FX 75-VG-166/22 (fx75vg166-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 75-VG-166/22 (fx75vg166-il) Reynolds number: 500,000 Max Cl/Cd: 84.02 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx75vg166-il-500000-n5.txt Download as CSV file: xf-fx75vg166-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 75-VG-166/22
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -0.6227 0.07247 0.06830 -0.0964 0.7387 0.0084
-15.250 -0.6583 0.06204 0.05761 -0.1034 0.7384 0.0083
-15.000 -0.6897 0.05414 0.04946 -0.1077 0.7380 0.0084
-14.750 -0.6974 0.05026 0.04542 -0.1094 0.7376 0.0085
-14.500 -0.7087 0.04636 0.04134 -0.1102 0.7371 0.0085
-14.250 -0.7189 0.04294 0.03771 -0.1102 0.7366 0.0087
-14.000 -0.7212 0.04047 0.03507 -0.1099 0.7361 0.0089
-13.750 -0.7237 0.03805 0.03249 -0.1091 0.7356 0.0087
-13.500 -0.7233 0.03596 0.03021 -0.1081 0.7349 0.0090
-13.250 -0.7210 0.03405 0.02811 -0.1069 0.7343 0.0092
-13.000 -0.7154 0.03245 0.02637 -0.1058 0.7337 0.0092
-12.750 -0.7080 0.03099 0.02475 -0.1046 0.7331 0.0094
-12.500 -0.6979 0.02978 0.02339 -0.1034 0.7325 0.0096
-12.250 -0.6875 0.02858 0.02206 -0.1022 0.7319 0.0096
-12.000 -0.6755 0.02756 0.02094 -0.1011 0.7312 0.0096
-11.750 -0.6653 0.02638 0.01969 -0.0997 0.7305 0.0100
-11.500 -0.6512 0.02556 0.01881 -0.0986 0.7297 0.0102
-11.250 -0.6368 0.02475 0.01790 -0.0974 0.7288 0.0102
-11.000 -0.6203 0.02417 0.01728 -0.0964 0.7279 0.0106
-10.750 -0.6039 0.02350 0.01653 -0.0954 0.7272 0.0111
-10.500 -0.5888 0.02264 0.01558 -0.0941 0.7264 0.0110
-10.250 -0.5710 0.02208 0.01495 -0.0932 0.7258 0.0116
-10.000 -0.5528 0.02153 0.01430 -0.0922 0.7252 0.0121
-9.750 -0.5353 0.02093 0.01362 -0.0912 0.7245 0.0123
-9.500 -0.5190 0.02026 0.01291 -0.0898 0.7239 0.0127
-9.250 -0.5011 0.01976 0.01241 -0.0888 0.7232 0.0132
-9.000 -0.4833 0.01926 0.01188 -0.0876 0.7224 0.0136
-8.750 -0.4635 0.01892 0.01152 -0.0868 0.7216 0.0144
-8.500 -0.4448 0.01848 0.01105 -0.0857 0.7208 0.0150
-8.250 -0.4260 0.01807 0.01059 -0.0846 0.7200 0.0157
-8.000 -0.4086 0.01758 0.01009 -0.0833 0.7191 0.0165
-7.750 -0.3895 0.01721 0.00971 -0.0822 0.7182 0.0173
-7.500 -0.3710 0.01681 0.00929 -0.0809 0.7174 0.0183
-7.250 -0.3520 0.01646 0.00890 -0.0797 0.7166 0.0192
-7.000 -0.3332 0.01613 0.00853 -0.0785 0.7158 0.0197
-6.750 -0.3161 0.01573 0.00815 -0.0770 0.7150 0.0213
-6.500 -0.2979 0.01545 0.00785 -0.0756 0.7143 0.0226
-6.250 -0.2800 0.01519 0.00756 -0.0741 0.7136 0.0238
-6.000 -0.2629 0.01491 0.00727 -0.0725 0.7129 0.0252
-5.750 -0.2448 0.01467 0.00701 -0.0710 0.7121 0.0273
-5.500 -0.2242 0.01446 0.00677 -0.0700 0.7114 0.0295
-5.250 -0.2038 0.01422 0.00654 -0.0689 0.7108 0.0326
-5.000 -0.1832 0.01402 0.00635 -0.0678 0.7099 0.0372
-4.750 -0.1628 0.01382 0.00619 -0.0668 0.7087 0.0428
-4.500 -0.1424 0.01360 0.00604 -0.0657 0.7075 0.0531
-4.250 -0.1221 0.01336 0.00589 -0.0646 0.7063 0.0708
-4.000 -0.1018 0.01309 0.00574 -0.0636 0.7052 0.0959
-3.750 -0.0819 0.01277 0.00557 -0.0625 0.7041 0.1335
-3.500 -0.0638 0.01234 0.00539 -0.0612 0.7030 0.1949
-3.250 -0.0470 0.01180 0.00518 -0.0597 0.7020 0.2775
-3.000 -0.0316 0.01114 0.00492 -0.0580 0.7010 0.3810
-2.750 -0.0185 0.01025 0.00454 -0.0560 0.6999 0.5126
-2.500 -0.0058 0.00952 0.00450 -0.0532 0.6989 0.6690
-2.250 0.0220 0.00998 0.00513 -0.0526 0.6981 0.7210
-2.000 0.0524 0.01048 0.00563 -0.0526 0.6974 0.7378
-1.750 0.0812 0.01082 0.00594 -0.0528 0.6962 0.7557
-1.500 0.1087 0.01125 0.00636 -0.0527 0.6946 0.7679
-1.250 0.1358 0.01145 0.00653 -0.0527 0.6930 0.7749
-1.000 0.1634 0.01161 0.00667 -0.0527 0.6916 0.7779
-0.750 0.1915 0.01176 0.00682 -0.0527 0.6902 0.7795
-0.500 0.2196 0.01182 0.00686 -0.0528 0.6889 0.7811
-0.250 0.2478 0.01183 0.00685 -0.0530 0.6878 0.7827
0.000 0.2760 0.01182 0.00681 -0.0533 0.6868 0.7845
0.250 0.3045 0.01176 0.00672 -0.0536 0.6857 0.7868
0.500 0.3330 0.01165 0.00656 -0.0541 0.6848 0.7897
0.750 0.3618 0.01158 0.00647 -0.0545 0.6839 0.7909
1.000 0.3892 0.01160 0.00650 -0.0545 0.6824 0.7917
1.250 0.4150 0.01167 0.00661 -0.0543 0.6798 0.7925
1.500 0.4419 0.01167 0.00664 -0.0544 0.6776 0.7934
1.750 0.4696 0.01163 0.00662 -0.0545 0.6755 0.7942
2.000 0.4977 0.01156 0.00655 -0.0547 0.6736 0.7952
2.250 0.5262 0.01148 0.00647 -0.0550 0.6721 0.7962
2.500 0.5549 0.01137 0.00637 -0.0554 0.6706 0.7970
2.750 0.5840 0.01125 0.00623 -0.0558 0.6691 0.7979
3.000 0.6091 0.01128 0.00632 -0.0556 0.6650 0.7989
3.250 0.6359 0.01124 0.00633 -0.0557 0.6617 0.8000
3.500 0.6638 0.01115 0.00625 -0.0559 0.6587 0.8010
3.750 0.6921 0.01103 0.00615 -0.0562 0.6562 0.8022
4.000 0.7195 0.01093 0.00606 -0.0564 0.6510 0.8035
4.250 0.7465 0.01075 0.00589 -0.0564 0.6412 0.8046
4.500 0.7727 0.01064 0.00579 -0.0562 0.6301 0.8054
4.750 0.7988 0.01053 0.00568 -0.0560 0.6201 0.8060
5.000 0.8245 0.01048 0.00564 -0.0557 0.6113 0.8067
5.250 0.8492 0.01050 0.00567 -0.0552 0.6009 0.8075
5.500 0.8724 0.01054 0.00570 -0.0545 0.5854 0.8082
5.750 0.8940 0.01064 0.00576 -0.0535 0.5649 0.8088
6.000 0.9097 0.01087 0.00587 -0.0513 0.5351 0.8096
6.250 0.9139 0.01144 0.00619 -0.0470 0.4867 0.8106
6.500 0.9147 0.01206 0.00664 -0.0423 0.4481 0.8118
6.750 0.9051 0.01274 0.00715 -0.0357 0.4102 0.8131
7.000 0.8912 0.01364 0.00788 -0.0287 0.3747 0.8146
7.500 0.8771 0.01617 0.01020 -0.0196 0.3236 0.8175
7.750 0.8689 0.01757 0.01143 -0.0152 0.2897 0.8185
8.000 0.8661 0.01879 0.01248 -0.0116 0.2588 0.8193
8.250 0.8616 0.02013 0.01361 -0.0079 0.2219 0.8199
8.500 0.8665 0.02108 0.01444 -0.0055 0.1994 0.8204
8.750 0.8702 0.02213 0.01536 -0.0030 0.1715 0.8209
9.000 0.8790 0.02300 0.01615 -0.0012 0.1549 0.8213
9.250 0.8888 0.02385 0.01693 0.0004 0.1375 0.8217
9.500 0.8997 0.02467 0.01771 0.0018 0.1240 0.8221
10.000 0.9209 0.02646 0.01938 0.0046 0.0957 0.8227
10.250 0.9310 0.02743 0.02026 0.0059 0.0784 0.8230
10.500 0.9390 0.02855 0.02128 0.0073 0.0612 0.8233
10.750 0.9516 0.02946 0.02217 0.0082 0.0528 0.8236
11.000 0.9607 0.03065 0.02327 0.0093 0.0406 0.8238
11.250 0.9740 0.03159 0.02423 0.0101 0.0351 0.8240
11.500 0.9863 0.03265 0.02528 0.0108 0.0302 0.8242
11.750 0.9987 0.03373 0.02636 0.0115 0.0265 0.8244
12.000 1.0123 0.03475 0.02741 0.0120 0.0243 0.8246
12.250 1.0246 0.03590 0.02857 0.0126 0.0227 0.8248
12.500 1.0374 0.03702 0.02975 0.0131 0.0211 0.8249
12.750 1.0499 0.03820 0.03097 0.0136 0.0194 0.8251
13.000 1.0623 0.03941 0.03223 0.0140 0.0189 0.8254
13.250 1.0724 0.04084 0.03369 0.0145 0.0177 0.8255
13.500 1.0846 0.04213 0.03504 0.0148 0.0170 0.8256
13.750 1.0963 0.04348 0.03645 0.0151 0.0158 0.8257
14.000 1.1071 0.04492 0.03795 0.0154 0.0150 0.8260
14.250 1.1167 0.04651 0.03960 0.0157 0.0147 0.8263
14.500 1.1231 0.04842 0.04156 0.0160 0.0141 0.8267
14.750 1.1337 0.04996 0.04318 0.0162 0.0135 0.8273
15.000 1.1416 0.05179 0.04510 0.0164 0.0132 0.8275
15.250 1.1503 0.05359 0.04697 0.0165 0.0127 0.8278
15.500 1.1582 0.05551 0.04897 0.0164 0.0124 0.8280
15.750 1.1658 0.05751 0.05104 0.0163 0.0121 0.8280
16.000 1.1711 0.05978 0.05337 0.0162 0.0116 0.8280
16.250 1.1771 0.06201 0.05566 0.0160 0.0113 0.8281
16.500 1.1771 0.06495 0.05868 0.0158 0.0110 0.8281
16.750 1.1799 0.06763 0.06147 0.0155 0.0109 0.8281
17.000 1.1872 0.06988 0.06381 0.0150 0.0106 0.8282
17.250 1.1859 0.07316 0.06719 0.0145 0.0104 0.8282
17.500 1.1903 0.07579 0.06991 0.0139 0.0103 0.8282
17.750 1.1915 0.07888 0.07312 0.0132 0.0101 0.8282
18.000 1.1924 0.08205 0.07639 0.0123 0.0098 0.8283
18.250 1.1916 0.08551 0.07995 0.0114 0.0098 0.8283
18.500 1.1917 0.08891 0.08345 0.0103 0.0095 0.8283
18.750 1.1917 0.09238 0.08701 0.0091 0.0095 0.8283
19.000 1.1889 0.09626 0.09099 0.0077 0.0093 0.8283
19.250 1.1861 0.10021 0.09504 0.0062 0.0092 0.8284
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