FX 60-157 AIRFOIL (fx60157-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 60-157 AIRFOIL (fx60157-il) Reynolds number: 200,000 Max Cl/Cd: 56.52 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx60157-il-200000.txt Download as CSV file: xf-fx60157-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: FX 60-157 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5369 0.09275 0.08962 -0.0468 1.0000 0.0581
-10.000 -0.5774 0.08494 0.08180 -0.0505 1.0000 0.0576
-9.750 -0.6136 0.07927 0.07606 -0.0524 0.9991 0.0574
-9.500 -0.6354 0.07393 0.07058 -0.0564 0.9947 0.0578
-9.250 -0.7406 0.05625 0.05169 -0.0563 0.9832 0.0334
-9.000 -0.7688 0.04617 0.04042 -0.0528 0.9763 0.0269
-8.750 -0.7559 0.04254 0.03642 -0.0527 0.9730 0.0268
-8.500 -0.7357 0.03922 0.03267 -0.0534 0.9706 0.0268
-8.250 -0.7190 0.03664 0.02963 -0.0526 0.9667 0.0270
-8.000 -0.6999 0.03432 0.02714 -0.0520 0.9629 0.0276
-7.750 -0.6742 0.03317 0.02598 -0.0526 0.9599 0.0289
-7.500 -0.6440 0.03213 0.02465 -0.0538 0.9574 0.0316
-7.250 -0.6105 0.03071 0.02313 -0.0555 0.9555 0.0340
-7.000 -0.5958 0.02967 0.02202 -0.0535 0.9494 0.0364
-6.750 -0.5702 0.02831 0.02056 -0.0533 0.9461 0.0402
-6.500 -0.5396 0.02759 0.01977 -0.0543 0.9434 0.0445
-6.250 -0.5068 0.02675 0.01896 -0.0558 0.9414 0.0489
-6.000 -0.4868 0.02656 0.01866 -0.0550 0.9361 0.0537
-5.750 -0.4645 0.02578 0.01799 -0.0547 0.9319 0.0578
-5.500 -0.4337 0.02544 0.01756 -0.0558 0.9290 0.0626
-5.250 -0.4010 0.02452 0.01671 -0.0574 0.9268 0.0670
-5.000 -0.3626 0.02393 0.01611 -0.0600 0.9250 0.0730
-4.750 -0.3502 0.02313 0.01537 -0.0581 0.9169 0.0798
-4.500 -0.3144 0.02228 0.01461 -0.0605 0.9136 0.1016
-4.250 -0.2684 0.01943 0.01335 -0.0677 0.9125 0.3911
-4.000 -0.2312 0.01899 0.01384 -0.0696 0.9107 0.5835
-3.750 -0.2107 0.01936 0.01424 -0.0680 0.9043 0.6249
-3.500 -0.1833 0.01979 0.01463 -0.0674 0.8990 0.6521
-3.250 -0.1465 0.02026 0.01500 -0.0685 0.8959 0.6753
-3.000 -0.1100 0.02081 0.01550 -0.0690 0.8936 0.6882
-2.750 -0.1001 0.02122 0.01587 -0.0654 0.8839 0.6977
-2.500 -0.0671 0.02164 0.01622 -0.0657 0.8805 0.7111
-2.250 -0.0390 0.02233 0.01694 -0.0637 0.8779 0.7205
-2.000 -0.0318 0.02287 0.01747 -0.0593 0.8680 0.7307
-1.750 0.0008 0.02317 0.01772 -0.0593 0.8645 0.7434
-1.500 0.0284 0.02346 0.01801 -0.0572 0.8621 0.7491
-1.250 0.0455 0.02362 0.01811 -0.0559 0.8523 0.7594
-1.000 0.0706 0.02364 0.01813 -0.0539 0.8487 0.7637
-0.750 0.1090 0.02338 0.01782 -0.0552 0.8467 0.7688
-0.500 0.1324 0.02332 0.01771 -0.0554 0.8374 0.7761
-0.250 0.1622 0.02304 0.01741 -0.0549 0.8337 0.7790
0.000 0.2002 0.02261 0.01696 -0.0563 0.8316 0.7822
0.250 0.2350 0.02223 0.01654 -0.0576 0.8272 0.7861
0.500 0.2719 0.02182 0.01609 -0.0600 0.8197 0.7916
0.750 0.3089 0.02109 0.01535 -0.0607 0.8171 0.7940
1.000 0.3493 0.02039 0.01465 -0.0621 0.8154 0.7971
1.250 0.3940 0.01979 0.01404 -0.0647 0.8141 0.8011
1.500 0.4144 0.01968 0.01394 -0.0640 0.8030 0.8068
1.750 0.4596 0.01897 0.01322 -0.0669 0.8005 0.8091
2.000 0.5092 0.01822 0.01249 -0.0703 0.7981 0.8109
2.250 0.5237 0.01793 0.01222 -0.0674 0.7861 0.8142
2.500 0.5778 0.01727 0.01155 -0.0722 0.7822 0.8163
2.750 0.5994 0.01700 0.01130 -0.0712 0.7697 0.8197
3.000 0.6389 0.01665 0.01096 -0.0738 0.7598 0.8230
3.250 0.6776 0.01622 0.01053 -0.0755 0.7499 0.8255
3.500 0.6961 0.01596 0.01028 -0.0732 0.7350 0.8287
3.750 0.7235 0.01570 0.01001 -0.0729 0.7183 0.8324
4.000 0.7527 0.01553 0.00981 -0.0732 0.6994 0.8361
4.250 0.7819 0.01544 0.00968 -0.0738 0.6774 0.8389
4.500 0.8096 0.01534 0.00950 -0.0739 0.6543 0.8408
4.750 0.8277 0.01530 0.00940 -0.0719 0.6288 0.8428
5.000 0.8496 0.01537 0.00935 -0.0708 0.6018 0.8449
5.250 0.8669 0.01552 0.00940 -0.0690 0.5732 0.8477
5.500 0.8865 0.01575 0.00952 -0.0677 0.5455 0.8507
5.750 0.9077 0.01606 0.00971 -0.0670 0.5178 0.8533
6.000 0.9270 0.01648 0.00997 -0.0661 0.4867 0.8557
6.250 0.9397 0.01678 0.01020 -0.0635 0.4595 0.8578
6.500 0.9522 0.01718 0.01049 -0.0611 0.4308 0.8602
6.750 0.9660 0.01765 0.01085 -0.0591 0.4047 0.8627
7.000 0.9818 0.01812 0.01125 -0.0576 0.3781 0.8656
7.250 0.9982 0.01870 0.01170 -0.0563 0.3539 0.8686
7.500 1.0184 0.01927 0.01221 -0.0559 0.3317 0.8711
7.750 1.0322 0.01972 0.01265 -0.0540 0.3116 0.8733
8.000 1.0468 0.02024 0.01312 -0.0523 0.2944 0.8760
8.250 1.0625 0.02079 0.01366 -0.0509 0.2784 0.8790
8.500 1.0802 0.02138 0.01424 -0.0500 0.2623 0.8819
8.750 1.0984 0.02203 0.01487 -0.0493 0.2464 0.8845
9.000 1.1169 0.02272 0.01555 -0.0488 0.2325 0.8869
9.250 1.1295 0.02333 0.01616 -0.0469 0.2210 0.8898
9.500 1.1436 0.02399 0.01685 -0.0454 0.2088 0.8930
9.750 1.1607 0.02463 0.01755 -0.0445 0.1968 0.8960
10.000 1.1774 0.02541 0.01835 -0.0438 0.1859 0.8988
10.250 1.1932 0.02635 0.01928 -0.0431 0.1759 0.9016
10.500 1.2064 0.02709 0.02010 -0.0417 0.1650 0.9044
10.750 1.2200 0.02786 0.02093 -0.0404 0.1533 0.9077
11.000 1.2326 0.02880 0.02190 -0.0393 0.1414 0.9112
11.250 1.2444 0.02993 0.02302 -0.0383 0.1309 0.9151
11.500 1.2545 0.03107 0.02419 -0.0369 0.1197 0.9190
11.750 1.2646 0.03211 0.02531 -0.0355 0.1061 0.9234
12.000 1.2702 0.03369 0.02683 -0.0340 0.0929 0.9277
12.250 1.2759 0.03545 0.02861 -0.0327 0.0783 0.9320
12.500 1.2770 0.03724 0.03038 -0.0307 0.0644 0.9373
12.750 1.2748 0.03959 0.03270 -0.0290 0.0574 0.9431
13.000 1.2728 0.04181 0.03500 -0.0272 0.0527 0.9503
13.250 1.2658 0.04459 0.03783 -0.0255 0.0498 0.9603
13.500 1.2678 0.04653 0.03994 -0.0245 0.0475 0.9985
13.750 1.2749 0.04917 0.04271 -0.0250 0.0453 1.0000
14.000 1.2802 0.05199 0.04562 -0.0255 0.0437 1.0000
14.250 1.2834 0.05508 0.04877 -0.0261 0.0425 1.0000
14.500 1.2866 0.05823 0.05198 -0.0266 0.0415 1.0000
14.750 1.2941 0.06102 0.05491 -0.0274 0.0405 1.0000
15.000 1.3008 0.06392 0.05793 -0.0283 0.0395 1.0000
15.250 1.3071 0.06689 0.06102 -0.0292 0.0386 1.0000
15.500 1.3124 0.07002 0.06424 -0.0303 0.0376 1.0000
15.750 1.3170 0.07327 0.06756 -0.0316 0.0366 1.0000
16.000 1.3216 0.07645 0.07077 -0.0326 0.0357 1.0000
16.250 1.3280 0.07939 0.07376 -0.0333 0.0349 1.0000
16.500 1.3320 0.08285 0.07739 -0.0346 0.0344 1.0000
16.750 1.3357 0.08635 0.08105 -0.0360 0.0339 1.0000
17.000 1.3388 0.08993 0.08478 -0.0374 0.0334 1.0000
17.250 1.3410 0.09368 0.08869 -0.0389 0.0330 1.0000
17.500 1.3420 0.09764 0.09281 -0.0407 0.0326 1.0000
17.750 1.3420 0.10178 0.09710 -0.0426 0.0322 1.0000
18.000 1.3414 0.10603 0.10148 -0.0447 0.0317 1.0000
18.250 1.3407 0.11030 0.10588 -0.0470 0.0313 1.0000
18.500 1.3406 0.11444 0.11011 -0.0493 0.0307 1.0000
18.750 1.3447 0.11771 0.11339 -0.0510 0.0299 1.0000
19.000 1.3407 0.12249 0.11829 -0.0535 0.0292 1.0000
19.250 1.3299 0.12883 0.12486 -0.0576 0.0291 1.0000
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