FX 60-157 AIRFOIL (fx60157-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: FX 60-157 AIRFOIL (fx60157-il) Reynolds number: 100,000 Max Cl/Cd: 41.87 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx60157-il-100000-n5.txt Download as CSV file: xf-fx60157-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.5420 0.09204 0.08692 -0.0616 1.0000 0.0226
-12.000 -0.5675 0.08552 0.08036 -0.0641 1.0000 0.0224
-11.750 -0.5907 0.08045 0.07524 -0.0653 1.0000 0.0222
-11.500 -0.6153 0.07591 0.07064 -0.0657 1.0000 0.0220
-11.250 -0.6413 0.07188 0.06652 -0.0652 1.0000 0.0218
-11.000 -0.6694 0.06814 0.06267 -0.0638 1.0000 0.0217
-10.750 -0.6889 0.06352 0.05782 -0.0651 0.9969 0.0217
-10.500 -0.7069 0.05907 0.05304 -0.0663 0.9918 0.0219
-10.250 -0.7258 0.05551 0.04913 -0.0655 0.9859 0.0222
-10.000 -0.7351 0.05199 0.04521 -0.0650 0.9806 0.0224
-9.750 -0.7375 0.04870 0.04150 -0.0639 0.9748 0.0228
-9.500 -0.7247 0.04665 0.03930 -0.0641 0.9714 0.0233
-9.250 -0.7120 0.04449 0.03690 -0.0638 0.9678 0.0239
-9.000 -0.7015 0.04246 0.03464 -0.0626 0.9630 0.0246
-8.750 -0.6847 0.04018 0.03202 -0.0623 0.9595 0.0257
-8.500 -0.6627 0.03781 0.02924 -0.0623 0.9570 0.0273
-8.250 -0.6407 0.03661 0.02798 -0.0625 0.9541 0.0285
-8.000 -0.6262 0.03551 0.02672 -0.0609 0.9495 0.0306
-7.750 -0.6055 0.03441 0.02547 -0.0606 0.9460 0.0337
-7.500 -0.5802 0.03339 0.02426 -0.0609 0.9432 0.0371
-7.250 -0.5530 0.03248 0.02331 -0.0618 0.9410 0.0412
-7.000 -0.5374 0.03189 0.02253 -0.0603 0.9363 0.0458
-6.750 -0.5184 0.03105 0.02178 -0.0595 0.9324 0.0489
-6.500 -0.4938 0.03019 0.02085 -0.0594 0.9293 0.0515
-6.250 -0.4668 0.02935 0.01994 -0.0597 0.9268 0.0545
-6.000 -0.4416 0.02860 0.01920 -0.0600 0.9239 0.0587
-5.750 -0.4277 0.02801 0.01853 -0.0580 0.9180 0.0624
-5.500 -0.4035 0.02718 0.01767 -0.0582 0.9140 0.0671
-5.250 -0.3744 0.02646 0.01689 -0.0592 0.9112 0.0749
-5.000 -0.3436 0.02571 0.01620 -0.0606 0.9090 0.0871
-4.750 -0.3309 0.02520 0.01575 -0.0586 0.9023 0.1044
-4.500 -0.3056 0.02423 0.01517 -0.0593 0.8986 0.1634
-4.250 -0.2772 0.02254 0.01453 -0.0617 0.8961 0.3625
-4.000 -0.2520 0.02217 0.01508 -0.0609 0.8938 0.5200
-3.750 -0.2421 0.02275 0.01588 -0.0564 0.8865 0.5833
-3.500 -0.2131 0.02314 0.01618 -0.0562 0.8820 0.6278
-3.250 -0.1815 0.02364 0.01656 -0.0561 0.8788 0.6530
-3.000 -0.1600 0.02415 0.01695 -0.0546 0.8727 0.6775
-2.750 -0.1411 0.02490 0.01767 -0.0517 0.8670 0.6955
-2.500 -0.1135 0.02544 0.01811 -0.0506 0.8635 0.7113
-2.250 -0.0966 0.02582 0.01844 -0.0477 0.8570 0.7187
-2.000 -0.0673 0.02571 0.01819 -0.0485 0.8512 0.7276
-1.750 -0.0367 0.02568 0.01807 -0.0485 0.8475 0.7317
-1.500 -0.0128 0.02569 0.01799 -0.0479 0.8417 0.7376
-1.250 0.0149 0.02559 0.01779 -0.0486 0.8356 0.7440
-1.000 0.0451 0.02550 0.01762 -0.0486 0.8320 0.7475
-0.750 0.0711 0.02543 0.01750 -0.0484 0.8262 0.7523
-0.500 0.1006 0.02527 0.01725 -0.0494 0.8191 0.7585
-0.250 0.1334 0.02501 0.01694 -0.0499 0.8154 0.7618
0.000 0.1516 0.02508 0.01700 -0.0482 0.8070 0.7660
0.250 0.1822 0.02491 0.01679 -0.0488 0.8019 0.7712
0.500 0.2220 0.02451 0.01632 -0.0512 0.7989 0.7760
0.750 0.2380 0.02456 0.01638 -0.0490 0.7886 0.7792
1.000 0.2712 0.02416 0.01597 -0.0497 0.7842 0.7826
1.500 0.3315 0.02367 0.01545 -0.0509 0.7695 0.7905
1.750 0.3703 0.02309 0.01486 -0.0525 0.7657 0.7932
2.000 0.3871 0.02308 0.01488 -0.0505 0.7535 0.7963
2.250 0.4160 0.02276 0.01457 -0.0505 0.7450 0.7996
2.500 0.4473 0.02243 0.01427 -0.0511 0.7363 0.8031
2.750 0.4772 0.02225 0.01410 -0.0518 0.7258 0.8065
3.000 0.5152 0.02174 0.01359 -0.0534 0.7180 0.8086
3.250 0.5381 0.02161 0.01351 -0.0525 0.7043 0.8107
3.500 0.5654 0.02138 0.01332 -0.0523 0.6909 0.8130
3.750 0.5964 0.02109 0.01304 -0.0527 0.6771 0.8156
4.000 0.6295 0.02080 0.01277 -0.0535 0.6618 0.8183
4.250 0.6628 0.02060 0.01256 -0.0546 0.6451 0.8208
4.500 0.6972 0.02042 0.01237 -0.0559 0.6265 0.8231
4.750 0.7301 0.02024 0.01217 -0.0567 0.6069 0.8249
5.000 0.7605 0.02014 0.01202 -0.0570 0.5862 0.8268
5.250 0.7844 0.02024 0.01209 -0.0564 0.5622 0.8294
5.500 0.8121 0.02033 0.01210 -0.0564 0.5376 0.8320
5.750 0.8362 0.02057 0.01229 -0.0560 0.5131 0.8348
6.000 0.8616 0.02086 0.01251 -0.0560 0.4889 0.8374
6.250 0.8855 0.02122 0.01281 -0.0558 0.4652 0.8401
6.500 0.9026 0.02157 0.01313 -0.0541 0.4423 0.8426
6.750 0.9204 0.02198 0.01348 -0.0527 0.4198 0.8454
7.000 0.9388 0.02245 0.01392 -0.0515 0.3974 0.8483
7.250 0.9579 0.02296 0.01441 -0.0507 0.3757 0.8510
7.500 0.9775 0.02354 0.01493 -0.0500 0.3561 0.8540
7.750 0.9947 0.02412 0.01547 -0.0488 0.3380 0.8569
8.000 1.0100 0.02468 0.01605 -0.0472 0.3202 0.8597
8.250 1.0259 0.02530 0.01668 -0.0459 0.3027 0.8626
8.500 1.0420 0.02600 0.01736 -0.0448 0.2859 0.8655
8.750 1.0581 0.02675 0.01812 -0.0438 0.2684 0.8684
9.000 1.0742 0.02756 0.01893 -0.0429 0.2505 0.8713
9.250 1.0855 0.02833 0.01970 -0.0411 0.2352 0.8744
9.500 1.0976 0.02918 0.02054 -0.0395 0.2217 0.8779
9.750 1.1111 0.03006 0.02146 -0.0383 0.2080 0.8816
10.000 1.1258 0.03097 0.02245 -0.0374 0.1942 0.8852
10.250 1.1382 0.03192 0.02344 -0.0361 0.1824 0.8885
10.500 1.1493 0.03290 0.02448 -0.0347 0.1719 0.8921
10.750 1.1598 0.03401 0.02563 -0.0334 0.1612 0.8959
11.000 1.1733 0.03506 0.02682 -0.0325 0.1497 0.8999
11.250 1.1834 0.03621 0.02806 -0.0313 0.1404 0.9042
11.500 1.1897 0.03753 0.02941 -0.0297 0.1323 0.9093
11.750 1.1996 0.03881 0.03081 -0.0285 0.1231 0.9149
12.000 1.2062 0.04018 0.03229 -0.0271 0.1154 0.9211
12.250 1.2127 0.04162 0.03388 -0.0258 0.1061 0.9282
12.500 1.2168 0.04328 0.03561 -0.0245 0.0975 0.9367
12.750 1.2186 0.04519 0.03758 -0.0233 0.0902 0.9484
13.000 1.2192 0.04704 0.03956 -0.0221 0.0829 0.9811
13.250 1.2261 0.04939 0.04206 -0.0224 0.0749 1.0000
13.500 1.2301 0.05211 0.04488 -0.0226 0.0673 1.0000
13.750 1.2314 0.05518 0.04802 -0.0230 0.0621 1.0000
14.000 1.2293 0.05873 0.05163 -0.0236 0.0581 1.0000
14.250 1.2288 0.06226 0.05531 -0.0243 0.0544 1.0000
14.500 1.2249 0.06628 0.05945 -0.0253 0.0516 1.0000
14.750 1.2183 0.07080 0.06403 -0.0266 0.0496 1.0000
15.000 1.2173 0.07477 0.06822 -0.0279 0.0471 1.0000
15.250 1.2140 0.07914 0.07276 -0.0294 0.0451 1.0000
15.500 1.2093 0.08382 0.07759 -0.0313 0.0435 1.0000
15.750 1.2036 0.08874 0.08264 -0.0334 0.0423 1.0000
16.000 1.1988 0.09365 0.08766 -0.0356 0.0413 1.0000
16.250 1.1957 0.09834 0.09252 -0.0378 0.0402 1.0000
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