NACA 63(3)-218 (naca633218-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 63(3)-218 (naca633218-il) Reynolds number: 100,000 Max Cl/Cd: 38.85 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca633218-il-100000-n5.txt Download as CSV file: xf-naca633218-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63(3)-218
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
------ -------- --------- --------- -------- -------- --------
-16.750 -0.7828 0.10795 0.10212 -0.0342 1.0000 0.0438
-16.500 -0.8276 0.09586 0.08973 -0.0416 1.0000 0.0437
-16.250 -0.8497 0.08862 0.08226 -0.0457 1.0000 0.0441
-16.000 -0.8663 0.08263 0.07606 -0.0488 1.0000 0.0445
-15.750 -0.8790 0.07748 0.07071 -0.0512 1.0000 0.0450
-15.500 -0.8891 0.07290 0.06591 -0.0531 1.0000 0.0456
-15.250 -0.8970 0.06875 0.06155 -0.0546 1.0000 0.0464
-15.000 -0.9025 0.06503 0.05757 -0.0558 1.0000 0.0471
-14.750 -0.9073 0.06157 0.05384 -0.0567 1.0000 0.0479
-14.500 -0.8962 0.05977 0.05211 -0.0568 1.0000 0.0490
-14.250 -0.8891 0.05773 0.05004 -0.0570 1.0000 0.0501
-14.000 -0.8835 0.05555 0.04778 -0.0573 1.0000 0.0514
-13.750 -0.8775 0.05338 0.04549 -0.0575 1.0000 0.0528
-13.500 -0.8708 0.05127 0.04321 -0.0575 1.0000 0.0543
-13.250 -0.8617 0.04942 0.04124 -0.0574 1.0000 0.0559
-13.000 -0.8494 0.04796 0.03983 -0.0572 1.0000 0.0574
-12.750 -0.8379 0.04644 0.03829 -0.0570 1.0000 0.0591
-12.500 -0.8259 0.04495 0.03674 -0.0567 1.0000 0.0610
-12.250 -0.8136 0.04352 0.03519 -0.0563 1.0000 0.0631
-12.000 -0.8005 0.04221 0.03390 -0.0559 1.0000 0.0651
-11.750 -0.7889 0.04088 0.03260 -0.0555 1.0000 0.0672
-11.500 -0.7767 0.03961 0.03132 -0.0550 1.0000 0.0697
-11.250 -0.7635 0.03844 0.03009 -0.0544 1.0000 0.0723
-11.000 -0.7532 0.03714 0.02884 -0.0537 1.0000 0.0750
-10.750 -0.7439 0.03583 0.02756 -0.0532 1.0000 0.0781
-10.500 -0.7283 0.03458 0.02627 -0.0535 0.9595 0.0825
-10.250 -0.7073 0.03305 0.02474 -0.0555 0.9283 0.0877
-10.000 -0.6892 0.03172 0.02332 -0.0563 0.9056 0.0940
-9.500 -0.6686 0.02914 0.02064 -0.0552 0.8676 0.1098
-9.250 -0.6632 0.02782 0.01934 -0.0539 0.8518 0.1197
-9.000 -0.6582 0.02658 0.01810 -0.0523 0.8377 0.1318
-8.750 -0.6542 0.02539 0.01693 -0.0504 0.8255 0.1466
-8.500 -0.6521 0.02432 0.01588 -0.0480 0.8139 0.1635
-8.250 -0.6489 0.02333 0.01495 -0.0456 0.8035 0.1854
-8.000 -0.6435 0.02232 0.01405 -0.0433 0.7940 0.2130
-7.750 -0.6357 0.02136 0.01326 -0.0413 0.7846 0.2483
-7.250 -0.6117 0.01990 0.01218 -0.0378 0.7679 0.3331
-7.000 -0.5940 0.01953 0.01193 -0.0365 0.7597 0.3752
-6.750 -0.5739 0.01931 0.01173 -0.0353 0.7528 0.4091
-6.500 -0.5518 0.01923 0.01166 -0.0345 0.7446 0.4360
-6.250 -0.5288 0.01920 0.01155 -0.0336 0.7374 0.4585
-6.000 -0.5044 0.01920 0.01148 -0.0330 0.7306 0.4769
-5.750 -0.4791 0.01923 0.01145 -0.0324 0.7234 0.4917
-5.500 -0.4542 0.01920 0.01128 -0.0318 0.7160 0.5050
-5.250 -0.4290 0.01916 0.01113 -0.0314 0.7077 0.5174
-5.000 -0.4021 0.01926 0.01119 -0.0309 0.7007 0.5269
-4.750 -0.3770 0.01918 0.01096 -0.0305 0.6941 0.5388
-4.500 -0.3496 0.01933 0.01112 -0.0300 0.6871 0.5475
-4.250 -0.3242 0.01920 0.01084 -0.0297 0.6807 0.5575
-4.000 -0.2967 0.01924 0.01086 -0.0293 0.6740 0.5633
-3.750 -0.2706 0.01910 0.01062 -0.0292 0.6666 0.5708
-3.500 -0.2443 0.01896 0.01035 -0.0289 0.6589 0.5772
-3.250 -0.2172 0.01894 0.01031 -0.0286 0.6497 0.5823
-3.000 -0.1910 0.01879 0.01003 -0.0284 0.6408 0.5891
-2.750 -0.1649 0.01863 0.00978 -0.0283 0.6287 0.5952
-2.500 -0.1381 0.01861 0.00971 -0.0279 0.6175 0.5999
-2.250 -0.1115 0.01852 0.00955 -0.0277 0.6082 0.6058
-2.000 -0.0850 0.01834 0.00925 -0.0278 0.5994 0.6127
-1.750 -0.0581 0.01833 0.00922 -0.0275 0.5895 0.6167
-1.500 -0.0314 0.01828 0.00914 -0.0272 0.5791 0.6218
-1.250 -0.0049 0.01817 0.00890 -0.0272 0.5673 0.6281
-1.000 0.0217 0.01809 0.00877 -0.0271 0.5541 0.6331
-0.750 0.0480 0.01809 0.00873 -0.0267 0.5400 0.6373
-0.500 0.0741 0.01807 0.00863 -0.0265 0.5247 0.6427
-0.250 0.1005 0.01800 0.00842 -0.0266 0.5083 0.6494
0.000 0.1262 0.01803 0.00841 -0.0261 0.4922 0.6534
0.250 0.1517 0.01809 0.00839 -0.0257 0.4762 0.6579
0.500 0.1774 0.01813 0.00834 -0.0255 0.4613 0.6638
0.750 0.2035 0.01815 0.00827 -0.0255 0.4488 0.6702
1.000 0.2285 0.01826 0.00835 -0.0250 0.4388 0.6744
1.250 0.2541 0.01834 0.00840 -0.0247 0.4308 0.6796
1.500 0.2802 0.01840 0.00839 -0.0246 0.4249 0.6860
1.750 0.3061 0.01848 0.00847 -0.0244 0.4203 0.6913
2.000 0.3314 0.01858 0.00860 -0.0240 0.4162 0.6965
2.250 0.3574 0.01868 0.00869 -0.0238 0.4124 0.7028
2.500 0.3835 0.01876 0.00875 -0.0238 0.4092 0.7090
2.750 0.4084 0.01889 0.00891 -0.0233 0.4063 0.7139
3.000 0.4343 0.01900 0.00907 -0.0231 0.4035 0.7203
3.250 0.4609 0.01910 0.00918 -0.0231 0.4011 0.7275
3.500 0.4857 0.01923 0.00938 -0.0226 0.3991 0.7326
3.750 0.5113 0.01935 0.00957 -0.0223 0.3975 0.7390
4.000 0.5380 0.01948 0.00973 -0.0224 0.3961 0.7465
4.250 0.5624 0.01963 0.00997 -0.0218 0.3949 0.7521
4.500 0.5876 0.01978 0.01019 -0.0214 0.3935 0.7591
4.750 0.6134 0.01995 0.01039 -0.0213 0.3919 0.7664
5.000 0.6374 0.02012 0.01064 -0.0207 0.3903 0.7726
5.250 0.6628 0.02029 0.01091 -0.0205 0.3886 0.7805
5.500 0.6871 0.02047 0.01120 -0.0200 0.3866 0.7876
5.750 0.7109 0.02066 0.01151 -0.0194 0.3846 0.7950
6.000 0.7361 0.02087 0.01182 -0.0192 0.3827 0.8034
6.250 0.7588 0.02107 0.01215 -0.0184 0.3808 0.8107
6.500 0.7820 0.02129 0.01243 -0.0179 0.3765 0.8199
6.750 0.8019 0.02151 0.01276 -0.0167 0.3705 0.8278
7.000 0.8220 0.02177 0.01309 -0.0157 0.3634 0.8378
7.250 0.8407 0.02201 0.01338 -0.0143 0.3573 0.8468
7.500 0.8598 0.02230 0.01378 -0.0131 0.3510 0.8578
7.750 0.8768 0.02259 0.01407 -0.0114 0.3438 0.8684
8.000 0.8919 0.02296 0.01447 -0.0097 0.3346 0.8807
8.250 0.9062 0.02342 0.01493 -0.0078 0.3236 0.8948
8.500 0.9191 0.02390 0.01545 -0.0058 0.3124 0.9114
8.750 0.9305 0.02438 0.01605 -0.0039 0.3012 0.9341
9.000 0.9460 0.02494 0.01695 -0.0038 0.2854 0.9909
9.250 0.9508 0.02583 0.01798 -0.0027 0.2199 1.0000
9.500 0.9442 0.02774 0.01951 -0.0010 0.2064 1.0000
10.000 0.9467 0.03160 0.02331 0.0009 0.1854 1.0000
10.250 0.9530 0.03330 0.02510 0.0014 0.1742 1.0000
10.500 0.9602 0.03499 0.02690 0.0018 0.1618 1.0000
10.750 0.9662 0.03682 0.02882 0.0021 0.1479 1.0000
11.000 0.9688 0.03899 0.03101 0.0024 0.1349 1.0000
11.250 0.9683 0.04151 0.03353 0.0025 0.1239 1.0000
11.500 0.9655 0.04432 0.03634 0.0025 0.1151 1.0000
11.750 0.9609 0.04741 0.03939 0.0024 0.1078 1.0000
12.000 0.9595 0.05026 0.04227 0.0022 0.1010 1.0000
12.250 0.9561 0.05340 0.04537 0.0019 0.0952 1.0000
12.500 0.9579 0.05605 0.04805 0.0017 0.0895 1.0000
12.750 0.9595 0.05878 0.05077 0.0014 0.0846 1.0000
13.000 0.9638 0.06118 0.05316 0.0012 0.0804 1.0000
13.250 0.9714 0.06322 0.05525 0.0011 0.0762 1.0000
13.500 0.9783 0.06537 0.05736 0.0009 0.0728 1.0000
13.750 0.9893 0.06702 0.05903 0.0010 0.0693 1.0000
14.000 1.0005 0.06869 0.06073 0.0010 0.0662 1.0000
14.250 1.0104 0.07052 0.06254 0.0009 0.0637 1.0000
14.500 1.0233 0.07201 0.06405 0.0010 0.0613 1.0000
14.750 1.0337 0.07394 0.06607 0.0009 0.0588 1.0000
15.000 1.0420 0.07617 0.06834 0.0005 0.0568 1.0000
15.250 1.0503 0.07833 0.07048 0.0001 0.0549 1.0000
15.500 1.0599 0.08045 0.07268 -0.0002 0.0532 1.0000
15.750 1.0669 0.08303 0.07543 -0.0008 0.0514 1.0000
16.000 1.0728 0.08571 0.07819 -0.0015 0.0497 1.0000
16.250 1.0792 0.08829 0.08081 -0.0023 0.0483 1.0000
16.500 1.0881 0.09046 0.08293 -0.0028 0.0469 1.0000
16.750 1.0888 0.09416 0.08687 -0.0042 0.0457 1.0000
17.000 1.0895 0.09785 0.09076 -0.0056 0.0445 1.0000
17.250 1.0900 0.10159 0.09465 -0.0071 0.0433 1.0000
17.500 1.0911 0.10522 0.09839 -0.0087 0.0423 1.0000
17.750 1.0945 0.10844 0.10168 -0.0101 0.0415 1.0000
18.000 1.1015 0.11102 0.10426 -0.0111 0.0407 1.0000
18.250 1.0927 0.11661 0.11008 -0.0140 0.0400 1.0000
18.500 1.0780 0.12342 0.11718 -0.0178 0.0395 1.0000
18.750 1.0597 0.13119 0.12522 -0.0223 0.0391 1.0000
19.000 1.0316 0.14140 0.13573 -0.0287 0.0388 1.0000
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