NACA 66 (p51hroot-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 66 (p51hroot-il) Reynolds number: 50,000 Max Cl/Cd: 19.47 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-p51hroot-il-50000-n5.txt Download as CSV file: xf-p51hroot-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.4693 0.11027 0.10310 -0.0658 1.0000 0.0605
-12.500 -0.4819 0.10573 0.09863 -0.0667 1.0000 0.0601
-12.250 -0.4990 0.10156 0.09453 -0.0669 1.0000 0.0597
-12.000 -0.5214 0.09754 0.09057 -0.0667 1.0000 0.0591
-11.750 -0.5469 0.09382 0.08689 -0.0661 1.0000 0.0584
-11.500 -0.5779 0.08999 0.08307 -0.0652 1.0000 0.0579
-11.250 -0.6062 0.08573 0.07877 -0.0651 0.9981 0.0572
-11.000 -0.6292 0.08033 0.07320 -0.0675 0.9918 0.0568
-10.750 -0.6510 0.07585 0.06851 -0.0683 0.9855 0.0565
-10.500 -0.6705 0.07234 0.06477 -0.0675 0.9791 0.0561
-10.250 -0.6883 0.06928 0.06145 -0.0657 0.9731 0.0561
-10.000 -0.7045 0.06683 0.05877 -0.0624 0.9668 0.0561
-9.750 -0.7133 0.06394 0.05557 -0.0600 0.9618 0.0561
-9.500 -0.7194 0.06128 0.05260 -0.0573 0.9572 0.0561
-9.250 -0.7249 0.05888 0.04989 -0.0540 0.9522 0.0562
-9.000 -0.7226 0.05626 0.04688 -0.0518 0.9483 0.0566
-8.750 -0.7156 0.05385 0.04408 -0.0500 0.9450 0.0573
-8.500 -0.7160 0.05213 0.04204 -0.0463 0.9408 0.0582
-8.250 -0.7104 0.05027 0.03975 -0.0435 0.9376 0.0596
-8.000 -0.6987 0.04843 0.03745 -0.0415 0.9349 0.0608
-7.750 -0.6778 0.04633 0.03506 -0.0411 0.9331 0.0620
-7.500 -0.6500 0.04443 0.03298 -0.0417 0.9315 0.0633
-7.250 -0.6292 0.04306 0.03146 -0.0408 0.9292 0.0651
-7.000 -0.6089 0.04195 0.03018 -0.0398 0.9267 0.0679
-6.750 -0.5807 0.04088 0.02885 -0.0398 0.9248 0.0713
-6.500 -0.5387 0.03967 0.02757 -0.0420 0.9240 0.0746
-6.250 -0.5022 0.03883 0.02667 -0.0434 0.9230 0.0791
-6.000 -0.4757 0.03824 0.02589 -0.0432 0.9214 0.0852
-5.750 -0.4562 0.03750 0.02519 -0.0422 0.9197 0.0903
-5.500 -0.4384 0.03686 0.02446 -0.0409 0.9177 0.0966
-5.250 -0.4241 0.03618 0.02377 -0.0392 0.9155 0.1054
-5.000 -0.4258 0.03573 0.02329 -0.0345 0.9119 0.1146
-4.500 -0.4240 0.03405 0.02210 -0.0266 0.9066 0.1668
-4.250 -0.3920 0.03365 0.02471 -0.0232 0.9063 0.6163
-4.000 -0.4048 0.03350 0.02441 -0.0165 0.9026 0.6801
-3.750 -0.3978 0.03479 0.02555 -0.0108 0.9002 0.7447
-3.500 -0.2614 0.04074 0.03099 -0.0206 0.9030 0.8382
-3.250 -0.2350 0.04086 0.03087 -0.0208 0.9014 0.8507
-3.000 -0.1972 0.04096 0.03070 -0.0233 0.9002 0.8600
-2.750 -0.1844 0.04095 0.03056 -0.0212 0.8971 0.8697
-2.500 -0.1703 0.04094 0.03041 -0.0195 0.8941 0.8795
-2.250 -0.1432 0.04092 0.03022 -0.0203 0.8919 0.8864
-2.000 -0.1196 0.04091 0.03007 -0.0205 0.8894 0.8939
-1.750 -0.0957 0.04091 0.02994 -0.0208 0.8869 0.9005
-1.500 -0.0615 0.04093 0.02982 -0.0231 0.8850 0.9055
-1.250 -0.0567 0.04096 0.02978 -0.0198 0.8814 0.9133
-1.000 -0.0339 0.04095 0.02969 -0.0201 0.8780 0.9179
-0.750 -0.0109 0.04098 0.02965 -0.0203 0.8748 0.9229
-0.500 0.0069 0.04106 0.02965 -0.0195 0.8716 0.9284
-0.250 0.0385 0.04116 0.02969 -0.0213 0.8690 0.9320
0.000 0.0587 0.04124 0.02973 -0.0212 0.8652 0.9364
0.250 0.0713 0.04133 0.02980 -0.0195 0.8605 0.9418
0.500 0.0914 0.04145 0.02990 -0.0192 0.8565 0.9457
0.750 0.1229 0.04160 0.03004 -0.0210 0.8533 0.9482
1.000 0.1431 0.04176 0.03020 -0.0209 0.8488 0.9518
1.250 0.1555 0.04191 0.03036 -0.0192 0.8431 0.9562
1.500 0.1779 0.04210 0.03056 -0.0193 0.8387 0.9593
1.750 0.2138 0.04234 0.03084 -0.0218 0.8353 0.9614
2.000 0.2245 0.04253 0.03108 -0.0201 0.8281 0.9657
2.250 0.2487 0.04276 0.03136 -0.0206 0.8227 0.9690
2.500 0.2797 0.04305 0.03170 -0.0220 0.8187 0.9717
2.750 0.2938 0.04328 0.03202 -0.0210 0.8103 0.9755
3.000 0.3244 0.04354 0.03238 -0.0226 0.8048 0.9785
3.250 0.3467 0.04384 0.03278 -0.0227 0.7981 0.9821
3.500 0.3690 0.04411 0.03316 -0.0229 0.7904 0.9852
3.750 0.4076 0.04433 0.03352 -0.0254 0.7856 0.9872
4.000 0.4207 0.04465 0.03397 -0.0243 0.7749 0.9918
4.250 0.4600 0.04482 0.03433 -0.0269 0.7695 0.9943
4.750 0.4997 0.04527 0.03508 -0.0261 0.7500 1.0000
5.000 0.5123 0.04531 0.03525 -0.0239 0.7397 1.0000
5.250 0.5166 0.04539 0.03546 -0.0205 0.7278 1.0000
5.500 0.5402 0.04520 0.03546 -0.0197 0.7189 1.0000
5.750 0.5510 0.04506 0.03546 -0.0170 0.7069 1.0000
6.000 0.5544 0.04494 0.03548 -0.0133 0.6933 1.0000
6.250 0.5607 0.04471 0.03540 -0.0098 0.6796 1.0000
6.500 0.5694 0.04423 0.03509 -0.0065 0.6648 1.0000
6.750 0.5791 0.04351 0.03453 -0.0029 0.6483 1.0000
7.000 0.5888 0.04177 0.03294 0.0017 0.6218 1.0000
7.250 0.5976 0.03900 0.03024 0.0078 0.5786 1.0000
7.500 0.6022 0.03665 0.02786 0.0142 0.5123 1.0000
7.750 0.6483 0.03330 0.02326 0.0177 0.3069 1.0000
8.000 0.6348 0.03475 0.02394 0.0227 0.2130 1.0000
8.250 0.6261 0.03654 0.02510 0.0265 0.1448 1.0000
8.500 0.6247 0.03827 0.02641 0.0292 0.1095 1.0000
8.750 0.6288 0.03981 0.02776 0.0313 0.0934 1.0000
9.000 0.6372 0.04114 0.02907 0.0329 0.0832 1.0000
9.250 0.6472 0.04246 0.03037 0.0344 0.0767 1.0000
9.500 0.6601 0.04367 0.03163 0.0356 0.0718 1.0000
9.750 0.6749 0.04491 0.03281 0.0368 0.0681 1.0000
10.000 0.6984 0.04577 0.03387 0.0375 0.0650 1.0000
10.250 0.7303 0.04652 0.03475 0.0378 0.0619 1.0000
10.500 0.7715 0.04730 0.03557 0.0372 0.0595 1.0000
10.750 0.8214 0.04867 0.03712 0.0358 0.0575 1.0000
11.000 0.8542 0.05056 0.03934 0.0353 0.0555 1.0000
11.250 0.8773 0.05266 0.04169 0.0354 0.0536 1.0000
11.500 0.8970 0.05487 0.04414 0.0357 0.0523 1.0000
11.750 0.9129 0.05741 0.04691 0.0363 0.0515 1.0000
12.000 0.9241 0.06011 0.04985 0.0371 0.0510 1.0000
12.250 0.9331 0.06292 0.05284 0.0379 0.0503 1.0000
12.500 0.9283 0.06592 0.05612 0.0397 0.0498 1.0000
12.750 0.9192 0.06908 0.05959 0.0414 0.0497 1.0000
13.000 0.9046 0.07251 0.06333 0.0431 0.0494 1.0000
13.250 0.8885 0.07631 0.06741 0.0442 0.0492 1.0000
13.500 0.8720 0.08034 0.07168 0.0448 0.0492 1.0000
13.750 0.8512 0.08497 0.07654 0.0448 0.0492 1.0000
14.000 0.8301 0.08998 0.08176 0.0440 0.0493 1.0000
14.250 0.8057 0.09580 0.08776 0.0424 0.0494 1.0000
14.500 0.7844 0.10193 0.09404 0.0399 0.0497 1.0000
14.750 0.7611 0.10910 0.10133 0.0363 0.0499 1.0000
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