FX 79-W-151 A (fx79w151a-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 79-W-151 A (fx79w151a-il) Reynolds number: 1,000,000 Max Cl/Cd: 132.22 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx79w151a-il-1000000.txt Download as CSV file: xf-fx79w151a-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: FX 79-W-151 A
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
------ -------- --------- --------- -------- -------- --------
-16.000 -0.8007 0.08569 0.08331 -0.0482 1.0000 0.0086
-15.750 -0.8419 0.07545 0.07293 -0.0543 1.0000 0.0084
-15.500 -0.8882 0.06417 0.06149 -0.0612 1.0000 0.0082
-15.250 -0.9344 0.05152 0.04864 -0.0701 1.0000 0.0082
-15.000 -0.9596 0.04190 0.03877 -0.0789 1.0000 0.0080
-14.750 -0.9760 0.03582 0.03252 -0.0842 1.0000 0.0082
-14.500 -0.9836 0.03230 0.02889 -0.0860 1.0000 0.0085
-14.250 -0.9912 0.02948 0.02591 -0.0858 0.9847 0.0084
-14.000 -0.9644 0.02719 0.02348 -0.0905 0.9719 0.0086
-13.750 -0.9337 0.02529 0.02143 -0.0949 0.9600 0.0088
-13.500 -0.9012 0.02410 0.02011 -0.0981 0.9464 0.0093
-13.250 -0.8849 0.02277 0.01860 -0.0984 0.9280 0.0093
-13.000 -0.8768 0.02184 0.01752 -0.0961 0.9104 0.0095
-12.750 -0.8702 0.02108 0.01662 -0.0931 0.8961 0.0095
-12.500 -0.8593 0.02058 0.01599 -0.0906 0.8846 0.0099
-12.250 -0.8496 0.02000 0.01530 -0.0878 0.8733 0.0102
-12.000 -0.8367 0.01940 0.01460 -0.0856 0.8639 0.0102
-11.500 -0.8159 0.01771 0.01263 -0.0803 0.8457 0.0109
-11.250 -0.8014 0.01702 0.01182 -0.0783 0.8377 0.0113
-11.000 -0.7841 0.01644 0.01117 -0.0766 0.8297 0.0118
-10.750 -0.7654 0.01596 0.01060 -0.0752 0.8226 0.0122
-10.500 -0.7455 0.01551 0.01007 -0.0739 0.8149 0.0126
-10.250 -0.7253 0.01508 0.00954 -0.0726 0.8080 0.0133
-10.000 -0.7045 0.01463 0.00902 -0.0715 0.8007 0.0139
-9.750 -0.6856 0.01404 0.00834 -0.0700 0.7938 0.0151
-9.500 -0.6634 0.01365 0.00791 -0.0690 0.7868 0.0166
-9.250 -0.6405 0.01336 0.00754 -0.0681 0.7798 0.0177
-9.000 -0.6196 0.01284 0.00700 -0.0670 0.7732 0.0204
-8.750 -0.5957 0.01260 0.00670 -0.0663 0.7663 0.0224
-8.500 -0.5734 0.01219 0.00626 -0.0653 0.7599 0.0252
-8.250 -0.5494 0.01192 0.00596 -0.0646 0.7532 0.0278
-8.000 -0.5255 0.01167 0.00564 -0.0639 0.7469 0.0300
-7.750 -0.5018 0.01133 0.00530 -0.0632 0.7402 0.0334
-7.500 -0.4772 0.01114 0.00504 -0.0626 0.7335 0.0358
-7.250 -0.4529 0.01085 0.00473 -0.0619 0.7271 0.0397
-7.000 -0.4285 0.01060 0.00447 -0.0613 0.7202 0.0436
-6.750 -0.4038 0.01038 0.00422 -0.0607 0.7140 0.0486
-6.500 -0.3788 0.01016 0.00400 -0.0601 0.7072 0.0542
-6.250 -0.3541 0.00996 0.00379 -0.0595 0.7008 0.0615
-6.000 -0.3282 0.00980 0.00362 -0.0592 0.6943 0.0674
-5.750 -0.3032 0.00962 0.00346 -0.0586 0.6876 0.0764
-5.500 -0.2769 0.00950 0.00331 -0.0583 0.6814 0.0824
-5.250 -0.2512 0.00937 0.00318 -0.0579 0.6743 0.0893
-5.000 -0.2245 0.00931 0.00307 -0.0576 0.6680 0.0928
-4.750 -0.1989 0.00914 0.00290 -0.0572 0.6614 0.0994
-4.500 -0.1728 0.00907 0.00279 -0.0568 0.6551 0.1044
-4.250 -0.1460 0.00898 0.00268 -0.0566 0.6489 0.1084
-4.000 -0.1203 0.00887 0.00255 -0.0561 0.6425 0.1149
-3.750 -0.0937 0.00879 0.00245 -0.0559 0.6364 0.1200
-3.500 -0.0675 0.00869 0.00234 -0.0555 0.6301 0.1264
-3.250 -0.0414 0.00861 0.00224 -0.0552 0.6244 0.1332
-3.000 -0.0148 0.00852 0.00215 -0.0549 0.6185 0.1408
-2.750 0.0111 0.00845 0.00207 -0.0545 0.6124 0.1503
-2.500 0.0373 0.00834 0.00199 -0.0542 0.6071 0.1628
-2.250 0.0634 0.00823 0.00191 -0.0539 0.6015 0.1771
-2.000 0.0889 0.00815 0.00185 -0.0535 0.5961 0.1965
-1.750 0.1147 0.00800 0.00179 -0.0531 0.5907 0.2230
-1.500 0.1399 0.00785 0.00174 -0.0526 0.5852 0.2585
-1.250 0.1643 0.00772 0.00170 -0.0520 0.5799 0.2987
-1.000 0.1891 0.00752 0.00166 -0.0515 0.5748 0.3490
-0.750 0.2122 0.00728 0.00162 -0.0506 0.5695 0.4197
-0.500 0.2347 0.00708 0.00161 -0.0496 0.5644 0.4910
-0.250 0.2577 0.00685 0.00160 -0.0486 0.5597 0.5599
0.000 0.2793 0.00666 0.00160 -0.0473 0.5547 0.6288
0.250 0.2992 0.00649 0.00162 -0.0457 0.5498 0.6991
0.500 0.3194 0.00628 0.00165 -0.0439 0.5453 0.7690
0.750 0.3421 0.00612 0.00169 -0.0427 0.5400 0.8371
1.000 0.3817 0.00607 0.00178 -0.0453 0.5345 0.8965
1.250 0.4385 0.00611 0.00186 -0.0517 0.5289 0.9272
1.500 0.4901 0.00622 0.00194 -0.0570 0.5231 0.9412
1.750 0.5273 0.00635 0.00204 -0.0591 0.5179 0.9522
2.000 0.5586 0.00647 0.00215 -0.0598 0.5125 0.9627
2.250 0.5970 0.00666 0.00228 -0.0621 0.5066 0.9697
2.500 0.6301 0.00681 0.00242 -0.0632 0.5015 0.9771
2.750 0.6731 0.00694 0.00253 -0.0666 0.4958 0.9795
3.000 0.7142 0.00712 0.00265 -0.0696 0.4900 0.9834
3.250 0.7530 0.00725 0.00278 -0.0720 0.4844 0.9875
3.500 0.7938 0.00735 0.00286 -0.0750 0.4784 0.9893
3.750 0.8300 0.00746 0.00293 -0.0770 0.4729 0.9912
4.000 0.8662 0.00754 0.00301 -0.0790 0.4675 0.9935
4.250 0.9010 0.00766 0.00311 -0.0808 0.4618 0.9957
4.500 0.9375 0.00773 0.00317 -0.0829 0.4566 0.9975
4.750 0.9741 0.00779 0.00324 -0.0850 0.4509 0.9993
5.000 1.0031 0.00792 0.00333 -0.0856 0.4452 1.0000
5.250 1.0260 0.00799 0.00342 -0.0848 0.4406 1.0000
5.500 1.0484 0.00809 0.00353 -0.0839 0.4354 1.0000
5.750 1.0697 0.00824 0.00366 -0.0828 0.4302 1.0000
6.000 1.0925 0.00832 0.00377 -0.0820 0.4253 1.0000
6.250 1.1145 0.00845 0.00390 -0.0810 0.4197 1.0000
6.500 1.1354 0.00861 0.00406 -0.0798 0.4129 1.0000
6.750 1.1569 0.00875 0.00419 -0.0788 0.4042 1.0000
7.000 1.1775 0.00892 0.00435 -0.0776 0.3946 1.0000
7.250 1.1966 0.00916 0.00454 -0.0761 0.3843 1.0000
7.500 1.2151 0.00941 0.00475 -0.0745 0.3694 1.0000
7.750 1.2333 0.00967 0.00497 -0.0729 0.3557 1.0000
8.000 1.2502 0.00997 0.00522 -0.0710 0.3410 1.0000
8.250 1.2659 0.01030 0.00550 -0.0690 0.3256 1.0000
8.500 1.2811 0.01064 0.00579 -0.0668 0.3111 1.0000
8.750 1.2940 0.01104 0.00614 -0.0643 0.2937 1.0000
9.000 1.3000 0.01165 0.00661 -0.0606 0.2668 1.0000
9.250 1.2902 0.01252 0.00727 -0.0540 0.2279 1.0000
9.500 1.2858 0.01351 0.00809 -0.0489 0.1963 1.0000
9.750 1.2741 0.01518 0.00948 -0.0436 0.1491 1.0000
10.000 1.2683 0.01686 0.01095 -0.0398 0.1122 1.0000
10.250 1.2647 0.01863 0.01255 -0.0366 0.0806 1.0000
10.500 1.2587 0.02073 0.01448 -0.0337 0.0507 1.0000
10.750 1.2550 0.02285 0.01648 -0.0313 0.0291 1.0000
11.000 1.2546 0.02486 0.01845 -0.0294 0.0178 1.0000
11.250 1.2632 0.02627 0.01988 -0.0284 0.0156 1.0000
11.500 1.2701 0.02785 0.02150 -0.0273 0.0136 1.0000
11.750 1.2747 0.02967 0.02336 -0.0261 0.0119 1.0000
12.000 1.2834 0.03119 0.02493 -0.0254 0.0114 1.0000
12.250 1.2904 0.03289 0.02668 -0.0246 0.0105 1.0000
12.500 1.2959 0.03475 0.02860 -0.0238 0.0102 1.0000
12.750 1.2929 0.03748 0.03140 -0.0228 0.0090 1.0000
13.000 1.3000 0.03933 0.03331 -0.0223 0.0092 1.0000
13.250 1.3030 0.04162 0.03568 -0.0217 0.0086 1.0000
13.500 1.3092 0.04364 0.03775 -0.0213 0.0086 1.0000
13.750 1.3122 0.04602 0.04021 -0.0210 0.0081 1.0000
14.000 1.3129 0.04871 0.04296 -0.0206 0.0076 1.0000
14.250 1.3165 0.05111 0.04542 -0.0204 0.0076 1.0000
14.500 1.3164 0.05396 0.04834 -0.0202 0.0074 1.0000
14.750 1.3108 0.05751 0.05195 -0.0200 0.0068 1.0000
15.000 1.3099 0.06058 0.05510 -0.0200 0.0068 1.0000
15.250 1.3074 0.06388 0.05848 -0.0201 0.0065 1.0000
15.500 1.3044 0.06731 0.06200 -0.0202 0.0065 1.0000
15.750 1.3063 0.07018 0.06494 -0.0204 0.0064 1.0000
16.000 1.3000 0.07410 0.06895 -0.0207 0.0064 1.0000
16.250 1.3028 0.07690 0.07181 -0.0210 0.0064 1.0000
16.500 1.3065 0.07964 0.07461 -0.0214 0.0060 1.0000
16.750 1.3004 0.08369 0.07875 -0.0219 0.0060 1.0000
17.000 1.3011 0.08687 0.08199 -0.0224 0.0058 1.0000
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Polar data table (+)
Polar graphs
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