NACA 66-018 (naca66-018-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 66-018 (naca66-018-il) Reynolds number: 100,000 Max Cl/Cd: 18.81 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca66-018-il-100000-n5.txt Download as CSV file: xf-naca66-018-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66-018
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
------ -------- --------- --------- -------- -------- --------
-16.000 -0.6501 0.10776 0.10217 -0.0607 1.0000 0.0328
-15.750 -0.6878 0.09702 0.09124 -0.0670 1.0000 0.0324
-15.500 -0.7204 0.08870 0.08270 -0.0712 1.0000 0.0322
-15.250 -0.7480 0.08209 0.07588 -0.0737 1.0000 0.0321
-15.000 -0.7713 0.07661 0.07017 -0.0750 1.0000 0.0320
-14.750 -0.7912 0.07197 0.06530 -0.0756 1.0000 0.0320
-14.500 -0.8083 0.06788 0.06098 -0.0755 1.0000 0.0320
-14.250 -0.8225 0.06425 0.05711 -0.0749 1.0000 0.0321
-14.000 -0.8341 0.06102 0.05364 -0.0739 1.0000 0.0322
-13.750 -0.8434 0.05823 0.05061 -0.0725 1.0000 0.0324
-13.500 -0.8457 0.05550 0.04763 -0.0717 0.9885 0.0326
-13.250 -0.8401 0.05261 0.04439 -0.0722 0.9762 0.0330
-13.000 -0.8305 0.04992 0.04131 -0.0728 0.9687 0.0337
-12.750 -0.8145 0.04763 0.03878 -0.0737 0.9627 0.0347
-12.500 -0.7904 0.04581 0.03683 -0.0751 0.9580 0.0355
-12.250 -0.7687 0.04419 0.03507 -0.0759 0.9523 0.0365
-12.000 -0.7427 0.04260 0.03329 -0.0769 0.9479 0.0376
-11.750 -0.7151 0.04118 0.03168 -0.0777 0.9433 0.0386
-11.500 -0.6879 0.03996 0.03026 -0.0782 0.9383 0.0397
-11.250 -0.6605 0.03888 0.02912 -0.0788 0.9340 0.0409
-11.000 -0.6398 0.03791 0.02816 -0.0788 0.9288 0.0427
-10.750 -0.6198 0.03703 0.02720 -0.0786 0.9235 0.0447
-10.500 -0.5987 0.03619 0.02622 -0.0783 0.9192 0.0468
-10.250 -0.5817 0.03526 0.02531 -0.0776 0.9147 0.0484
-10.000 -0.5671 0.03437 0.02441 -0.0768 0.9099 0.0504
-9.750 -0.5521 0.03354 0.02349 -0.0759 0.9057 0.0536
-9.500 -0.5385 0.03265 0.02255 -0.0748 0.9022 0.0570
-9.250 -0.5258 0.03183 0.02171 -0.0736 0.8978 0.0605
-9.000 -0.5129 0.03104 0.02086 -0.0724 0.8937 0.0650
-8.750 -0.5005 0.03021 0.02003 -0.0710 0.8900 0.0715
-8.500 -0.4878 0.02939 0.01924 -0.0696 0.8869 0.0818
-8.250 -0.4757 0.02857 0.01853 -0.0681 0.8834 0.1000
-8.000 -0.4673 0.02754 0.01791 -0.0663 0.8794 0.1507
-7.750 -0.4628 0.02641 0.01729 -0.0639 0.8754 0.2350
-7.500 -0.4630 0.02528 0.01665 -0.0606 0.8718 0.3197
-7.250 -0.4603 0.02449 0.01637 -0.0572 0.8690 0.4073
-7.000 -0.4103 0.02644 0.01899 -0.0576 0.8683 0.5225
-6.750 -0.3676 0.02881 0.02145 -0.0572 0.8666 0.5791
-6.500 -0.3578 0.02953 0.02214 -0.0541 0.8630 0.6130
-6.250 -0.3469 0.03020 0.02272 -0.0511 0.8597 0.6365
-6.000 -0.3325 0.03050 0.02290 -0.0490 0.8569 0.6509
-5.500 -0.2840 0.03125 0.02338 -0.0476 0.8531 0.6683
-5.250 -0.2776 0.03113 0.02316 -0.0446 0.8504 0.6814
-5.000 -0.2403 0.03182 0.02374 -0.0458 0.8484 0.6847
-4.500 -0.2036 0.03227 0.02404 -0.0433 0.8431 0.7002
-4.250 -0.1705 0.03263 0.02431 -0.0442 0.8416 0.7039
-4.000 -0.1706 0.03246 0.02408 -0.0403 0.8386 0.7152
-3.750 -0.1348 0.03274 0.02427 -0.0416 0.8375 0.7177
-3.500 -0.1056 0.03289 0.02435 -0.0421 0.8363 0.7216
-3.250 -0.1060 0.03259 0.02399 -0.0381 0.8340 0.7318
-3.000 -0.0777 0.03296 0.02433 -0.0385 0.8315 0.7342
-2.750 -0.0561 0.03327 0.02461 -0.0379 0.8289 0.7379
-2.500 -0.0755 0.03329 0.02462 -0.0307 0.8244 0.7485
-2.250 -0.0442 0.03349 0.02479 -0.0316 0.8230 0.7505
-2.000 -0.0164 0.03361 0.02488 -0.0320 0.8213 0.7532
-1.500 -0.0046 0.03334 0.02454 -0.0255 0.8169 0.7658
-1.250 0.0074 0.03397 0.02520 -0.0233 0.8130 0.7684
-0.750 -0.0304 0.03411 0.02532 -0.0079 0.8027 0.7828
-0.500 0.0033 0.03415 0.02535 -0.0094 0.8014 0.7841
-0.250 0.0359 0.03413 0.02533 -0.0107 0.8001 0.7857
0.000 0.0018 0.03479 0.02603 -0.0003 0.7918 0.7915
0.250 -0.0396 0.03411 0.02531 0.0113 0.7854 0.8005
0.500 -0.0071 0.03413 0.02534 0.0100 0.7838 0.8017
0.750 0.0270 0.03410 0.02531 0.0085 0.7824 0.8030
1.250 -0.0061 0.03404 0.02527 0.0231 0.7683 0.8127
1.500 0.0017 0.03332 0.02451 0.0260 0.7655 0.8171
2.000 0.0151 0.03358 0.02484 0.0322 0.7530 0.8214
2.250 0.0426 0.03348 0.02477 0.0319 0.7502 0.8231
2.500 0.0735 0.03329 0.02463 0.0310 0.7482 0.8245
2.750 0.0566 0.03329 0.02464 0.0378 0.7379 0.8288
3.000 0.0781 0.03301 0.02438 0.0384 0.7341 0.8312
3.250 0.1049 0.03261 0.02401 0.0382 0.7315 0.8340
3.500 0.1050 0.03287 0.02433 0.0422 0.7216 0.8364
3.750 0.1336 0.03273 0.02426 0.0418 0.7175 0.8377
4.000 0.1693 0.03246 0.02407 0.0405 0.7149 0.8388
4.250 0.1702 0.03263 0.02430 0.0442 0.7038 0.8416
4.500 0.2030 0.03227 0.02404 0.0434 0.6999 0.8431
5.000 0.2399 0.03186 0.02378 0.0458 0.6845 0.8483
5.250 0.2736 0.03125 0.02327 0.0451 0.6803 0.8505
5.500 0.2832 0.03125 0.02338 0.0477 0.6681 0.8532
6.000 0.3314 0.03054 0.02294 0.0491 0.6507 0.8571
6.500 0.3586 0.02950 0.02211 0.0540 0.6130 0.8629
6.750 0.3681 0.02880 0.02145 0.0572 0.5789 0.8666
7.000 0.4111 0.02640 0.01894 0.0575 0.5211 0.8684
7.250 0.4604 0.02448 0.01635 0.0571 0.4066 0.8691
7.500 0.4629 0.02529 0.01664 0.0606 0.3178 0.8719
7.750 0.4630 0.02641 0.01728 0.0638 0.2336 0.8754
8.000 0.4674 0.02756 0.01791 0.0662 0.1477 0.8792
8.250 0.4764 0.02855 0.01852 0.0680 0.1002 0.8833
8.500 0.4881 0.02938 0.01923 0.0696 0.0813 0.8869
8.750 0.5009 0.03021 0.02002 0.0710 0.0712 0.8901
9.000 0.5134 0.03103 0.02085 0.0723 0.0647 0.8938
9.250 0.5265 0.03182 0.02170 0.0735 0.0603 0.8979
9.500 0.5390 0.03264 0.02253 0.0747 0.0566 0.9023
9.750 0.5528 0.03353 0.02347 0.0758 0.0534 0.9058
10.000 0.5678 0.03437 0.02440 0.0767 0.0502 0.9100
10.250 0.5826 0.03524 0.02529 0.0775 0.0483 0.9147
10.500 0.5993 0.03618 0.02621 0.0782 0.0466 0.9193
10.750 0.6209 0.03702 0.02718 0.0784 0.0448 0.9235
11.000 0.6419 0.03791 0.02816 0.0786 0.0428 0.9287
11.250 0.6628 0.03884 0.02911 0.0786 0.0412 0.9339
11.500 0.6893 0.03995 0.03023 0.0780 0.0397 0.9383
11.750 0.7162 0.04116 0.03166 0.0775 0.0386 0.9434
12.000 0.7437 0.04259 0.03328 0.0767 0.0375 0.9480
12.250 0.7695 0.04420 0.03508 0.0757 0.0364 0.9525
12.500 0.7920 0.04588 0.03692 0.0749 0.0355 0.9581
12.750 0.8149 0.04761 0.03875 0.0735 0.0345 0.9630
13.000 0.8330 0.04985 0.04121 0.0725 0.0337 0.9689
13.250 0.8428 0.05255 0.04430 0.0719 0.0331 0.9764
13.500 0.8479 0.05542 0.04754 0.0714 0.0326 0.9894
13.750 0.8434 0.05825 0.05064 0.0724 0.0323 1.0000
14.000 0.8352 0.06102 0.05363 0.0738 0.0322 1.0000
14.250 0.8243 0.06417 0.05702 0.0747 0.0321 1.0000
14.500 0.8101 0.06781 0.06090 0.0753 0.0320 1.0000
14.750 0.7928 0.07194 0.06526 0.0754 0.0319 1.0000
15.000 0.7722 0.07665 0.07021 0.0748 0.0319 1.0000
15.250 0.7496 0.08206 0.07584 0.0735 0.0320 1.0000
15.500 0.7226 0.08859 0.08259 0.0710 0.0321 1.0000
15.750 0.6917 0.09662 0.09082 0.0670 0.0324 1.0000
16.000 0.6516 0.10778 0.10219 0.0605 0.0327 1.0000
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Polar data table (+)
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