FX 79-L-100 (fx79l100-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 79-L-100 (fx79l100-il) Reynolds number: 1,000,000 Max Cl/Cd: 72.67 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx79l100-il-1000000-n5.txt Download as CSV file: xf-fx79l100-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 79-L-100
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.500 -1.0284 0.14035 0.13835 0.0352 1.0000 0.0055
-17.250 -1.0925 0.12165 0.11950 0.0252 1.0000 0.0053
-17.000 -1.1883 0.09708 0.09468 0.0119 1.0000 0.0053
-16.750 -1.2433 0.08155 0.07892 0.0030 1.0000 0.0052
-16.500 -1.2644 0.07339 0.07063 -0.0019 1.0000 0.0052
-16.250 -1.2994 0.06339 0.06042 -0.0079 1.0000 0.0052
-16.000 -1.3320 0.05463 0.05145 -0.0131 1.0000 0.0051
-15.750 -1.3386 0.05026 0.04695 -0.0153 1.0000 0.0051
-15.500 -1.3436 0.04629 0.04286 -0.0172 1.0000 0.0052
-15.250 -1.3506 0.04221 0.03864 -0.0191 1.0000 0.0052
-15.000 -1.3551 0.03868 0.03496 -0.0203 1.0000 0.0052
-14.750 -1.3541 0.03600 0.03215 -0.0210 1.0000 0.0053
-14.500 -1.3463 0.03421 0.03028 -0.0212 1.0000 0.0054
-14.250 -1.3448 0.03193 0.02786 -0.0211 1.0000 0.0054
-14.000 -1.3417 0.03006 0.02587 -0.0204 1.0000 0.0054
-13.750 -1.3405 0.02822 0.02390 -0.0189 1.0000 0.0055
-13.500 -1.3376 0.02667 0.02221 -0.0168 1.0000 0.0057
-13.250 -1.3288 0.02543 0.02086 -0.0150 1.0000 0.0058
-13.000 -1.3148 0.02433 0.01966 -0.0139 1.0000 0.0059
-12.750 -1.2998 0.02329 0.01854 -0.0127 1.0000 0.0061
-12.500 -1.2824 0.02244 0.01762 -0.0118 1.0000 0.0063
-12.250 -1.2641 0.02163 0.01673 -0.0109 1.0000 0.0064
-12.000 -1.2456 0.02080 0.01581 -0.0099 1.0000 0.0066
-11.750 -1.2257 0.02009 0.01504 -0.0092 1.0000 0.0068
-11.500 -1.2055 0.01940 0.01427 -0.0084 1.0000 0.0070
-11.250 -1.1853 0.01865 0.01344 -0.0075 1.0000 0.0072
-11.000 -1.1642 0.01801 0.01272 -0.0068 1.0000 0.0074
-10.750 -1.1426 0.01740 0.01204 -0.0060 1.0000 0.0075
-10.500 -1.1205 0.01684 0.01142 -0.0053 1.0000 0.0078
-10.250 -1.0990 0.01619 0.01070 -0.0046 1.0000 0.0082
-10.000 -1.0769 0.01560 0.01007 -0.0038 1.0000 0.0086
-9.750 -1.0539 0.01512 0.00956 -0.0032 1.0000 0.0092
-9.500 -1.0307 0.01467 0.00907 -0.0026 1.0000 0.0096
-9.250 -1.0072 0.01424 0.00859 -0.0020 1.0000 0.0101
-9.000 -0.9834 0.01385 0.00816 -0.0014 1.0000 0.0106
-8.750 -0.9602 0.01339 0.00766 -0.0007 1.0000 0.0113
-8.500 -0.9366 0.01296 0.00722 0.0000 1.0000 0.0122
-8.250 -0.9127 0.01259 0.00682 0.0006 1.0000 0.0129
-8.000 -0.8885 0.01226 0.00646 0.0012 1.0000 0.0138
-7.750 -0.8642 0.01193 0.00610 0.0018 1.0000 0.0143
-7.500 -0.8402 0.01157 0.00573 0.0025 1.0000 0.0153
-7.250 -0.8162 0.01124 0.00539 0.0031 1.0000 0.0167
-7.000 -0.7918 0.01095 0.00509 0.0037 1.0000 0.0177
-6.750 -0.7673 0.01069 0.00481 0.0044 1.0000 0.0188
-6.500 -0.7431 0.01037 0.00448 0.0051 0.9894 0.0206
-6.250 -0.7048 0.01005 0.00418 0.0026 0.9707 0.0230
-6.000 -0.6527 0.00975 0.00385 -0.0030 0.9509 0.0261
-5.750 -0.5932 0.00941 0.00349 -0.0103 0.9209 0.0306
-5.500 -0.5522 0.00928 0.00321 -0.0134 0.8732 0.0341
-5.250 -0.5268 0.00918 0.00300 -0.0128 0.8353 0.0389
-5.000 -0.5024 0.00910 0.00282 -0.0121 0.8086 0.0419
-4.750 -0.4781 0.00895 0.00263 -0.0113 0.7873 0.0484
-4.500 -0.4534 0.00883 0.00245 -0.0106 0.7689 0.0543
-4.250 -0.4288 0.00868 0.00229 -0.0099 0.7518 0.0633
-4.000 -0.4040 0.00853 0.00213 -0.0092 0.7359 0.0747
-3.750 -0.3791 0.00837 0.00197 -0.0086 0.7218 0.0899
-3.500 -0.3541 0.00819 0.00182 -0.0080 0.7095 0.1079
-3.250 -0.3293 0.00799 0.00167 -0.0073 0.6983 0.1338
-3.000 -0.3053 0.00770 0.00151 -0.0066 0.6880 0.1752
-2.750 -0.2811 0.00740 0.00136 -0.0059 0.6784 0.2237
-2.500 -0.2573 0.00708 0.00121 -0.0051 0.6694 0.2788
-2.250 -0.2333 0.00678 0.00109 -0.0044 0.6605 0.3341
-2.000 -0.2094 0.00648 0.00098 -0.0036 0.6524 0.3950
-1.750 -0.1840 0.00634 0.00092 -0.0031 0.6442 0.4314
-1.500 -0.1586 0.00618 0.00087 -0.0025 0.6367 0.4702
-1.250 -0.1325 0.00610 0.00084 -0.0020 0.6287 0.4953
-1.000 -0.1064 0.00601 0.00082 -0.0016 0.6212 0.5225
-0.750 -0.0801 0.00596 0.00081 -0.0011 0.6135 0.5432
-0.500 -0.0532 0.00593 0.00080 -0.0008 0.6059 0.5569
0.000 0.0000 0.00590 0.00080 0.0000 0.5863 0.5860
0.250 0.0269 0.00591 0.00080 0.0003 0.5751 0.5962
0.500 0.0534 0.00592 0.00081 0.0007 0.5606 0.6056
0.750 0.0800 0.00597 0.00081 0.0011 0.5423 0.6135
1.000 0.1061 0.00602 0.00082 0.0016 0.5202 0.6215
1.250 0.1325 0.00610 0.00084 0.0020 0.4953 0.6287
1.500 0.1585 0.00618 0.00087 0.0025 0.4684 0.6366
1.750 0.1839 0.00634 0.00092 0.0031 0.4295 0.6442
2.000 0.2092 0.00649 0.00098 0.0036 0.3936 0.6527
2.250 0.2334 0.00677 0.00108 0.0043 0.3367 0.6604
2.500 0.2571 0.00710 0.00122 0.0051 0.2755 0.6693
2.750 0.2810 0.00740 0.00136 0.0059 0.2224 0.6783
3.000 0.3051 0.00771 0.00152 0.0066 0.1736 0.6881
3.250 0.3297 0.00793 0.00166 0.0073 0.1413 0.6990
3.500 0.3541 0.00817 0.00181 0.0079 0.1102 0.7101
3.750 0.3790 0.00837 0.00197 0.0086 0.0894 0.7220
4.000 0.4039 0.00854 0.00213 0.0092 0.0734 0.7356
4.250 0.4287 0.00869 0.00229 0.0099 0.0632 0.7512
4.500 0.4534 0.00883 0.00245 0.0106 0.0545 0.7681
4.750 0.4781 0.00894 0.00262 0.0113 0.0488 0.7872
5.000 0.5023 0.00909 0.00282 0.0121 0.0423 0.8093
5.250 0.5267 0.00917 0.00301 0.0129 0.0391 0.8378
5.500 0.5523 0.00927 0.00321 0.0133 0.0352 0.8738
5.750 0.5911 0.00941 0.00348 0.0108 0.0307 0.9182
6.000 0.6522 0.00975 0.00385 0.0031 0.0257 0.9507
6.250 0.7045 0.01004 0.00417 -0.0025 0.0232 0.9702
6.500 0.7430 0.01036 0.00448 -0.0051 0.0207 0.9894
6.750 0.7673 0.01069 0.00480 -0.0044 0.0189 1.0000
7.000 0.7918 0.01094 0.00508 -0.0038 0.0176 1.0000
7.250 0.8161 0.01123 0.00538 -0.0031 0.0165 1.0000
7.500 0.8401 0.01157 0.00571 -0.0025 0.0152 1.0000
7.750 0.8642 0.01191 0.00609 -0.0018 0.0141 1.0000
8.000 0.8885 0.01223 0.00643 -0.0012 0.0134 1.0000
8.250 0.9127 0.01257 0.00680 -0.0006 0.0127 1.0000
8.500 0.9364 0.01297 0.00721 0.0000 0.0118 1.0000
8.750 0.9597 0.01343 0.00769 0.0007 0.0109 1.0000
9.000 0.9833 0.01385 0.00817 0.0014 0.0104 1.0000
9.250 1.0069 0.01426 0.00861 0.0020 0.0100 1.0000
9.500 1.0304 0.01468 0.00908 0.0026 0.0094 1.0000
9.750 1.0536 0.01514 0.00957 0.0032 0.0090 1.0000
10.000 1.0763 0.01566 0.01013 0.0039 0.0085 1.0000
10.250 1.0984 0.01624 0.01075 0.0046 0.0080 1.0000
10.500 1.1198 0.01690 0.01148 0.0054 0.0078 1.0000
10.750 1.1414 0.01754 0.01219 0.0062 0.0076 1.0000
11.000 1.1633 0.01810 0.01281 0.0069 0.0075 1.0000
11.250 1.1846 0.01871 0.01350 0.0076 0.0072 1.0000
11.500 1.2049 0.01944 0.01431 0.0084 0.0070 1.0000
11.750 1.2252 0.02012 0.01507 0.0092 0.0068 1.0000
12.000 1.2446 0.02089 0.01592 0.0101 0.0067 1.0000
12.250 1.2634 0.02168 0.01679 0.0110 0.0065 1.0000
12.500 1.2810 0.02256 0.01775 0.0119 0.0064 1.0000
12.750 1.2978 0.02346 0.01874 0.0129 0.0062 1.0000
13.000 1.3130 0.02447 0.01984 0.0140 0.0061 1.0000
13.250 1.3269 0.02558 0.02104 0.0152 0.0060 1.0000
13.500 1.3372 0.02668 0.02222 0.0169 0.0058 1.0000
13.750 1.3384 0.02838 0.02406 0.0191 0.0055 1.0000
14.000 1.3411 0.03009 0.02590 0.0204 0.0055 1.0000
14.250 1.3437 0.03204 0.02797 0.0210 0.0054 1.0000
14.500 1.3456 0.03428 0.03035 0.0211 0.0054 1.0000
14.750 1.3480 0.03668 0.03286 0.0207 0.0054 1.0000
15.000 1.3463 0.03976 0.03608 0.0198 0.0053 1.0000
15.250 1.3431 0.04320 0.03966 0.0184 0.0053 1.0000
15.500 1.3348 0.04755 0.04415 0.0164 0.0053 1.0000
15.750 1.3301 0.05155 0.04828 0.0144 0.0053 1.0000
16.000 1.3098 0.05814 0.05505 0.0107 0.0053 1.0000
16.250 1.2854 0.06588 0.06296 0.0061 0.0053 1.0000
16.500 1.2565 0.07501 0.07227 0.0006 0.0053 1.0000
16.750 1.2150 0.08739 0.08485 -0.0069 0.0053 1.0000
17.000 1.1754 0.09998 0.09761 -0.0139 0.0053 1.0000
17.250 1.0939 0.12155 0.11939 -0.0254 0.0055 1.0000
17.500 1.0301 0.14029 0.13831 -0.0354 0.0058 1.0000
18.000 0.8249 0.21770 0.21600 -0.0716 0.0041 1.0000
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