FX 67-K-170/17 AIRFOIL (fx67k170-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 67-K-170/17 AIRFOIL (fx67k170-il) Reynolds number: 1,000,000 Max Cl/Cd: 152.67 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx67k170-il-1000000.txt Download as CSV file: xf-fx67k170-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.0924 0.08876 0.08580 -0.1095 0.7264 0.0107
-11.000 -0.0932 0.08455 0.08161 -0.1114 0.7254 0.0108
-10.750 -0.0917 0.08106 0.07815 -0.1130 0.7242 0.0108
-10.500 -0.0885 0.07814 0.07524 -0.1145 0.7228 0.0110
-10.250 -0.0918 0.07372 0.07084 -0.1167 0.7212 0.0110
-10.000 -0.0980 0.06873 0.06589 -0.1193 0.7197 0.0111
-9.750 -0.1105 0.06200 0.05918 -0.1240 0.7181 0.0111
-9.500 -0.1546 0.05155 0.04865 -0.1306 0.7162 0.0109
-9.250 -0.2809 0.03679 0.03339 -0.1221 0.7137 0.0079
-9.000 -0.2742 0.03603 0.03256 -0.1208 0.7120 0.0080
-8.750 -0.2774 0.03322 0.02956 -0.1183 0.7106 0.0081
-8.500 -0.2657 0.03213 0.02839 -0.1172 0.7090 0.0083
-8.250 -0.3077 0.02019 0.01514 -0.1088 0.7073 0.0076
-8.000 -0.2949 0.01760 0.01221 -0.1072 0.7056 0.0081
-7.750 -0.2720 0.01686 0.01137 -0.1068 0.7040 0.0083
-7.500 -0.2470 0.01655 0.01100 -0.1067 0.7024 0.0086
-7.250 -0.2234 0.01576 0.01008 -0.1063 0.7008 0.0089
-7.000 -0.1988 0.01522 0.00942 -0.1061 0.6991 0.0092
-6.750 -0.1746 0.01450 0.00861 -0.1058 0.6977 0.0095
-6.500 -0.1502 0.01381 0.00784 -0.1054 0.6963 0.0098
-6.250 -0.1252 0.01327 0.00724 -0.1052 0.6947 0.0101
-6.000 -0.1011 0.01263 0.00652 -0.1048 0.6931 0.0105
-5.750 -0.0760 0.01217 0.00604 -0.1047 0.6913 0.0113
-5.500 -0.0487 0.01201 0.00587 -0.1049 0.6897 0.0120
-5.250 -0.0222 0.01172 0.00554 -0.1049 0.6882 0.0130
-5.000 0.0051 0.01155 0.00531 -0.1050 0.6866 0.0138
-4.750 0.0293 0.01103 0.00474 -0.1047 0.6847 0.0154
-4.500 0.0566 0.01084 0.00456 -0.1049 0.6834 0.0173
-4.250 0.0831 0.01054 0.00423 -0.1049 0.6820 0.0194
-4.000 0.1093 0.01021 0.00390 -0.1049 0.6803 0.0217
-3.750 0.1368 0.01003 0.00370 -0.1051 0.6785 0.0235
-3.500 0.1648 0.00990 0.00356 -0.1054 0.6768 0.0247
-3.250 0.1915 0.00960 0.00320 -0.1055 0.6752 0.0270
-3.000 0.2192 0.00944 0.00302 -0.1057 0.6737 0.0288
-2.750 0.2472 0.00933 0.00287 -0.1060 0.6720 0.0308
-2.500 0.2753 0.00926 0.00276 -0.1063 0.6702 0.0323
-2.250 0.3030 0.00909 0.00263 -0.1066 0.6688 0.0399
-2.000 0.3277 0.00852 0.00247 -0.1065 0.6672 0.1587
-1.750 0.3507 0.00776 0.00231 -0.1064 0.6654 0.3512
-1.500 0.3744 0.00711 0.00220 -0.1063 0.6636 0.5218
-1.250 0.3992 0.00669 0.00216 -0.1061 0.6619 0.6462
-1.000 0.4253 0.00656 0.00225 -0.1059 0.6604 0.7318
-0.750 0.4536 0.00662 0.00232 -0.1061 0.6587 0.7580
-0.500 0.4823 0.00672 0.00240 -0.1065 0.6568 0.7720
-0.250 0.5106 0.00678 0.00247 -0.1068 0.6553 0.7835
0.000 0.5392 0.00685 0.00253 -0.1071 0.6536 0.7930
0.250 0.5674 0.00689 0.00259 -0.1074 0.6518 0.7998
0.500 0.5960 0.00697 0.00265 -0.1077 0.6501 0.8071
0.750 0.6241 0.00701 0.00271 -0.1080 0.6484 0.8139
1.000 0.6528 0.00706 0.00274 -0.1084 0.6467 0.8182
1.250 0.6817 0.00712 0.00277 -0.1089 0.6449 0.8220
1.500 0.7104 0.00719 0.00281 -0.1094 0.6429 0.8252
1.750 0.7385 0.00722 0.00287 -0.1097 0.6412 0.8280
2.000 0.7664 0.00722 0.00289 -0.1100 0.6381 0.8310
2.250 0.7946 0.00721 0.00288 -0.1104 0.6345 0.8342
2.500 0.8231 0.00725 0.00291 -0.1108 0.6321 0.8371
2.750 0.8513 0.00729 0.00293 -0.1112 0.6297 0.8397
3.000 0.8793 0.00734 0.00300 -0.1116 0.6275 0.8421
3.250 0.9070 0.00737 0.00307 -0.1119 0.6251 0.8445
3.500 0.9349 0.00740 0.00312 -0.1123 0.6225 0.8469
3.750 0.9627 0.00743 0.00316 -0.1127 0.6194 0.8493
4.000 0.9905 0.00749 0.00319 -0.1130 0.6159 0.8514
4.250 1.0174 0.00751 0.00325 -0.1132 0.6116 0.8536
4.500 1.0442 0.00752 0.00330 -0.1134 0.6073 0.8559
4.750 1.0710 0.00757 0.00337 -0.1136 0.6038 0.8583
5.000 1.0975 0.00765 0.00345 -0.1137 0.5998 0.8608
5.250 1.1240 0.00769 0.00355 -0.1138 0.5954 0.8633
5.500 1.1500 0.00776 0.00363 -0.1139 0.5901 0.8655
5.750 1.1751 0.00785 0.00373 -0.1138 0.5838 0.8677
6.000 1.1995 0.00791 0.00383 -0.1136 0.5761 0.8701
6.250 1.2232 0.00802 0.00396 -0.1132 0.5689 0.8725
6.500 1.2458 0.00816 0.00411 -0.1126 0.5602 0.8752
6.750 1.2657 0.00835 0.00430 -0.1115 0.5469 0.8782
7.000 1.2836 0.00860 0.00453 -0.1101 0.5330 0.8811
7.250 1.2938 0.00895 0.00485 -0.1072 0.5149 0.8849
7.500 1.2812 0.00961 0.00542 -0.1000 0.4861 0.8917
7.750 1.2686 0.01058 0.00635 -0.0935 0.4620 0.8995
8.000 1.2419 0.01245 0.00811 -0.0857 0.4277 0.9128
8.250 1.2341 0.01380 0.00945 -0.0811 0.4042 0.9339
8.500 1.2209 0.01699 0.01239 -0.0787 0.3447 1.0000
8.750 1.2054 0.01929 0.01448 -0.0742 0.3052 1.0000
9.000 1.2099 0.02059 0.01572 -0.0721 0.2884 1.0000
9.250 1.1920 0.02319 0.01806 -0.0676 0.2429 1.0000
9.500 1.1768 0.02586 0.02046 -0.0637 0.1956 1.0000
9.750 1.1781 0.02758 0.02205 -0.0616 0.1706 1.0000
10.000 1.1713 0.02990 0.02416 -0.0589 0.1320 1.0000
10.250 1.1693 0.03198 0.02608 -0.0567 0.1017 1.0000
10.500 1.1638 0.03436 0.02824 -0.0543 0.0645 1.0000
10.750 1.1685 0.03607 0.02987 -0.0529 0.0476 1.0000
11.000 1.1793 0.03734 0.03112 -0.0520 0.0425 1.0000
11.250 1.1895 0.03871 0.03248 -0.0511 0.0386 1.0000
11.500 1.2012 0.03996 0.03376 -0.0504 0.0355 1.0000
11.750 1.2143 0.04111 0.03495 -0.0498 0.0344 1.0000
12.000 1.2240 0.04254 0.03638 -0.0490 0.0316 1.0000
12.250 1.2341 0.04396 0.03782 -0.0483 0.0295 1.0000
12.500 1.2451 0.04531 0.03920 -0.0476 0.0270 1.0000
12.750 1.2605 0.04632 0.04024 -0.0474 0.0247 1.0000
13.000 1.2695 0.04789 0.04180 -0.0467 0.0191 1.0000
13.250 1.2684 0.05033 0.04412 -0.0453 0.0065 1.0000
13.500 1.2739 0.05228 0.04610 -0.0445 0.0048 1.0000
13.750 1.2811 0.05409 0.04795 -0.0438 0.0041 1.0000
14.000 1.2890 0.05586 0.04978 -0.0432 0.0039 1.0000
14.250 1.2974 0.05763 0.05160 -0.0427 0.0038 1.0000
14.500 1.3053 0.05944 0.05347 -0.0422 0.0035 1.0000
14.750 1.3112 0.06148 0.05557 -0.0416 0.0033 1.0000
15.000 1.3170 0.06356 0.05772 -0.0411 0.0031 1.0000
15.250 1.3226 0.06570 0.05993 -0.0407 0.0030 1.0000
15.500 1.3264 0.06810 0.06239 -0.0403 0.0029 1.0000
15.750 1.3317 0.07033 0.06469 -0.0399 0.0029 1.0000
16.000 1.3320 0.07317 0.06761 -0.0396 0.0027 1.0000
16.250 1.3285 0.07652 0.07107 -0.0391 0.0026 1.0000
16.500 1.3306 0.07930 0.07393 -0.0390 0.0026 1.0000
16.750 1.3363 0.08166 0.07635 -0.0390 0.0025 1.0000
17.000 1.3356 0.08487 0.07966 -0.0391 0.0025 1.0000
17.250 1.3378 0.08773 0.08260 -0.0392 0.0024 1.0000
17.500 1.3390 0.09078 0.08573 -0.0394 0.0024 1.0000
17.750 1.3417 0.09368 0.08871 -0.0398 0.0023 1.0000
18.000 1.3408 0.09712 0.09224 -0.0402 0.0023 1.0000
18.250 1.3398 0.10063 0.09585 -0.0407 0.0023 1.0000
18.500 1.3373 0.10438 0.09969 -0.0414 0.0023 1.0000
18.750 1.3364 0.10792 0.10332 -0.0421 0.0022 1.0000
19.000 1.3345 0.11170 0.10719 -0.0430 0.0022 1.0000
19.250 1.3344 0.11522 0.11080 -0.0440 0.0022 1.0000
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