NACA 66-018 (naca66-018-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: NACA 66-018 (naca66-018-il) Reynolds number: 200,000 Max Cl/Cd: 30.99 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca66-018-il-200000.txt Download as CSV file: xf-naca66-018-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.3440 0.11372 0.11030 -0.0700 0.9633 0.0929
-14.000 -0.7117 0.05922 0.05464 -0.0859 0.9781 0.0462
-13.750 -0.7205 0.05399 0.04923 -0.0864 0.9747 0.0452
-13.500 -0.8495 0.06165 0.05655 -0.0762 0.9834 0.0485
-13.250 -0.8583 0.06464 0.05938 -0.0763 0.9744 0.0549
-13.000 -0.8971 0.05026 0.04379 -0.0729 0.9692 0.0406
-12.750 -0.8928 0.04845 0.04165 -0.0721 0.9619 0.0403
-12.500 -0.8803 0.04554 0.03846 -0.0720 0.9563 0.0403
-12.250 -0.8555 0.04175 0.03442 -0.0731 0.9522 0.0408
-12.000 -0.8276 0.03918 0.03164 -0.0742 0.9483 0.0411
-11.750 -0.7970 0.03702 0.02927 -0.0753 0.9449 0.0414
-11.500 -0.7657 0.03530 0.02743 -0.0763 0.9408 0.0420
-11.250 -0.7326 0.03388 0.02587 -0.0774 0.9371 0.0424
-11.000 -0.7009 0.03278 0.02468 -0.0782 0.9337 0.0436
-10.750 -0.6712 0.03183 0.02363 -0.0787 0.9301 0.0449
-10.500 -0.6441 0.03103 0.02270 -0.0788 0.9260 0.0462
-10.250 -0.6127 0.03022 0.02183 -0.0793 0.9226 0.0479
-10.000 -0.5834 0.02950 0.02120 -0.0796 0.9195 0.0499
-9.750 -0.5616 0.02890 0.02058 -0.0790 0.9159 0.0520
-9.500 -0.5418 0.02830 0.01993 -0.0783 0.9119 0.0543
-9.250 -0.5253 0.02752 0.01919 -0.0772 0.9083 0.0566
-9.000 -0.5120 0.02682 0.01852 -0.0758 0.9049 0.0600
-8.750 -0.4977 0.02629 0.01790 -0.0743 0.9020 0.0640
-8.500 -0.4892 0.02533 0.01702 -0.0726 0.8984 0.0685
-8.000 -0.4702 0.02379 0.01550 -0.0689 0.8915 0.0860
-7.750 -0.4696 0.02266 0.01460 -0.0657 0.8883 0.1139
-7.500 -0.4850 0.02103 0.01362 -0.0605 0.8850 0.2109
-7.250 -0.5040 0.01954 0.01273 -0.0549 0.8802 0.3104
-7.000 -0.5243 0.01839 0.01204 -0.0483 0.8754 0.3926
-6.750 -0.5430 0.01752 0.01166 -0.0410 0.8717 0.4767
-6.500 -0.4796 0.02003 0.01496 -0.0435 0.8719 0.6272
-6.250 -0.5093 0.01911 0.01396 -0.0349 0.8683 0.6492
-6.000 -0.5291 0.01960 0.01445 -0.0272 0.8638 0.6641
-5.750 -0.5285 0.02052 0.01532 -0.0221 0.8607 0.6784
-5.500 -0.4712 0.02236 0.01708 -0.0258 0.8603 0.6912
-5.250 -0.3123 0.02786 0.02238 -0.0418 0.8653 0.6997
-5.000 -0.2536 0.02929 0.02370 -0.0458 0.8652 0.7013
-4.750 -0.2521 0.02954 0.02392 -0.0422 0.8620 0.7135
-4.500 -0.2071 0.03028 0.02458 -0.0446 0.8610 0.7160
-4.250 -0.1598 0.03099 0.02521 -0.0475 0.8602 0.7180
-4.000 -0.1618 0.03119 0.02539 -0.0433 0.8575 0.7302
-3.750 -0.1204 0.03161 0.02575 -0.0455 0.8569 0.7327
-3.500 -0.0764 0.03204 0.02612 -0.0482 0.8563 0.7348
-3.250 -0.0401 0.03238 0.02642 -0.0498 0.8555 0.7384
-3.000 -0.0407 0.03244 0.02646 -0.0457 0.8535 0.7495
-2.750 0.0013 0.03261 0.02659 -0.0481 0.8528 0.7515
-2.500 0.0370 0.03278 0.02673 -0.0497 0.8520 0.7547
-2.250 0.0131 0.03351 0.02749 -0.0421 0.8485 0.7665
-2.000 0.0426 0.03403 0.02801 -0.0429 0.8463 0.7689
-1.750 0.0607 0.03459 0.02858 -0.0417 0.8437 0.7730
-1.500 0.0233 0.03507 0.02907 -0.0311 0.8389 0.7841
-1.250 0.0693 0.03508 0.02907 -0.0346 0.8380 0.7859
-1.000 -0.0647 0.03644 0.03048 -0.0063 0.8282 0.8009
-0.750 -0.0334 0.03673 0.03077 -0.0073 0.8255 0.8028
-0.500 -0.1307 0.03609 0.03011 0.0147 0.8188 0.8170
-0.250 -0.0519 0.03642 0.03043 0.0050 0.8185 0.8161
0.000 -0.0042 0.03624 0.03024 0.0008 0.8175 0.8179
0.250 0.0443 0.03642 0.03044 -0.0036 0.8155 0.8189
0.500 0.1254 0.03612 0.03014 -0.0138 0.8166 0.8192
0.750 0.0307 0.03673 0.03077 0.0078 0.8025 0.8257
1.000 0.0642 0.03648 0.03052 0.0064 0.8007 0.8282
1.250 -0.0725 0.03502 0.02900 0.0352 0.7856 0.8382
1.500 -0.0291 0.03499 0.02899 0.0321 0.7837 0.8392
1.750 0.0191 0.03497 0.02898 0.0281 0.7824 0.8399
2.000 -0.0415 0.03409 0.02808 0.0427 0.7687 0.8461
2.250 -0.0117 0.03364 0.02762 0.0420 0.7663 0.8482
2.500 0.0189 0.03318 0.02717 0.0410 0.7638 0.8498
2.750 -0.0035 0.03256 0.02653 0.0484 0.7512 0.8530
3.000 0.0387 0.03238 0.02639 0.0459 0.7491 0.8537
3.250 0.0778 0.03220 0.02626 0.0439 0.7464 0.8544
3.500 0.0751 0.03200 0.02608 0.0484 0.7346 0.8564
3.750 0.1184 0.03159 0.02572 0.0458 0.7324 0.8570
4.000 0.1650 0.03112 0.02532 0.0427 0.7309 0.8575
4.250 0.1587 0.03099 0.02521 0.0477 0.7177 0.8602
4.500 0.2056 0.03029 0.02459 0.0448 0.7157 0.8609
4.750 0.2569 0.02946 0.02385 0.0414 0.7144 0.8615
5.000 0.2528 0.02933 0.02374 0.0459 0.7011 0.8652
5.250 0.3100 0.02795 0.02248 0.0421 0.6994 0.8654
5.500 0.4779 0.02218 0.01691 0.0248 0.6910 0.8599
5.750 0.5315 0.02046 0.01526 0.0217 0.6783 0.8604
6.000 0.5296 0.01960 0.01445 0.0272 0.6636 0.8638
6.250 0.5094 0.01912 0.01398 0.0349 0.6489 0.8683
6.500 0.4789 0.02003 0.01496 0.0435 0.6264 0.8720
6.750 0.5427 0.01751 0.01164 0.0410 0.4756 0.8718
7.000 0.5246 0.01837 0.01202 0.0482 0.3928 0.8754
7.250 0.5037 0.01956 0.01273 0.0549 0.3091 0.8800
7.500 0.4847 0.02104 0.01363 0.0605 0.2096 0.8851
7.750 0.4697 0.02267 0.01460 0.0657 0.1129 0.8884
8.000 0.4702 0.02380 0.01551 0.0689 0.0852 0.8915
8.250 0.4779 0.02464 0.01630 0.0710 0.0746 0.8949
8.500 0.4896 0.02533 0.01701 0.0726 0.0683 0.8984
8.750 0.4978 0.02630 0.01791 0.0743 0.0639 0.9020
9.000 0.5123 0.02684 0.01853 0.0757 0.0602 0.9050
9.250 0.5263 0.02750 0.01918 0.0771 0.0570 0.9083
9.500 0.5424 0.02830 0.01993 0.0782 0.0541 0.9120
9.750 0.5626 0.02889 0.02058 0.0789 0.0520 0.9158
10.000 0.5847 0.02951 0.02120 0.0794 0.0498 0.9194
10.250 0.6114 0.03016 0.02181 0.0794 0.0481 0.9228
10.500 0.6453 0.03105 0.02272 0.0786 0.0461 0.9259
10.750 0.6715 0.03182 0.02362 0.0787 0.0448 0.9302
11.000 0.7002 0.03274 0.02464 0.0783 0.0434 0.9339
11.250 0.7333 0.03392 0.02594 0.0773 0.0427 0.9371
11.500 0.7658 0.03529 0.02742 0.0763 0.0418 0.9409
11.750 0.7964 0.03697 0.02924 0.0754 0.0413 0.9452
12.000 0.8260 0.03907 0.03155 0.0744 0.0411 0.9487
12.250 0.8521 0.04156 0.03427 0.0735 0.0408 0.9529
12.500 0.8646 0.04384 0.03688 0.0743 0.0411 0.9596
12.750 0.8574 0.04748 0.04117 0.0761 0.0421 0.9664
13.000 0.8551 0.05129 0.04542 0.0766 0.0426 0.9729
13.250 0.8468 0.05643 0.05103 0.0766 0.0444 0.9783
13.500 0.8508 0.06124 0.05605 0.0756 0.0460 0.9836
13.750 0.7208 0.05393 0.04917 0.0863 0.0452 0.9747
14.000 0.7138 0.05905 0.05445 0.0858 0.0461 0.9781
14.250 0.3437 0.11350 0.11008 0.0699 0.0929 0.9631
|
Polar data table (+)
Polar graphs
<< Back to NACA 66-018 (naca66-018-il)