FX 79-L-120 (fx79l120-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 79-L-120 (fx79l120-il) Reynolds number: 500,000 Max Cl/Cd: 58.71 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx79l120-il-500000.txt Download as CSV file: xf-fx79l120-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: FX 79-L-120
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
------ -------- --------- --------- -------- -------- --------
-16.750 -1.0502 0.10248 0.09943 0.0008 1.0000 0.0169
-16.500 -1.0729 0.09353 0.09030 -0.0048 1.0000 0.0169
-16.250 -1.0987 0.08467 0.08125 -0.0102 1.0000 0.0169
-16.000 -1.1123 0.07836 0.07478 -0.0140 1.0000 0.0168
-15.750 -1.1324 0.07153 0.06777 -0.0177 1.0000 0.0169
-15.500 -1.1534 0.06513 0.06121 -0.0207 1.0000 0.0172
-15.250 -1.1654 0.06017 0.05607 -0.0229 1.0000 0.0171
-15.000 -1.1721 0.05617 0.05198 -0.0244 1.0000 0.0174
-14.750 -1.1824 0.05175 0.04737 -0.0258 1.0000 0.0174
-14.500 -1.1835 0.04868 0.04421 -0.0268 1.0000 0.0176
-14.250 -1.1815 0.04608 0.04154 -0.0276 1.0000 0.0180
-14.000 -1.1821 0.04319 0.03853 -0.0282 1.0000 0.0183
-13.750 -1.1786 0.04090 0.03615 -0.0287 1.0000 0.0187
-13.500 -1.1762 0.03847 0.03357 -0.0287 1.0000 0.0188
-13.250 -1.1710 0.03651 0.03149 -0.0287 1.0000 0.0193
-13.000 -1.1660 0.03453 0.02937 -0.0284 1.0000 0.0197
-12.750 -1.1599 0.03270 0.02740 -0.0278 1.0000 0.0201
-12.500 -1.1510 0.03135 0.02591 -0.0271 1.0000 0.0205
-12.250 -1.1464 0.02929 0.02368 -0.0257 1.0000 0.0210
-12.000 -1.1389 0.02774 0.02207 -0.0243 1.0000 0.0217
-11.750 -1.1277 0.02680 0.02110 -0.0229 1.0000 0.0223
-11.500 -1.1161 0.02585 0.02009 -0.0211 1.0000 0.0229
-11.250 -1.1029 0.02506 0.01923 -0.0195 1.0000 0.0236
-11.000 -1.0875 0.02418 0.01825 -0.0181 1.0000 0.0245
-10.750 -1.0708 0.02336 0.01733 -0.0168 1.0000 0.0251
-10.500 -1.0571 0.02209 0.01597 -0.0152 1.0000 0.0261
-10.250 -1.0410 0.02117 0.01504 -0.0139 1.0000 0.0271
-10.000 -1.0220 0.02057 0.01442 -0.0128 1.0000 0.0283
-9.750 -1.0022 0.01999 0.01379 -0.0118 1.0000 0.0295
-9.500 -0.9820 0.01940 0.01310 -0.0107 1.0000 0.0306
-9.250 -0.9653 0.01841 0.01206 -0.0092 1.0000 0.0319
-9.000 -0.9471 0.01765 0.01130 -0.0079 1.0000 0.0335
-8.750 -0.9260 0.01715 0.01079 -0.0069 1.0000 0.0351
-8.500 -0.9040 0.01673 0.01032 -0.0060 1.0000 0.0370
-8.250 -0.8848 0.01602 0.00955 -0.0047 1.0000 0.0388
-8.000 -0.8653 0.01536 0.00891 -0.0034 1.0000 0.0411
-7.750 -0.8435 0.01492 0.00845 -0.0024 1.0000 0.0435
-7.500 -0.8203 0.01462 0.00810 -0.0016 1.0000 0.0457
-7.250 -0.8017 0.01387 0.00736 -0.0001 1.0000 0.0491
-7.000 -0.7795 0.01348 0.00698 0.0009 1.0000 0.0524
-6.750 -0.7565 0.01319 0.00664 0.0018 1.0000 0.0552
-6.500 -0.7368 0.01259 0.00608 0.0031 1.0000 0.0602
-6.250 -0.7146 0.01225 0.00574 0.0042 1.0000 0.0645
-6.000 -0.6940 0.01182 0.00532 0.0055 1.0000 0.0704
-5.500 -0.6337 0.01095 0.00455 0.0040 0.9823 0.0900
-5.250 -0.5917 0.01040 0.00412 0.0006 0.9644 0.1135
-5.000 -0.5431 0.00970 0.00366 -0.0044 0.9439 0.1643
-4.750 -0.4971 0.00886 0.00316 -0.0090 0.9138 0.2480
-4.500 -0.4667 0.00823 0.00280 -0.0100 0.8782 0.3361
-4.250 -0.4436 0.00786 0.00261 -0.0091 0.8490 0.4069
-4.000 -0.4202 0.00771 0.00250 -0.0081 0.8260 0.4499
-3.750 -0.3956 0.00764 0.00242 -0.0073 0.8072 0.4791
-3.500 -0.3707 0.00760 0.00236 -0.0065 0.7909 0.5022
-3.250 -0.3453 0.00759 0.00230 -0.0058 0.7768 0.5211
-3.000 -0.3195 0.00759 0.00225 -0.0052 0.7645 0.5372
-2.750 -0.2935 0.00759 0.00221 -0.0046 0.7531 0.5505
-2.500 -0.2673 0.00758 0.00218 -0.0041 0.7422 0.5633
-2.250 -0.2409 0.00760 0.00214 -0.0036 0.7327 0.5752
-2.000 -0.2145 0.00762 0.00213 -0.0031 0.7231 0.5881
-1.750 -0.1882 0.00762 0.00213 -0.0026 0.7145 0.5999
-1.500 -0.1616 0.00762 0.00212 -0.0021 0.7062 0.6104
-1.250 -0.1349 0.00766 0.00211 -0.0017 0.6985 0.6213
-1.000 -0.1083 0.00764 0.00211 -0.0013 0.6905 0.6305
-0.750 -0.0813 0.00766 0.00210 -0.0010 0.6831 0.6390
-0.500 -0.0543 0.00764 0.00210 -0.0006 0.6756 0.6467
-0.250 -0.0271 0.00768 0.00208 -0.0003 0.6690 0.6546
0.000 0.0000 0.00764 0.00209 0.0000 0.6615 0.6616
0.250 0.0272 0.00768 0.00208 0.0003 0.6546 0.6690
0.500 0.0543 0.00764 0.00210 0.0006 0.6468 0.6758
0.750 0.0813 0.00766 0.00210 0.0010 0.6391 0.6834
1.000 0.1083 0.00764 0.00211 0.0013 0.6304 0.6905
1.250 0.1350 0.00766 0.00211 0.0017 0.6214 0.6983
1.500 0.1617 0.00762 0.00212 0.0022 0.6105 0.7062
1.750 0.1882 0.00761 0.00212 0.0026 0.5993 0.7147
2.000 0.2145 0.00762 0.00213 0.0031 0.5879 0.7233
2.250 0.2409 0.00760 0.00214 0.0036 0.5753 0.7328
2.500 0.2673 0.00758 0.00217 0.0041 0.5631 0.7422
2.750 0.2936 0.00759 0.00221 0.0046 0.5508 0.7531
3.000 0.3195 0.00759 0.00225 0.0052 0.5373 0.7646
3.250 0.3453 0.00759 0.00230 0.0058 0.5212 0.7768
3.500 0.3708 0.00760 0.00236 0.0065 0.5024 0.7910
3.750 0.3957 0.00764 0.00242 0.0073 0.4789 0.8072
4.000 0.4201 0.00771 0.00250 0.0081 0.4495 0.8262
4.250 0.4435 0.00787 0.00260 0.0091 0.4049 0.8493
4.500 0.4667 0.00823 0.00280 0.0100 0.3357 0.8787
4.750 0.4973 0.00885 0.00316 0.0090 0.2484 0.9140
5.000 0.5430 0.00970 0.00366 0.0045 0.1638 0.9437
5.250 0.5918 0.01039 0.00412 -0.0006 0.1139 0.9644
5.500 0.6337 0.01095 0.00454 -0.0040 0.0903 0.9823
6.000 0.6940 0.01182 0.00532 -0.0054 0.0702 1.0000
6.250 0.7148 0.01224 0.00573 -0.0042 0.0644 1.0000
6.500 0.7368 0.01259 0.00607 -0.0031 0.0599 1.0000
6.750 0.7568 0.01316 0.00662 -0.0018 0.0550 1.0000
7.000 0.7796 0.01348 0.00697 -0.0009 0.0522 1.0000
7.250 0.8018 0.01387 0.00736 0.0001 0.0490 1.0000
7.500 0.8204 0.01461 0.00809 0.0016 0.0456 1.0000
7.750 0.8436 0.01493 0.00846 0.0024 0.0434 1.0000
8.000 0.8654 0.01536 0.00891 0.0034 0.0412 1.0000
8.250 0.8849 0.01602 0.00955 0.0047 0.0389 1.0000
8.500 0.9041 0.01673 0.01032 0.0060 0.0370 1.0000
8.750 0.9259 0.01718 0.01082 0.0069 0.0352 1.0000
9.000 0.9471 0.01765 0.01130 0.0079 0.0334 1.0000
9.250 0.9654 0.01842 0.01207 0.0092 0.0319 1.0000
9.500 0.9821 0.01942 0.01312 0.0107 0.0306 1.0000
9.750 1.0031 0.01989 0.01368 0.0116 0.0293 1.0000
10.000 1.0228 0.02048 0.01432 0.0127 0.0281 1.0000
10.250 1.0419 0.02109 0.01495 0.0137 0.0270 1.0000
10.500 1.0571 0.02211 0.01598 0.0152 0.0260 1.0000
10.750 1.0708 0.02341 0.01737 0.0168 0.0251 1.0000
11.000 1.0878 0.02419 0.01827 0.0181 0.0244 1.0000
11.250 1.1033 0.02507 0.01924 0.0194 0.0237 1.0000
11.500 1.1160 0.02599 0.02025 0.0211 0.0230 1.0000
11.750 1.1291 0.02665 0.02093 0.0227 0.0222 1.0000
12.000 1.1394 0.02781 0.02215 0.0242 0.0217 1.0000
12.250 1.1446 0.02972 0.02413 0.0258 0.0209 1.0000
12.500 1.1526 0.03127 0.02581 0.0269 0.0205 1.0000
12.750 1.1604 0.03276 0.02746 0.0277 0.0201 1.0000
13.000 1.1674 0.03449 0.02933 0.0282 0.0198 1.0000
13.250 1.1733 0.03630 0.03127 0.0285 0.0191 1.0000
13.500 1.1776 0.03841 0.03351 0.0285 0.0187 1.0000
13.750 1.1801 0.04084 0.03607 0.0284 0.0184 1.0000
14.000 1.1816 0.04343 0.03878 0.0281 0.0182 1.0000
14.250 1.1831 0.04606 0.04151 0.0274 0.0179 1.0000
14.500 1.1816 0.04913 0.04470 0.0266 0.0177 1.0000
14.750 1.1826 0.05193 0.04756 0.0256 0.0174 1.0000
15.000 1.1756 0.05591 0.05170 0.0242 0.0173 1.0000
15.250 1.1667 0.06024 0.05614 0.0226 0.0171 1.0000
15.500 1.1473 0.06620 0.06228 0.0201 0.0169 1.0000
15.750 1.1244 0.07308 0.06936 0.0166 0.0167 1.0000
16.000 1.1115 0.07885 0.07528 0.0135 0.0168 1.0000
16.250 1.0925 0.08606 0.08267 0.0092 0.0168 1.0000
16.500 1.0785 0.09297 0.08974 0.0048 0.0170 1.0000
16.750 1.0481 0.10355 0.10053 -0.0019 0.0171 1.0000
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Polar data table (+)
Polar graphs
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