FX 71-L-150/20 AIRFOIL (fx711520-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 71-L-150/20 AIRFOIL (fx711520-il) Reynolds number: 500,000 Max Cl/Cd: 49.13 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx711520-il-500000.txt Download as CSV file: xf-fx711520-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: FX 71-L-150/20 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-17.500 -0.9087 0.13192 0.12901 0.0107 1.0000 0.0204
-17.250 -0.9111 0.12704 0.12413 0.0083 1.0000 0.0202
-17.000 -0.9431 0.11521 0.11214 0.0007 1.0000 0.0200
-16.750 -0.9757 0.10408 0.10080 -0.0065 1.0000 0.0198
-16.500 -0.9999 0.09541 0.09197 -0.0117 1.0000 0.0196
-16.250 -1.0251 0.08711 0.08346 -0.0167 1.0000 0.0195
-16.000 -1.0466 0.08000 0.07614 -0.0205 1.0000 0.0193
-15.750 -1.0677 0.07340 0.06932 -0.0236 1.0000 0.0191
-15.500 -1.0885 0.06724 0.06292 -0.0261 1.0000 0.0189
-15.250 -1.1083 0.06163 0.05702 -0.0279 1.0000 0.0187
-15.000 -1.1167 0.05776 0.05297 -0.0288 1.0000 0.0186
-14.750 -1.1287 0.05341 0.04834 -0.0294 1.0000 0.0184
-14.500 -1.1284 0.05071 0.04551 -0.0295 1.0000 0.0184
-14.250 -1.1279 0.04783 0.04244 -0.0294 1.0000 0.0183
-14.000 -1.1230 0.04569 0.04020 -0.0292 1.0000 0.0183
-13.750 -1.1166 0.04365 0.03806 -0.0289 1.0000 0.0183
-13.500 -1.1086 0.04164 0.03592 -0.0284 1.0000 0.0182
-13.250 -1.0995 0.03991 0.03411 -0.0280 1.0000 0.0182
-13.000 -1.0891 0.03827 0.03239 -0.0274 1.0000 0.0182
-12.750 -1.0782 0.03674 0.03080 -0.0269 1.0000 0.0182
-12.500 -1.0667 0.03526 0.02926 -0.0263 1.0000 0.0182
-12.250 -1.0547 0.03386 0.02782 -0.0257 1.0000 0.0183
-12.000 -1.0426 0.03249 0.02639 -0.0250 1.0000 0.0182
-11.750 -1.0337 0.03121 0.02508 -0.0237 0.9582 0.0183
-11.500 -0.9877 0.02967 0.02328 -0.0299 0.8644 0.0184
-11.250 -0.9772 0.02863 0.02205 -0.0287 0.8418 0.0183
-11.000 -0.9670 0.02757 0.02091 -0.0276 0.8299 0.0186
-10.750 -0.9566 0.02654 0.01978 -0.0264 0.8207 0.0186
-10.500 -0.9461 0.02550 0.01869 -0.0252 0.8127 0.0188
-10.250 -0.9362 0.02450 0.01760 -0.0239 0.8055 0.0189
-10.000 -0.9264 0.02347 0.01652 -0.0226 0.7990 0.0191
-9.750 -0.9182 0.02243 0.01542 -0.0209 0.7924 0.0191
-9.500 -0.9111 0.02151 0.01441 -0.0190 0.7866 0.0192
-9.250 -0.9036 0.02069 0.01355 -0.0166 0.7810 0.0193
-9.000 -0.8931 0.01998 0.01278 -0.0144 0.7756 0.0194
-8.750 -0.8784 0.01931 0.01205 -0.0129 0.7707 0.0195
-8.500 -0.8619 0.01869 0.01137 -0.0116 0.7661 0.0197
-8.250 -0.8436 0.01807 0.01071 -0.0104 0.7613 0.0199
-8.000 -0.8241 0.01750 0.01009 -0.0094 0.7568 0.0202
-7.750 -0.8035 0.01699 0.00952 -0.0085 0.7528 0.0204
-7.500 -0.7828 0.01647 0.00895 -0.0077 0.7489 0.0209
-7.250 -0.7604 0.01600 0.00847 -0.0070 0.7451 0.0215
-7.000 -0.7371 0.01558 0.00802 -0.0065 0.7408 0.0224
-6.750 -0.7133 0.01519 0.00759 -0.0059 0.7364 0.0234
-6.500 -0.6899 0.01476 0.00713 -0.0053 0.7325 0.0252
-6.250 -0.6662 0.01437 0.00670 -0.0048 0.7288 0.0283
-6.000 -0.6425 0.01388 0.00625 -0.0043 0.7256 0.0351
-5.750 -0.6193 0.01331 0.00581 -0.0038 0.7221 0.0571
-5.500 -0.5956 0.01279 0.00543 -0.0033 0.7186 0.0847
-5.250 -0.5723 0.01222 0.00503 -0.0029 0.7152 0.1183
-5.000 -0.5486 0.01167 0.00466 -0.0025 0.7120 0.1571
-4.750 -0.5251 0.01113 0.00432 -0.0020 0.7084 0.2080
-4.500 -0.5021 0.01040 0.00392 -0.0016 0.7052 0.2767
-4.250 -0.4781 0.00980 0.00359 -0.0013 0.7018 0.3418
-4.000 -0.4540 0.00924 0.00333 -0.0009 0.6982 0.4125
-3.750 -0.4284 0.00890 0.00319 -0.0005 0.6946 0.4635
-3.500 -0.4012 0.00876 0.00311 -0.0003 0.6910 0.4925
-3.250 -0.3735 0.00872 0.00309 -0.0002 0.6873 0.5175
-3.000 -0.3452 0.00865 0.00307 -0.0001 0.6840 0.5358
-2.750 -0.3167 0.00862 0.00306 -0.0001 0.6803 0.5508
-2.500 -0.2880 0.00863 0.00306 -0.0001 0.6768 0.5643
-2.250 -0.2594 0.00863 0.00308 0.0000 0.6736 0.5745
-2.000 -0.2305 0.00871 0.00308 -0.0001 0.6704 0.5845
-1.750 -0.2022 0.00881 0.00320 0.0001 0.6669 0.5953
-1.500 -0.1732 0.00888 0.00326 0.0000 0.6640 0.6052
-1.250 -0.1445 0.00890 0.00335 0.0001 0.6604 0.6138
-1.000 -0.1156 0.00897 0.00341 0.0001 0.6565 0.6219
-0.750 -0.0869 0.00897 0.00340 0.0001 0.6528 0.6282
-0.500 -0.0580 0.00899 0.00343 0.0002 0.6494 0.6330
-0.250 -0.0292 0.00908 0.00349 0.0001 0.6456 0.6373
0.000 0.0000 0.00907 0.00350 0.0000 0.6418 0.6418
0.250 0.0291 0.00908 0.00349 -0.0001 0.6373 0.6457
0.500 0.0580 0.00899 0.00343 -0.0002 0.6330 0.6494
0.750 0.0868 0.00897 0.00340 -0.0001 0.6281 0.6528
1.000 0.1156 0.00897 0.00341 -0.0001 0.6219 0.6565
1.250 0.1445 0.00890 0.00335 -0.0001 0.6138 0.6604
1.500 0.1732 0.00888 0.00326 0.0000 0.6053 0.6640
1.750 0.2021 0.00880 0.00319 0.0000 0.5945 0.6669
2.000 0.2305 0.00870 0.00307 0.0001 0.5842 0.6704
2.250 0.2594 0.00863 0.00308 0.0000 0.5743 0.6735
2.500 0.2880 0.00863 0.00306 0.0001 0.5639 0.6768
2.750 0.3167 0.00862 0.00306 0.0001 0.5508 0.6803
3.000 0.3452 0.00865 0.00307 0.0001 0.5357 0.6840
3.250 0.3735 0.00872 0.00309 0.0002 0.5175 0.6873
3.500 0.4011 0.00876 0.00310 0.0003 0.4921 0.6910
3.750 0.4283 0.00891 0.00319 0.0005 0.4619 0.6946
4.000 0.4540 0.00924 0.00333 0.0009 0.4116 0.6982
4.250 0.4780 0.00981 0.00360 0.0013 0.3405 0.7018
4.500 0.5020 0.01042 0.00393 0.0016 0.2745 0.7052
4.750 0.5252 0.01112 0.00431 0.0020 0.2088 0.7084
5.000 0.5487 0.01166 0.00466 0.0024 0.1590 0.7120
5.250 0.5724 0.01220 0.00503 0.0029 0.1202 0.7152
5.500 0.5956 0.01279 0.00543 0.0033 0.0840 0.7185
6.000 0.6428 0.01385 0.00624 0.0043 0.0359 0.7256
6.250 0.6662 0.01438 0.00671 0.0048 0.0282 0.7288
6.500 0.6900 0.01476 0.00713 0.0053 0.0251 0.7325
6.750 0.7134 0.01519 0.00759 0.0059 0.0235 0.7364
7.000 0.7372 0.01558 0.00802 0.0064 0.0223 0.7408
7.250 0.7605 0.01600 0.00847 0.0070 0.0216 0.7451
7.500 0.7830 0.01647 0.00895 0.0077 0.0209 0.7489
7.750 0.8036 0.01699 0.00952 0.0085 0.0204 0.7528
8.000 0.8242 0.01750 0.01009 0.0094 0.0202 0.7568
8.250 0.8437 0.01807 0.01071 0.0104 0.0199 0.7613
8.500 0.8619 0.01869 0.01137 0.0115 0.0197 0.7662
8.750 0.8785 0.01931 0.01205 0.0129 0.0196 0.7708
9.000 0.8932 0.01999 0.01279 0.0144 0.0194 0.7756
9.250 0.9038 0.02069 0.01355 0.0165 0.0193 0.7811
9.500 0.9114 0.02151 0.01440 0.0189 0.0192 0.7866
9.750 0.9184 0.02243 0.01542 0.0209 0.0192 0.7925
10.000 0.9266 0.02348 0.01653 0.0225 0.0190 0.7990
10.250 0.9366 0.02449 0.01759 0.0238 0.0190 0.8056
10.500 0.9467 0.02547 0.01866 0.0252 0.0188 0.8127
10.750 0.9571 0.02652 0.01977 0.0264 0.0187 0.8208
11.000 0.9676 0.02754 0.02088 0.0275 0.0186 0.8300
11.250 0.9778 0.02863 0.02206 0.0287 0.0184 0.8419
11.500 0.9885 0.02961 0.02322 0.0297 0.0183 0.8649
11.750 1.0346 0.03121 0.02508 0.0236 0.0183 0.9612
12.000 1.0434 0.03246 0.02636 0.0249 0.0182 1.0000
12.250 1.0555 0.03385 0.02780 0.0256 0.0182 1.0000
12.500 1.0675 0.03523 0.02922 0.0261 0.0182 1.0000
12.750 1.0791 0.03671 0.03077 0.0268 0.0182 1.0000
13.000 1.0901 0.03825 0.03237 0.0273 0.0182 1.0000
13.250 1.1004 0.03986 0.03405 0.0278 0.0182 1.0000
13.500 1.1097 0.04155 0.03582 0.0282 0.0181 1.0000
13.750 1.1177 0.04364 0.03806 0.0288 0.0183 1.0000
14.000 1.1244 0.04554 0.04002 0.0290 0.0182 1.0000
14.250 1.1278 0.04809 0.04275 0.0294 0.0184 1.0000
14.500 1.1302 0.05056 0.04535 0.0294 0.0184 1.0000
14.750 1.1274 0.05370 0.04868 0.0292 0.0185 1.0000
15.000 1.1155 0.05808 0.05333 0.0286 0.0187 1.0000
15.250 1.1055 0.06217 0.05762 0.0276 0.0188 1.0000
15.500 1.0890 0.06733 0.06302 0.0259 0.0189 1.0000
15.750 1.0670 0.07370 0.06964 0.0234 0.0192 1.0000
16.000 1.0477 0.08002 0.07617 0.0203 0.0193 1.0000
16.250 1.0256 0.08720 0.08356 0.0164 0.0194 1.0000
16.500 1.0017 0.09530 0.09184 0.0117 0.0197 1.0000
16.750 0.9764 0.10417 0.10090 0.0063 0.0199 1.0000
17.000 0.9374 0.11681 0.11378 -0.0020 0.0200 1.0000
17.250 0.9075 0.12825 0.12535 -0.0093 0.0202 1.0000
17.500 0.9071 0.13263 0.12974 -0.0114 0.0204 1.0000
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