FX 60-177 AIRFOIL (fx60177-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 60-177 AIRFOIL (fx60177-il) Reynolds number: 200,000 Max Cl/Cd: 49.25 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx60177-il-200000.txt Download as CSV file: xf-fx60177-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: FX 60-177 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
------ -------- --------- --------- -------- -------- --------
-13.500 -0.4669 0.10926 0.10606 -0.0512 1.0001 0.0249
-13.250 -0.4590 0.10983 0.10670 -0.0491 1.0001 0.0253
-13.000 -0.6353 0.08724 0.08332 -0.0677 1.0001 0.0238
-12.750 -0.6566 0.08273 0.07876 -0.0679 1.0001 0.0236
-12.500 -0.6803 0.07848 0.07443 -0.0677 1.0001 0.0234
-12.250 -0.7046 0.07460 0.07045 -0.0668 1.0001 0.0232
-12.000 -0.7291 0.07105 0.06681 -0.0653 1.0001 0.0229
-11.750 -0.7539 0.06779 0.06343 -0.0633 1.0001 0.0227
-11.500 -0.7791 0.06475 0.06026 -0.0606 1.0001 0.0224
-11.250 -0.8051 0.06188 0.05724 -0.0573 1.0001 0.0221
-11.000 -0.8789 0.05496 0.04941 -0.0517 0.9966 0.0199
-10.750 -0.8812 0.05307 0.04720 -0.0511 0.9918 0.0196
-10.500 -0.8735 0.04969 0.04361 -0.0509 0.9882 0.0195
-10.250 -0.8622 0.04666 0.04031 -0.0511 0.9852 0.0193
-10.000 -0.8487 0.04399 0.03735 -0.0510 0.9818 0.0192
-9.750 -0.8353 0.04167 0.03475 -0.0501 0.9775 0.0192
-9.500 -0.8141 0.03957 0.03236 -0.0502 0.9746 0.0193
-9.250 -0.7882 0.03782 0.03035 -0.0508 0.9725 0.0195
-9.000 -0.7664 0.03624 0.02862 -0.0500 0.9699 0.0198
-8.750 -0.7492 0.03487 0.02726 -0.0484 0.9662 0.0204
-8.500 -0.7261 0.03381 0.02619 -0.0483 0.9629 0.0212
-8.250 -0.6988 0.03281 0.02514 -0.0490 0.9603 0.0224
-8.000 -0.6690 0.03190 0.02410 -0.0500 0.9584 0.0242
-7.750 -0.6656 0.03066 0.02293 -0.0469 0.9515 0.0257
-7.500 -0.6407 0.02966 0.02188 -0.0476 0.9477 0.0300
-7.250 -0.6111 0.02860 0.02083 -0.0496 0.9452 0.0372
-7.000 -0.5976 0.02778 0.02004 -0.0484 0.9397 0.0428
-6.750 -0.5750 0.02690 0.01917 -0.0490 0.9353 0.0504
-6.500 -0.5434 0.02604 0.01834 -0.0511 0.9325 0.0625
-6.250 -0.5075 0.02500 0.01743 -0.0543 0.9305 0.0852
-6.000 -0.4854 0.02376 0.01659 -0.0554 0.9261 0.1411
-5.750 -0.4392 0.02104 0.01522 -0.0639 0.9245 0.3720
-5.500 -0.3981 0.02026 0.01514 -0.0680 0.9221 0.5087
-5.250 -0.3650 0.02046 0.01556 -0.0688 0.9189 0.5726
-5.000 -0.3271 0.02091 0.01600 -0.0703 0.9164 0.6142
-4.750 -0.3073 0.02142 0.01649 -0.0684 0.9101 0.6327
-4.500 -0.2775 0.02181 0.01679 -0.0684 0.9052 0.6472
-4.250 -0.2439 0.02239 0.01729 -0.0687 0.9022 0.6617
-3.750 -0.2083 0.02390 0.01876 -0.0629 0.8903 0.6795
-3.500 -0.1802 0.02462 0.01944 -0.0612 0.8870 0.6856
-3.250 -0.1593 0.02504 0.01979 -0.0597 0.8803 0.6947
-3.000 -0.1409 0.02572 0.02046 -0.0564 0.8747 0.6989
-2.750 -0.1022 0.02583 0.02047 -0.0584 0.8723 0.7092
-2.500 -0.0895 0.02643 0.02107 -0.0546 0.8658 0.7120
-2.250 -0.0680 0.02676 0.02136 -0.0526 0.8603 0.7160
-2.000 -0.0230 0.02637 0.02086 -0.0567 0.8578 0.7250
-1.750 0.0112 0.02633 0.02078 -0.0567 0.8557 0.7270
-1.500 0.0194 0.02670 0.02115 -0.0526 0.8454 0.7308
-1.250 0.0661 0.02623 0.02058 -0.0571 0.8429 0.7402
-1.000 0.0987 0.02605 0.02038 -0.0567 0.8409 0.7421
-0.750 0.1093 0.02628 0.02061 -0.0532 0.8308 0.7452
-0.500 0.1461 0.02588 0.02018 -0.0544 0.8279 0.7491
-0.250 0.1961 0.02516 0.01939 -0.0595 0.8263 0.7564
0.000 0.2069 0.02535 0.01960 -0.0556 0.8173 0.7590
0.250 0.2375 0.02500 0.01924 -0.0551 0.8136 0.7624
0.500 0.2784 0.02432 0.01854 -0.0571 0.8116 0.7671
0.750 0.3334 0.02328 0.01745 -0.0627 0.8106 0.7725
1.000 0.3754 0.02250 0.01667 -0.0642 0.8093 0.7742
1.250 0.3835 0.02247 0.01666 -0.0601 0.7976 0.7774
1.500 0.4273 0.02176 0.01595 -0.0626 0.7955 0.7805
1.750 0.4728 0.02112 0.01530 -0.0661 0.7916 0.7852
2.000 0.4982 0.02073 0.01492 -0.0657 0.7821 0.7897
2.250 0.5433 0.02009 0.01428 -0.0682 0.7786 0.7919
2.500 0.5578 0.01989 0.01410 -0.0654 0.7669 0.7956
2.750 0.6033 0.01934 0.01354 -0.0688 0.7601 0.7986
3.000 0.6420 0.01891 0.01310 -0.0717 0.7487 0.8027
3.250 0.6622 0.01860 0.01281 -0.0700 0.7353 0.8055
3.500 0.6840 0.01834 0.01256 -0.0684 0.7215 0.8081
3.750 0.7099 0.01810 0.01231 -0.0679 0.7063 0.8110
4.000 0.7398 0.01787 0.01204 -0.0685 0.6888 0.8142
4.250 0.7772 0.01771 0.01180 -0.0710 0.6690 0.8180
4.500 0.7964 0.01761 0.01166 -0.0694 0.6476 0.8208
4.750 0.8128 0.01759 0.01159 -0.0670 0.6248 0.8235
5.000 0.8335 0.01765 0.01154 -0.0657 0.6011 0.8266
5.250 0.8548 0.01779 0.01160 -0.0649 0.5759 0.8297
5.500 0.8804 0.01803 0.01173 -0.0653 0.5501 0.8329
5.750 0.9013 0.01830 0.01188 -0.0645 0.5254 0.8358
6.000 0.9142 0.01858 0.01209 -0.0618 0.5016 0.8382
6.250 0.9301 0.01894 0.01235 -0.0601 0.4779 0.8407
6.500 0.9477 0.01935 0.01269 -0.0589 0.4540 0.8433
6.750 0.9670 0.01982 0.01307 -0.0582 0.4307 0.8461
7.000 0.9901 0.02039 0.01353 -0.0584 0.4093 0.8491
7.250 1.0047 0.02082 0.01392 -0.0566 0.3899 0.8516
7.500 1.0174 0.02126 0.01433 -0.0544 0.3713 0.8540
7.750 1.0327 0.02180 0.01480 -0.0529 0.3534 0.8565
8.000 1.0503 0.02238 0.01534 -0.0520 0.3366 0.8590
8.250 1.0700 0.02299 0.01593 -0.0516 0.3205 0.8615
8.500 1.0920 0.02368 0.01660 -0.0518 0.3054 0.8643
8.750 1.1067 0.02423 0.01713 -0.0502 0.2928 0.8667
9.000 1.1196 0.02484 0.01769 -0.0484 0.2809 0.8691
9.250 1.1344 0.02549 0.01835 -0.0470 0.2682 0.8716
9.500 1.1508 0.02616 0.01907 -0.0461 0.2557 0.8744
9.750 1.1685 0.02694 0.01986 -0.0456 0.2439 0.8773
10.000 1.1877 0.02785 0.02072 -0.0456 0.2333 0.8796
10.250 1.2013 0.02853 0.02147 -0.0442 0.2237 0.8817
10.500 1.2148 0.02928 0.02227 -0.0428 0.2148 0.8840
10.750 1.2269 0.03013 0.02312 -0.0414 0.2058 0.8867
11.000 1.2408 0.03099 0.02408 -0.0404 0.1959 0.8895
11.250 1.2542 0.03206 0.02515 -0.0397 0.1867 0.8921
11.500 1.2687 0.03321 0.02633 -0.0394 0.1773 0.8942
11.750 1.2795 0.03422 0.02742 -0.0381 0.1688 0.8963
12.000 1.2875 0.03538 0.02860 -0.0366 0.1608 0.8986
12.250 1.2985 0.03648 0.02983 -0.0356 0.1523 0.9011
12.500 1.3061 0.03794 0.03127 -0.0345 0.1446 0.9035
12.750 1.3179 0.03925 0.03271 -0.0340 0.1361 0.9062
13.000 1.3263 0.04099 0.03444 -0.0335 0.1294 0.9087
13.250 1.3343 0.04232 0.03591 -0.0323 0.1228 0.9114
13.500 1.3373 0.04413 0.03772 -0.0310 0.1172 0.9140
13.750 1.3464 0.04569 0.03946 -0.0303 0.1111 0.9166
14.000 1.3523 0.04766 0.04148 -0.0298 0.1055 0.9191
14.250 1.3584 0.04977 0.04366 -0.0296 0.1000 0.9216
14.500 1.3643 0.05193 0.04592 -0.0295 0.0942 0.9239
14.750 1.3628 0.05444 0.04842 -0.0286 0.0896 0.9264
15.000 1.3686 0.05647 0.05063 -0.0283 0.0846 0.9293
15.250 1.3697 0.05916 0.05338 -0.0283 0.0801 0.9324
15.500 1.3701 0.06209 0.05637 -0.0284 0.0764 0.9353
15.750 1.3741 0.06456 0.05901 -0.0285 0.0725 0.9383
16.000 1.3731 0.06744 0.06201 -0.0285 0.0693 0.9416
16.250 1.3692 0.07093 0.06554 -0.0289 0.0666 0.9446
16.500 1.3697 0.07409 0.06884 -0.0295 0.0641 0.9477
16.750 1.3697 0.07734 0.07225 -0.0303 0.0610 0.9509
17.000 1.3644 0.08097 0.07597 -0.0308 0.0585 0.9549
17.250 1.3574 0.08512 0.08020 -0.0318 0.0565 0.9589
17.500 1.3512 0.08923 0.08439 -0.0329 0.0547 0.9630
17.750 1.3480 0.09268 0.08803 -0.0337 0.0530 0.9685
18.000 1.3436 0.09661 0.09214 -0.0350 0.0509 0.9744
18.250 1.3359 0.10106 0.09672 -0.0368 0.0486 0.9831
18.500 1.3254 0.10631 0.10207 -0.0394 0.0464 0.9999
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Polar data table (+)
Polar graphs
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