FX 79-L-120 (fx79l120-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 79-L-120 (fx79l120-il) Reynolds number: 500,000 Max Cl/Cd: 60.37 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx79l120-il-500000-n5.txt Download as CSV file: xf-fx79l120-il-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.500 -1.0220 0.14262 0.13979 0.0261 1.0000 0.0116
-18.250 -1.0597 0.12978 0.12679 0.0190 1.0000 0.0115
-18.000 -1.0921 0.11871 0.11555 0.0130 1.0000 0.0113
-17.750 -1.1254 0.10769 0.10437 0.0070 1.0000 0.0114
-17.500 -1.1481 0.09911 0.09564 0.0023 1.0000 0.0114
-17.250 -1.1737 0.09027 0.08663 -0.0024 1.0000 0.0113
-17.000 -1.1898 0.08328 0.07951 -0.0063 1.0000 0.0115
-16.750 -1.2055 0.07672 0.07281 -0.0099 1.0000 0.0116
-16.500 -1.2185 0.07084 0.06679 -0.0129 1.0000 0.0116
-16.250 -1.2296 0.06556 0.06138 -0.0156 1.0000 0.0118
-16.000 -1.2403 0.06065 0.05632 -0.0178 1.0000 0.0117
-15.750 -1.2481 0.05628 0.05183 -0.0197 1.0000 0.0119
-15.500 -1.2510 0.05268 0.04811 -0.0211 1.0000 0.0122
-15.250 -1.2561 0.04892 0.04423 -0.0225 1.0000 0.0122
-15.000 -1.2568 0.04580 0.04098 -0.0235 1.0000 0.0125
-14.750 -1.2590 0.04259 0.03764 -0.0243 1.0000 0.0125
-14.500 -1.2564 0.04000 0.03494 -0.0249 1.0000 0.0128
-14.250 -1.2528 0.03759 0.03240 -0.0253 1.0000 0.0130
-14.000 -1.2476 0.03542 0.03010 -0.0256 1.0000 0.0132
-13.750 -1.2438 0.03319 0.02777 -0.0257 1.0000 0.0136
-13.500 -1.2384 0.03122 0.02570 -0.0255 1.0000 0.0137
-13.250 -1.2301 0.02962 0.02403 -0.0252 1.0000 0.0140
-13.000 -1.2204 0.02824 0.02259 -0.0247 1.0000 0.0146
-12.750 -1.2106 0.02695 0.02121 -0.0239 1.0000 0.0149
-12.500 -1.1993 0.02588 0.02005 -0.0229 1.0000 0.0153
-12.250 -1.1890 0.02481 0.01889 -0.0215 1.0000 0.0158
-12.000 -1.1762 0.02398 0.01797 -0.0200 1.0000 0.0162
-11.750 -1.1637 0.02318 0.01707 -0.0183 1.0000 0.0166
-11.500 -1.1516 0.02224 0.01608 -0.0165 1.0000 0.0172
-11.250 -1.1360 0.02144 0.01524 -0.0151 1.0000 0.0178
-11.000 -1.1187 0.02076 0.01451 -0.0139 1.0000 0.0184
-10.750 -1.1004 0.02013 0.01382 -0.0128 1.0000 0.0191
-10.500 -1.0812 0.01955 0.01317 -0.0117 1.0000 0.0200
-10.250 -1.0614 0.01900 0.01255 -0.0107 1.0000 0.0207
-10.000 -1.0433 0.01829 0.01183 -0.0095 1.0000 0.0218
-9.750 -1.0232 0.01774 0.01125 -0.0085 1.0000 0.0227
-9.500 -1.0025 0.01723 0.01070 -0.0075 1.0000 0.0237
-9.250 -0.9814 0.01675 0.01016 -0.0065 1.0000 0.0248
-9.000 -0.9603 0.01626 0.00963 -0.0055 1.0000 0.0260
-8.750 -0.9392 0.01577 0.00914 -0.0045 1.0000 0.0274
-8.500 -0.9172 0.01535 0.00870 -0.0036 1.0000 0.0291
-8.250 -0.8951 0.01495 0.00825 -0.0027 1.0000 0.0305
-8.000 -0.8732 0.01452 0.00780 -0.0018 1.0000 0.0321
-7.750 -0.8512 0.01410 0.00739 -0.0008 1.0000 0.0341
-7.500 -0.8285 0.01375 0.00703 0.0000 1.0000 0.0364
-7.250 -0.8057 0.01342 0.00666 0.0009 1.0000 0.0383
-6.750 -0.7459 0.01263 0.00588 -0.0005 0.9712 0.0447
-6.500 -0.6941 0.01217 0.00541 -0.0060 0.9425 0.0498
-6.250 -0.6397 0.01180 0.00497 -0.0121 0.9092 0.0554
-6.000 -0.6027 0.01150 0.00460 -0.0142 0.8695 0.0628
-5.750 -0.5763 0.01135 0.00432 -0.0140 0.8378 0.0684
-5.500 -0.5525 0.01115 0.00406 -0.0132 0.8138 0.0770
-5.250 -0.5289 0.01093 0.00381 -0.0123 0.7933 0.0875
-5.000 -0.5054 0.01070 0.00357 -0.0114 0.7755 0.1015
-4.750 -0.4818 0.01046 0.00333 -0.0106 0.7606 0.1193
-4.500 -0.4584 0.01018 0.00310 -0.0098 0.7474 0.1426
-4.250 -0.4353 0.00986 0.00285 -0.0089 0.7350 0.1755
-4.000 -0.4121 0.00950 0.00263 -0.0081 0.7238 0.2144
-3.750 -0.3890 0.00913 0.00240 -0.0073 0.7141 0.2605
-3.500 -0.3664 0.00873 0.00218 -0.0063 0.7044 0.3168
-3.250 -0.3434 0.00837 0.00201 -0.0055 0.6954 0.3744
-3.000 -0.3194 0.00813 0.00190 -0.0047 0.6871 0.4191
-2.750 -0.2939 0.00798 0.00183 -0.0041 0.6793 0.4498
-2.500 -0.2682 0.00789 0.00176 -0.0036 0.6716 0.4756
-2.250 -0.2420 0.00781 0.00172 -0.0031 0.6642 0.4957
-2.000 -0.2159 0.00775 0.00168 -0.0026 0.6567 0.5165
-1.750 -0.1894 0.00771 0.00166 -0.0022 0.6501 0.5347
-1.500 -0.1627 0.00767 0.00163 -0.0018 0.6432 0.5490
-1.250 -0.1361 0.00766 0.00162 -0.0014 0.6371 0.5625
-1.000 -0.1088 0.00764 0.00160 -0.0011 0.6306 0.5739
-0.750 -0.0819 0.00763 0.00159 -0.0008 0.6237 0.5828
-0.500 -0.0546 0.00762 0.00158 -0.0005 0.6176 0.5908
-0.250 -0.0273 0.00761 0.00157 -0.0002 0.6113 0.5984
0.000 0.0000 0.00763 0.00157 0.0000 0.6052 0.6053
0.250 0.0274 0.00761 0.00157 0.0003 0.5984 0.6113
0.500 0.0546 0.00762 0.00158 0.0005 0.5909 0.6180
0.750 0.0819 0.00762 0.00159 0.0008 0.5831 0.6240
1.000 0.1088 0.00764 0.00160 0.0012 0.5736 0.6304
1.250 0.1361 0.00766 0.00162 0.0014 0.5625 0.6369
1.500 0.1627 0.00767 0.00163 0.0018 0.5491 0.6433
1.750 0.1894 0.00771 0.00165 0.0022 0.5334 0.6504
2.000 0.2159 0.00775 0.00168 0.0026 0.5160 0.6570
2.250 0.2421 0.00781 0.00172 0.0031 0.4961 0.6642
2.500 0.2682 0.00789 0.00176 0.0036 0.4751 0.6715
2.750 0.2941 0.00798 0.00183 0.0041 0.4506 0.6794
3.000 0.3195 0.00813 0.00190 0.0047 0.4199 0.6871
3.250 0.3435 0.00836 0.00201 0.0055 0.3748 0.6954
3.500 0.3666 0.00872 0.00218 0.0063 0.3183 0.7045
3.750 0.3890 0.00914 0.00240 0.0073 0.2602 0.7141
4.000 0.4120 0.00951 0.00263 0.0081 0.2139 0.7241
4.500 0.4583 0.01018 0.00310 0.0098 0.1422 0.7478
4.750 0.4818 0.01046 0.00333 0.0106 0.1195 0.7607
5.000 0.5055 0.01071 0.00357 0.0115 0.1011 0.7752
5.250 0.5290 0.01093 0.00381 0.0123 0.0878 0.7934
5.500 0.5526 0.01114 0.00406 0.0132 0.0774 0.8133
5.750 0.5764 0.01134 0.00432 0.0140 0.0689 0.8382
6.000 0.6029 0.01150 0.00460 0.0142 0.0626 0.8704
6.250 0.6401 0.01180 0.00498 0.0120 0.0556 0.9096
6.500 0.6944 0.01217 0.00541 0.0060 0.0496 0.9427
6.750 0.7460 0.01262 0.00587 0.0005 0.0444 0.9711
7.250 0.8056 0.01343 0.00666 -0.0009 0.0381 1.0000
7.500 0.8286 0.01375 0.00703 0.0000 0.0363 1.0000
7.750 0.8512 0.01410 0.00739 0.0009 0.0340 1.0000
8.000 0.8732 0.01452 0.00780 0.0018 0.0321 1.0000
8.250 0.8951 0.01496 0.00826 0.0028 0.0305 1.0000
8.500 0.9173 0.01535 0.00870 0.0037 0.0291 1.0000
8.750 0.9392 0.01578 0.00915 0.0046 0.0275 1.0000
9.000 0.9603 0.01627 0.00964 0.0055 0.0260 1.0000
9.250 0.9813 0.01677 0.01018 0.0065 0.0248 1.0000
9.500 1.0024 0.01725 0.01072 0.0075 0.0238 1.0000
9.750 1.0234 0.01774 0.01125 0.0084 0.0226 1.0000
10.000 1.0435 0.01828 0.01182 0.0094 0.0216 1.0000
10.250 1.0625 0.01892 0.01247 0.0106 0.0205 1.0000
10.500 1.0821 0.01949 0.01312 0.0116 0.0198 1.0000
10.750 1.1008 0.02012 0.01381 0.0128 0.0191 1.0000
11.000 1.1190 0.02077 0.01452 0.0139 0.0184 1.0000
11.250 1.1364 0.02145 0.01525 0.0151 0.0177 1.0000
11.500 1.1521 0.02223 0.01607 0.0164 0.0172 1.0000
11.750 1.1649 0.02314 0.01704 0.0181 0.0166 1.0000
12.000 1.1770 0.02398 0.01797 0.0199 0.0162 1.0000
12.250 1.1891 0.02486 0.01894 0.0215 0.0157 1.0000
12.500 1.2005 0.02585 0.02002 0.0228 0.0154 1.0000
12.750 1.2110 0.02699 0.02125 0.0239 0.0149 1.0000
13.000 1.2216 0.02821 0.02255 0.0246 0.0146 1.0000
13.250 1.2324 0.02951 0.02391 0.0251 0.0140 1.0000
13.500 1.2392 0.03125 0.02573 0.0254 0.0137 1.0000
13.750 1.2428 0.03342 0.02798 0.0255 0.0133 1.0000
14.000 1.2489 0.03544 0.03013 0.0254 0.0132 1.0000
14.250 1.2540 0.03761 0.03242 0.0252 0.0130 1.0000
14.500 1.2572 0.04008 0.03501 0.0247 0.0128 1.0000
14.750 1.2594 0.04271 0.03777 0.0241 0.0125 1.0000
15.000 1.2591 0.04572 0.04090 0.0232 0.0124 1.0000
15.250 1.2577 0.04893 0.04423 0.0222 0.0122 1.0000
15.500 1.2539 0.05255 0.04798 0.0209 0.0119 1.0000
15.750 1.2519 0.05604 0.05157 0.0195 0.0117 1.0000
16.000 1.2432 0.06052 0.05619 0.0176 0.0117 1.0000
16.250 1.2336 0.06529 0.06110 0.0153 0.0116 1.0000
16.500 1.2200 0.07090 0.06686 0.0126 0.0117 1.0000
16.750 1.2071 0.07681 0.07290 0.0095 0.0116 1.0000
17.000 1.1935 0.08306 0.07929 0.0061 0.0115 1.0000
17.250 1.1747 0.09051 0.08687 0.0020 0.0113 1.0000
17.500 1.1521 0.09880 0.09533 -0.0025 0.0114 1.0000
17.750 1.1249 0.10824 0.10493 -0.0077 0.0114 1.0000
18.000 1.0961 0.11839 0.11523 -0.0132 0.0114 1.0000
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