FX 79-L-100 (fx79l100-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 79-L-100 (fx79l100-il) Reynolds number: 500,000 Max Cl/Cd: 57.95 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx79l100-il-500000.txt Download as CSV file: xf-fx79l100-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.8806 0.09620 0.09383 0.0085 1.0000 0.0146
-13.250 -0.8907 0.08797 0.08548 0.0029 1.0000 0.0144
-13.000 -0.9333 0.07434 0.07172 -0.0067 1.0000 0.0140
-12.750 -0.9665 0.06409 0.06127 -0.0143 1.0000 0.0139
-12.500 -0.9848 0.05760 0.05458 -0.0190 1.0000 0.0140
-12.250 -0.9996 0.05237 0.04914 -0.0224 1.0000 0.0141
-12.000 -1.0229 0.04657 0.04310 -0.0246 1.0000 0.0139
-11.750 -1.0342 0.04308 0.03937 -0.0249 1.0000 0.0141
-11.500 -1.0420 0.04033 0.03639 -0.0237 1.0000 0.0142
-11.250 -1.0544 0.03658 0.03233 -0.0211 1.0000 0.0141
-11.000 -1.0496 0.03444 0.02994 -0.0195 1.0000 0.0143
-10.750 -1.0403 0.03267 0.02793 -0.0181 1.0000 0.0144
-10.500 -1.0433 0.02798 0.02282 -0.0157 1.0000 0.0150
-10.250 -1.0281 0.02653 0.02126 -0.0146 1.0000 0.0154
-10.000 -1.0113 0.02522 0.01984 -0.0135 1.0000 0.0158
-9.750 -0.9920 0.02445 0.01900 -0.0126 1.0000 0.0166
-9.500 -0.9726 0.02350 0.01794 -0.0117 1.0000 0.0174
-9.250 -0.9528 0.02248 0.01677 -0.0106 1.0000 0.0182
-9.000 -0.9323 0.02153 0.01567 -0.0097 1.0000 0.0188
-8.750 -0.9158 0.01967 0.01364 -0.0082 1.0000 0.0198
-8.500 -0.8960 0.01868 0.01262 -0.0072 1.0000 0.0210
-8.250 -0.8746 0.01795 0.01184 -0.0062 1.0000 0.0221
-8.000 -0.8521 0.01738 0.01121 -0.0054 1.0000 0.0235
-7.750 -0.8296 0.01679 0.01054 -0.0045 1.0000 0.0246
-7.500 -0.8108 0.01566 0.00931 -0.0031 1.0000 0.0262
-7.250 -0.7885 0.01514 0.00881 -0.0023 1.0000 0.0285
-7.000 -0.7656 0.01467 0.00830 -0.0015 1.0000 0.0304
-6.750 -0.7417 0.01431 0.00789 -0.0007 1.0000 0.0322
-6.500 -0.7226 0.01336 0.00689 0.0008 1.0000 0.0351
-6.250 -0.6998 0.01293 0.00646 0.0016 1.0000 0.0378
-6.000 -0.6764 0.01255 0.00605 0.0025 1.0000 0.0408
-5.750 -0.6552 0.01194 0.00540 0.0037 1.0000 0.0446
-5.500 -0.6325 0.01154 0.00502 0.0047 1.0000 0.0496
-5.250 -0.6092 0.01121 0.00465 0.0056 1.0000 0.0538
-5.000 -0.5877 0.01073 0.00421 0.0068 1.0000 0.0619
-4.750 -0.5656 0.01036 0.00387 0.0079 1.0000 0.0712
-4.500 -0.5441 0.00998 0.00356 0.0091 1.0000 0.0850
-4.250 -0.5236 0.00958 0.00327 0.0105 1.0000 0.1077
-4.000 -0.4872 0.00884 0.00287 0.0081 0.9872 0.1745
-3.750 -0.4520 0.00797 0.00249 0.0059 0.9731 0.2851
-3.500 -0.4132 0.00716 0.00221 0.0030 0.9573 0.4184
-3.250 -0.3676 0.00682 0.00210 -0.0010 0.9374 0.4914
-3.000 -0.3220 0.00669 0.00200 -0.0049 0.9104 0.5302
-2.750 -0.2866 0.00668 0.00192 -0.0064 0.8795 0.5541
-2.500 -0.2583 0.00670 0.00187 -0.0062 0.8518 0.5727
-2.250 -0.2322 0.00673 0.00182 -0.0057 0.8282 0.5883
-2.000 -0.2066 0.00676 0.00179 -0.0049 0.8086 0.6040
-1.750 -0.1812 0.00678 0.00176 -0.0042 0.7913 0.6187
-1.500 -0.1559 0.00680 0.00175 -0.0035 0.7759 0.6350
-1.250 -0.1303 0.00682 0.00173 -0.0028 0.7621 0.6487
-1.000 -0.1047 0.00684 0.00172 -0.0021 0.7496 0.6624
-0.750 -0.0787 0.00685 0.00171 -0.0015 0.7375 0.6745
-0.500 -0.0526 0.00685 0.00171 -0.0010 0.7265 0.6856
-0.250 -0.0264 0.00685 0.00170 -0.0005 0.7163 0.6955
0.000 0.0000 0.00685 0.00169 0.0000 0.7060 0.7060
0.250 0.0263 0.00685 0.00170 0.0005 0.6958 0.7165
0.500 0.0525 0.00685 0.00171 0.0010 0.6857 0.7265
0.750 0.0786 0.00685 0.00171 0.0015 0.6746 0.7376
1.000 0.1046 0.00684 0.00172 0.0021 0.6627 0.7496
1.250 0.1303 0.00682 0.00174 0.0028 0.6489 0.7622
1.500 0.1558 0.00680 0.00174 0.0035 0.6341 0.7757
1.750 0.1812 0.00678 0.00176 0.0042 0.6189 0.7911
2.000 0.2066 0.00676 0.00178 0.0049 0.6038 0.8084
2.250 0.2321 0.00673 0.00182 0.0056 0.5883 0.8283
2.500 0.2582 0.00670 0.00187 0.0062 0.5728 0.8519
2.750 0.2867 0.00667 0.00192 0.0063 0.5551 0.8798
3.000 0.3220 0.00669 0.00200 0.0049 0.5299 0.9107
3.250 0.3674 0.00683 0.00209 0.0011 0.4896 0.9373
3.500 0.4132 0.00713 0.00221 -0.0030 0.4224 0.9570
3.750 0.4521 0.00794 0.00248 -0.0059 0.2888 0.9729
4.000 0.4871 0.00885 0.00287 -0.0081 0.1728 0.9873
4.250 0.5236 0.00959 0.00327 -0.0105 0.1074 1.0000
4.500 0.5440 0.00998 0.00356 -0.0091 0.0845 1.0000
4.750 0.5656 0.01035 0.00387 -0.0080 0.0718 1.0000
5.000 0.5876 0.01074 0.00423 -0.0068 0.0621 1.0000
5.250 0.6093 0.01120 0.00464 -0.0057 0.0542 1.0000
5.500 0.6322 0.01156 0.00505 -0.0047 0.0499 1.0000
5.750 0.6551 0.01195 0.00543 -0.0037 0.0453 1.0000
6.000 0.6760 0.01259 0.00608 -0.0025 0.0411 1.0000
6.250 0.6999 0.01289 0.00642 -0.0017 0.0381 1.0000
6.500 0.7230 0.01329 0.00681 -0.0009 0.0349 1.0000
6.750 0.7424 0.01420 0.00777 0.0005 0.0322 1.0000
7.000 0.7661 0.01458 0.00821 0.0013 0.0301 1.0000
7.250 0.7890 0.01504 0.00870 0.0022 0.0282 1.0000
7.500 0.8106 0.01567 0.00932 0.0031 0.0261 1.0000
7.750 0.8305 0.01662 0.01036 0.0044 0.0243 1.0000
8.000 0.8529 0.01722 0.01104 0.0053 0.0229 1.0000
8.250 0.8750 0.01784 0.01171 0.0061 0.0216 1.0000
8.500 0.8962 0.01857 0.01248 0.0071 0.0206 1.0000
8.750 0.9135 0.02008 0.01406 0.0084 0.0194 1.0000
9.000 0.9317 0.02164 0.01579 0.0098 0.0187 1.0000
9.250 0.9522 0.02258 0.01689 0.0107 0.0181 1.0000
9.500 0.9718 0.02367 0.01812 0.0118 0.0173 1.0000
9.750 0.9908 0.02471 0.01929 0.0128 0.0167 1.0000
10.000 1.0084 0.02597 0.02068 0.0139 0.0161 1.0000
10.250 1.0273 0.02666 0.02141 0.0147 0.0155 1.0000
10.500 1.0423 0.02817 0.02304 0.0159 0.0151 1.0000
10.750 1.0506 0.03083 0.02593 0.0175 0.0148 1.0000
11.250 1.0502 0.03727 0.03305 0.0213 0.0142 1.0000
11.500 1.0430 0.04014 0.03621 0.0237 0.0141 1.0000
11.750 1.0343 0.04304 0.03933 0.0249 0.0141 1.0000
12.000 1.0199 0.04704 0.04357 0.0245 0.0141 1.0000
12.250 1.0012 0.05218 0.04893 0.0224 0.0141 1.0000
12.500 0.9793 0.05850 0.05548 0.0186 0.0142 1.0000
12.750 0.9573 0.06570 0.06288 0.0134 0.0142 1.0000
13.000 0.9228 0.07614 0.07348 0.0059 0.0144 1.0000
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