 0.02441 0.01651 -0.0577 0.5773 0.7938
6.000 0.8651 0.02483 0.01708 -0.0558 0.5696 0.8019
6.250 0.8990 0.02434 0.01664 -0.0561 0.5641 0.8099
6.500 0.9107 0.02474 0.01720 -0.0538 0.5551 0.8193
6.750 0.9406 0.02425 0.01677 -0.0534 0.5473 0.8284
7.000 0.9522 0.02446 0.01712 -0.0509 0.5370 0.8387
7.250 0.9858 0.02375 0.01643 -0.0509 0.5277 0.8489
7.500 0.9873 0.02422 0.01710 -0.0469 0.5164 0.8615
7.750 1.0024 0.02418 0.01716 -0.0447 0.5058 0.8747
8.000 1.0208 0.02392 0.01697 -0.0427 0.4942 0.8891
8.250 1.0147 0.02445 0.01769 -0.0378 0.4817 0.9102
8.500 1.0197 0.02481 0.01819 -0.0347 0.4668 0.9386
8.750 1.0306 0.02530 0.01878 -0.0335 0.4472 1.0000
9.000 1.0350 0.02643 0.01994 -0.0320 0.4242 1.0000
9.250 1.0401 0.02759 0.02105 -0.0305 0.3923 1.0000
9.500 1.0524 0.02815 0.02129 -0.0291 0.3481 1.0000
9.750 1.0528 0.02979 0.02263 -0.0273 0.3062 1.0000
10.000 1.0481 0.03201 0.02459 -0.0255 0.2687 1.0000
10.250 1.0428 0.03447 0.02683 -0.0240 0.2369 1.0000
10.500 1.0382 0.03703 0.02921 -0.0228 0.2089 1.0000
10.750 1.0348 0.03961 0.03165 -0.0218 0.1848 1.0000
11.000 1.0343 0.04205 0.03398 -0.0210 0.1628 1.0000
11.250 1.0344 0.04450 0.03633 -0.0204 0.1438 1.0000
11.500 1.0356 0.04693 0.03866 -0.0199 0.1276 1.0000
11.750 1.0384 0.04929 0.04095 -0.0195 0.1140 1.0000
12.000 1.0421 0.05162 0.04323 -0.0192 0.1024 1.0000
12.250 1.0468 0.05390 0.04551 -0.0190 0.0927 1.0000
12.500 1.0513 0.05625 0.04783 -0.0188 0.0849 1.0000
12.750 1.0557 0.05865 0.05021 -0.0187 0.0786 1.0000
13.000 1.0620 0.06091 0.05250 -0.0187 0.0726 1.0000
13.250 1.0658 0.06346 0.05499 -0.0187 0.0683 1.0000
13.500 1.0736 0.06562 0.05725 -0.0187 0.0637 1.0000
13.750 1.0786 0.06811 0.05975 -0.0189 0.0604 1.0000
14.000 1.0862 0.07034 0.06204 -0.0190 0.0570 1.0000
14.250 1.0928 0.07273 0.06448 -0.0192 0.0542 1.0000
14.500 1.0989 0.07517 0.06692 -0.0194 0.0519 1.0000
14.750 1.1075 0.07738 0.06924 -0.0196 0.0495 1.0000
15.000 1.1143 0.07983 0.07175 -0.0199 0.0474 1.0000
15.250 1.1208 0.08228 0.07416 -0.0203 0.0458 1.0000
15.500 1.1291 0.08464 0.07670 -0.0205 0.0439 1.0000
15.750 1.1362 0.08714 0.07930 -0.0210 0.0423 1.0000
16.000 1.1422 0.08979 0.08199 -0.0216 0.0409 1.0000
16.250 1.1496 0.09219 0.08439 -0.0221 0.0397 1.0000
16.500 1.1555 0.09503 0.08743 -0.0226 0.0386 1.0000
16.750 1.1608 0.09795 0.09052 -0.0233 0.0376 1.0000
17.000 1.1653 0.10098 0.09368 -0.0242 0.0367 1.0000
17.250 1.1688 0.10414 0.09694 -0.0252 0.0358 1.0000
17.500 1.1739 0.10702 0.09987 -0.0262 0.0351 1.0000
17.750 1.1782 0.11008 0.10300 -0.0273 0.0344 1.0000
18.000 1.1724 0.11500 0.10820 -0.0295 0.0338 1.0000
18.250 1.1662 0.12008 0.11352 -0.0318 0.0332 1.0000
18.500 1.1582 0.12557 0.11924 -0.0347 0.0327 1.0000
18.750 1.1490 0.13142 0.12530 -0.0379 0.0322 1.0000
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