FX 67-K-170/17 AIRFOIL (fx67k170-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 67-K-170/17 AIRFOIL (fx67k170-il) Reynolds number: 500,000 Max Cl/Cd: 116.94 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx67k170-il-500000.txt Download as CSV file: xf-fx67k170-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: FX 67-K-170/17 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.0445 0.10230 0.09910 -0.0927 0.7477 0.0182
-11.750 -0.0443 0.09808 0.09487 -0.0952 0.7467 0.0184
-11.500 -0.0424 0.09402 0.09082 -0.0970 0.7457 0.0185
-11.250 -0.0414 0.08975 0.08654 -0.0989 0.7447 0.0185
-11.000 -0.0413 0.08522 0.08201 -0.1009 0.7437 0.0186
-10.750 -0.0419 0.08058 0.07736 -0.1028 0.7428 0.0186
-10.500 -0.0520 0.07424 0.07105 -0.1046 0.7418 0.0190
-10.250 -0.0514 0.07048 0.06729 -0.1058 0.7405 0.0192
-10.000 -0.0526 0.06630 0.06314 -0.1075 0.7391 0.0193
-9.750 -0.0555 0.06193 0.05880 -0.1093 0.7376 0.0195
-9.500 -0.0628 0.05643 0.05333 -0.1122 0.7362 0.0196
-9.250 -0.1097 0.04431 0.04110 -0.1217 0.7350 0.0192
-9.000 -0.1368 0.04021 0.03688 -0.1225 0.7332 0.0191
-8.750 -0.1490 0.03758 0.03420 -0.1215 0.7315 0.0193
-8.500 -0.1958 0.04689 0.04304 -0.1229 0.7326 0.0189
-8.250 -0.1976 0.04386 0.03991 -0.1215 0.7310 0.0192
-8.000 -0.1915 0.04172 0.03767 -0.1205 0.7295 0.0195
-7.750 -0.1849 0.03954 0.03534 -0.1193 0.7281 0.0198
-7.500 -0.1762 0.03753 0.03319 -0.1181 0.7265 0.0202
-7.250 -0.1664 0.03529 0.03079 -0.1167 0.7245 0.0207
-7.000 -0.1543 0.03314 0.02846 -0.1154 0.7225 0.0216
-6.750 -0.1499 0.02730 0.02193 -0.1117 0.7206 0.0172
-6.500 -0.1364 0.02334 0.01746 -0.1096 0.7189 0.0157
-6.250 -0.1149 0.02137 0.01519 -0.1087 0.7174 0.0157
-6.000 -0.0904 0.02046 0.01411 -0.1084 0.7160 0.0166
-5.750 -0.0651 0.01945 0.01289 -0.1081 0.7147 0.0175
-5.500 -0.0394 0.01839 0.01163 -0.1078 0.7134 0.0179
-5.250 -0.0134 0.01787 0.01097 -0.1075 0.7117 0.0185
-5.000 0.0087 0.01610 0.00918 -0.1068 0.7098 0.0198
-4.750 0.0331 0.01553 0.00861 -0.1065 0.7078 0.0214
-4.500 0.0581 0.01505 0.00809 -0.1062 0.7060 0.0235
-4.250 0.0814 0.01433 0.00733 -0.1057 0.7044 0.0265
-4.000 0.1072 0.01398 0.00696 -0.1057 0.7029 0.0297
-3.750 0.1338 0.01368 0.00660 -0.1057 0.7015 0.0319
-3.500 0.1591 0.01318 0.00603 -0.1055 0.7002 0.0352
-3.250 0.1862 0.01298 0.00579 -0.1057 0.6988 0.0391
-3.000 0.2121 0.01281 0.00561 -0.1056 0.6969 0.0415
-2.750 0.2380 0.01261 0.00540 -0.1055 0.6949 0.0462
-2.500 0.2636 0.01231 0.00520 -0.1054 0.6930 0.0714
-2.250 0.2806 0.01091 0.00492 -0.1047 0.6912 0.3828
-2.000 0.3005 0.01004 0.00480 -0.1038 0.6895 0.6003
-1.750 0.3248 0.00981 0.00488 -0.1031 0.6881 0.7039
-1.500 0.3519 0.00988 0.00499 -0.1029 0.6867 0.7526
-1.250 0.3797 0.01004 0.00512 -0.1028 0.6853 0.7802
-1.000 0.4058 0.01028 0.00536 -0.1023 0.6838 0.7993
-0.750 0.4312 0.01046 0.00555 -0.1019 0.6817 0.8110
-0.500 0.4574 0.01060 0.00569 -0.1017 0.6797 0.8207
-0.250 0.4838 0.01069 0.00578 -0.1015 0.6778 0.8278
0.000 0.5106 0.01079 0.00585 -0.1014 0.6761 0.8379
0.250 0.5366 0.01084 0.00590 -0.1009 0.6745 0.8459
0.500 0.5654 0.01088 0.00588 -0.1014 0.6731 0.8520
0.750 0.5934 0.01089 0.00586 -0.1015 0.6719 0.8560
1.000 0.6219 0.01098 0.00590 -0.1019 0.6705 0.8601
1.250 0.6470 0.01109 0.00605 -0.1018 0.6684 0.8647
1.500 0.6729 0.01116 0.00614 -0.1018 0.6661 0.8686
1.750 0.6987 0.01119 0.00620 -0.1016 0.6640 0.8722
2.000 0.7258 0.01123 0.00624 -0.1018 0.6623 0.8761
2.250 0.7542 0.01126 0.00626 -0.1023 0.6607 0.8799
2.500 0.7832 0.01126 0.00623 -0.1029 0.6593 0.8830
2.750 0.8119 0.01125 0.00622 -0.1033 0.6579 0.8858
3.000 0.8394 0.01128 0.00624 -0.1035 0.6555 0.8889
3.250 0.8630 0.01128 0.00631 -0.1031 0.6517 0.8924
3.500 0.8909 0.01119 0.00621 -0.1035 0.6483 0.8956
3.750 0.9200 0.01108 0.00609 -0.1040 0.6457 0.8982
4.000 0.9489 0.01105 0.00606 -0.1045 0.6439 0.9010
4.250 0.9756 0.01109 0.00612 -0.1047 0.6415 0.9042
4.500 0.9984 0.01115 0.00627 -0.1041 0.6379 0.9080
4.750 1.0252 0.01111 0.00626 -0.1044 0.6345 0.9112
5.000 1.0535 0.01097 0.00612 -0.1047 0.6312 0.9140
5.250 1.0831 0.01093 0.00607 -0.1053 0.6284 0.9168
5.500 1.1034 0.01102 0.00627 -0.1044 0.6247 0.9209
5.750 1.1280 0.01103 0.00634 -0.1042 0.6209 0.9248
6.000 1.1550 0.01097 0.00630 -0.1044 0.6174 0.9280
6.250 1.1821 0.01093 0.00629 -0.1046 0.6138 0.9317
6.500 1.2003 0.01100 0.00648 -0.1032 0.6087 0.9374
6.750 1.2240 0.01094 0.00646 -0.1027 0.6034 0.9422
7.000 1.2453 0.01093 0.00652 -0.1018 0.5972 0.9488
7.250 1.2651 0.01094 0.00660 -0.1008 0.5895 0.9581
7.500 1.2909 0.01104 0.00677 -0.1011 0.5813 0.9690
8.000 1.3355 0.01142 0.00726 -0.1008 0.5616 1.0000
8.250 1.3446 0.01180 0.00766 -0.0982 0.5510 1.0000
8.500 1.3492 0.01241 0.00827 -0.0951 0.5375 1.0000
8.750 1.3486 0.01339 0.00922 -0.0917 0.5191 1.0000
9.000 1.3431 0.01475 0.01049 -0.0877 0.4943 1.0000
9.250 1.3285 0.01665 0.01222 -0.0828 0.4613 1.0000
9.500 1.3025 0.01929 0.01461 -0.0767 0.4194 1.0000
9.750 1.2970 0.02104 0.01628 -0.0734 0.3982 1.0000
10.000 1.2791 0.02357 0.01862 -0.0688 0.3646 1.0000
10.250 1.2627 0.02626 0.02112 -0.0648 0.3303 1.0000
10.500 1.2465 0.02915 0.02380 -0.0611 0.2914 1.0000
10.750 1.2412 0.03143 0.02594 -0.0586 0.2628 1.0000
11.000 1.2329 0.03402 0.02835 -0.0560 0.2289 1.0000
11.250 1.2238 0.03675 0.03087 -0.0535 0.1915 1.0000
11.500 1.2139 0.03963 0.03350 -0.0511 0.1506 1.0000
11.750 1.2072 0.04233 0.03597 -0.0490 0.1134 1.0000
12.000 1.2021 0.04500 0.03843 -0.0472 0.0799 1.0000
12.250 1.2022 0.04732 0.04063 -0.0459 0.0592 1.0000
12.500 1.2084 0.04916 0.04244 -0.0450 0.0508 1.0000
12.750 1.2151 0.05098 0.04426 -0.0443 0.0445 1.0000
13.000 1.2239 0.05266 0.04597 -0.0437 0.0417 1.0000
13.250 1.2310 0.05450 0.04783 -0.0430 0.0381 1.0000
13.500 1.2392 0.05628 0.04966 -0.0425 0.0348 1.0000
13.750 1.2470 0.05812 0.05153 -0.0421 0.0311 1.0000
14.000 1.2537 0.06008 0.05351 -0.0415 0.0267 1.0000
14.250 1.2632 0.06179 0.05518 -0.0412 0.0152 1.0000
14.500 1.2635 0.06448 0.05780 -0.0405 0.0096 1.0000
14.750 1.2644 0.06720 0.06057 -0.0399 0.0078 1.0000
15.000 1.2702 0.06944 0.06289 -0.0396 0.0072 1.0000
15.250 1.2747 0.07183 0.06537 -0.0393 0.0067 1.0000
15.500 1.2780 0.07442 0.06805 -0.0390 0.0063 1.0000
15.750 1.2811 0.07707 0.07079 -0.0389 0.0061 1.0000
16.000 1.2819 0.08006 0.07386 -0.0387 0.0059 1.0000
16.250 1.2793 0.08351 0.07742 -0.0386 0.0056 1.0000
16.500 1.2813 0.08644 0.08045 -0.0387 0.0055 1.0000
16.750 1.2822 0.08957 0.08368 -0.0389 0.0053 1.0000
17.000 1.2835 0.09268 0.08688 -0.0391 0.0052 1.0000
17.250 1.2822 0.09620 0.09051 -0.0395 0.0050 1.0000
17.500 1.2821 0.09959 0.09400 -0.0399 0.0049 1.0000
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